Analysis of a Hinge-Connected Flapping Plate with an Implemented Torsional Spring Model
|
|
- Brandon Pope
- 5 years ago
- Views:
Transcription
1 Analysis of a Hinge-Connected Flapping Plate with an Implemented Torsional Spring Model Zach Gaston 1, Hui Wan 2 and Haibo Dong 3 Department of Mechanical & Materials Engineering, Wright State University, Dayton, OH Michael V. OL 4 Air Force Research Laboratory Wright-Patterson AFB, OH Hovering hinged plates are used to study the effects of passive deflection on aerodynamic performance using two-dimensional Direct Numerical Simulations (DNS) at low Reynolds numbers (Re). The hinge is modeled as a torsional spring at the leading edge, where the prescribed motion is applied. The influence of forced-to-natural frequency ratio (hinge stiffness) is studied, concluding that averaged glide ratio (lift-to-drag) improved as the hinge became stiffer, with a peak performance occurring for f = 1 4. The influences of stroketo-chord ratio on a hovering hinged plate are also investigated, concluding that glide ratio improved as the ratio increased for the frequency ratio that we studied. Nomenclature A x = Amplitude of stroke amplitude in x-direction (m) and orientation angle (deg) C, C = Lift coefficient and its average over flapping cycles C, C = Drag coefficient and its average over flapping cycles c, h = Chord and thickness of the plate (m). c is chosen as characteristic length k = Hinge Torsional spring stiffness (N/m) J = Moment of Inertia of plate (m 4 ) ω, ω = Forced and natural frequency of plate Re = St = " Reynolds number, is kinematic viscosity of fluid (m2 /s) " Strouhal number Glide Ratio = C / C, also known as lift-to-drag ratio U = Characteristic speed (m/s), based on maximum leading edge speed = Deflection angle of hinged plate, = Density of body and fluid respectively (kg/m 3 ) F = Net body force on plate, comprised of gravity and buoyancy (N) F = Aerodynamic force on body surface (N) = Torque generated by gravitational force and buoyancy, with respect to the hinge (Nm) = Torque with respect to the mass center of hinged body (Nm) 1 Graduate Student, AIAA Student Member, gaston.8@wright.edu 2 Research Associate, hui.wan@wright.edu 3 Associate Professor, AIAA Associate Fellow, haibo.dong@wright.edu. 4 Aerospace Engineer, AIAA Associate Fellow, Michael.Ol@wpafb.af.mil
2 I. Introduction Gaining a better understanding of the role of flexibility in flight for nature s creatures has been a major goal in research for both biologists and engineers alike. Understanding deformation mechanisms, whether active or passive, could lead to better designs for the development of micro air vehicles. Many researchers have made efforts in modeling deformable bodies in fluid-body interactions. Eldredge 1 performed numerical investigations on hinged bodies using the vortex particle method for fish modeled as a three rigid-link system. Kanso et al. 2, who studied a propulsion system in an inviscid medium, performed similar works. Passive pitching was modeled to study the effects of wing torsional flexibility and lift generation for Dipteran flight by Ishihara et al. 3 Vanella et al. 4 studied aerodynamic performance in hovering two-dimensional two-link wings numerically, arising at the conclusion that flexibility can promote better aerodynamic performance via lift-to-drag ratio. Zhao et al. 5 found otherwise experimentally when using materials with varying flexural stiffness to model a flapping wing. Granlund et al. 6 studied hovering motions of plates with free-to-pivot hinges located at the leading edge experimentally, concluding that the plate produces motions akin to normal-hover with delayed rotation. Wan et al. 7 found similar results modeling a free-to-pivot hinge located at the leading edge while also studying hinge locations and stroke amplitude effects on aerodynamic performance. In this work, deformable flapping wings are modeled as a hovering rigid membrane plate with prescribed leading edge kinematics. A torsional spring, whose stiffness is governed by a ratio of forced-to-natural frequency, is placed at the leading edge and driven sinusoidally with the deflection of the membrane determined by its interaction with the surrounding fluid. The effects of hinge stiffness and stroke amplitude are studied and aerodynamic performance is quantified by calculations of lift and drag. II. Governing Equation and Method of Fluid-Body Coupling The incompressible Navier Stokes (NS) equations can be written in tensor form as = 0, " + = " + (1) " in which u i (i = 1,2) is the velocity components, and p is the pressure. The NS equations are solved using a finitedifference based Cartesian grid immersed boundary method 8. A second-order central difference scheme in space is employed and a second-order accurate fraction-step method for time advancement is used as well. More validation on the DNS solver can be found in Mittal et al. 8 and Dong et al 9. (a) Figure 1. Flapping motion diagram (a) and schematic of hinged plate model with LE The hinged plates rotate and translate about the leading edge (LE) in the x-y plane, which is shown in Figure 1. The plate s prescribed motion is sinusoida, prescribed in the x-direction, with the deflection angle,, determined from the interaction between the body and the surrounding fluid. The LE equations of motion are given by Equation 2. () = cos (2"#), () = 0, (2) In general, the equations of motion for a rigid body can be written as
3 () =, (3) " = + + where the total force () includes the corrected gravitational force after taking into account of buoyancy, aerodynamic force on plate surface, and other external forces (e.g, force at the hinge location ). The net torque is with respect to the mass center of body, including aerodynamic torque and torque generated from external sources. K is the spring constant. The aerodynamic force and torque are obtained by the surface integration of pressure p and viscous stress tensor, and can be given as: = ( )", = ( ) " where is the outer normal to the body surface, and is the vector from mass center to certain surface element. The implicit methodology used in coupling the body and fluid is described in Wan et al. 7 III. Results As previously mentioned, a hovering one-link plate is studied. The Reynolds numbers in the simulations are 94.2, and 235.5, based on the maximum leading edge translation speed. The effects of stroke-to-chord ratio, A x /c, and frequency ratio, f, will be discussed. In the hovering case, the Strouhal number (St) can be further expressed as, when the characteristic speed is substituted into its definition. Thus, the stroke-to-chord ratio effect is equivalent to the Strouhal number effect, at a fixed Re on the aerodynamic performance of a hovering plate. The forced-to-natural frequency ratio is used to balance the inertial loading with the stiffness of the hinge. The hinge stiffness, k, is determined by the plate s natural frequency and moment of inertia ( n = (4) k / J ). In our study, the mass ratio defined as is 0.2. The mass ratio of a cranefly and dragonfly is estimated to be 0.34 (Ishihara et al.10 ) and 0.8 (Chen et al. 11 ) respectively. Hence the wing in the current study is light and most analogous to a cranefly. In current study, the plate is modeled as an infinitesimally thin membrane. The thickness of plate, h, comes into the parameter mass ratio defined as. Therefore, for a case of density ratio = 20, the ratio of thickness to chord length = 0.01, which is suitable to be assumed as a membrane. If the density ratio between solid and fluid increases, the ratio can be further reduced and the membrane assumption is more qualified. The methodology and ability of handling infinitesimally thin bodies are demonstrated in Mittal et al. 8 A. Frequency Ratio Effects In the first study, hinge-stiffness is examined over the same kinematic profile membrane plate with prescribed hover kinematics, A x /c=3 and Re = 94.2, 188.4, and 235.5, by varying the force-to-natural frequency ratio, ranging from f = 1 / 2.5 to 1 / 6. Figure 2 shows a comparison of vorticity contour snapshots at varying instances of a characteristic stroke for f = and f = 1 4, which represent the least and most aerodynamically efficient cases, respectively. Red contour magnitudes represent counter-clockwise vorticity and blue contours represent clockwise rotating vorticity. At t/t = 3.0, the leading edge is at its right-most extreme. The trailing edge is deflected to the left, in accordance with the inertial loading of the plate. At this instance, which occurs several periods from start, the more rigid of the two plates, f = 1 4, has developed a strong leading edge vortex (LEV) which has began to detach and shed from the lee side of the plate. The trailing edge vortex (TEV) has already developed and began to shed, forming a vortex sheet. In comparison between the least and most efficient cases, the most efficient case appears to have a much stronger downwash. This is facilitated by the release of stored energy in the plate. Because the plate has been inclined from its rest position, it has developed some stored energy in the torsional spring, which, at stroke reversal,
4 is released, helping convect the shed vortices in the downwash of the plate. For both cases, as the stroke progresses to t/t = 3.25, the previously forming LEV is attached to the windward-side of the plate and a counter-rotating LEV is formed and attached to the lee-side. It is at this moment that a reduction in surface pressure on the back of the plate occurs, causing an increase in lift. The position of the previously shed TEV varies in either case. (a) (f) t/t = 3.0 (g) t/t = 3.25 (c) (h) t/t = 3.5 (d) (i) t/t = 3.75 (e) (j) t/t = 4.0 Figure 2. Vorticity comparisons for Ax/c =3 and Re = between f = (a-e) and f n = 1 4 (i-j) The more stiff hinge forms a stronger downwash, forcing the shed TEV further downstream where it faces no risk of interacting with the newly formed LEV. However, in the less stiff hinge, the shed TEV is not convected as far downstream, allowing it to interact with the windward-side LEV on the plate. This results in a less pronounced vortex and also forces the plate to incline at greater angle. At t/t = 3.5, the plates are now at their left extreme. The
5 more rigid hinge has begun to form a trailing vortex sheet, while the counter-rotating LEV vortex has began to detach, resulting in a drop in lift. This phenomena is not present in the less stiff hinge, where the interaction between the previously shed vortex has disrupted the formation of the trailing vortex sheet. At this moment of stroke reversal, the stored torsional spring energy is released, helping to propel the shedding vortices away from the plate, downstream. This strong downwash is essential to promoting increases in lift production which occur at mid-stroke when the pair of LEV are formed and attached to the plate. It is noted that this is often when the plate is at its maximum deflection angle and also when it is at its maximum translational velocity. This stored energy effect is observed in the upstroke as well, where vortex patterns similar to those in the downstroke are observed. Cases of various frequency ratios are also simulated. The vortex development for these cases follows patterns shown in Figure 2. (a) Figure 3. Force history for varying frequency ratios. Lift coefficient (a) and drag coefficient. f = (green), 1 3 (blue), 1 4 (orange), 1 5 (pink), and 1 6 (black). The force coefficient history for two characteristic periods has been shown in Figure 3. Peaks in both lift and drag coefficient are observed at t/t = 0.25 and 0.75, where the plate is at midstroke. This increase is observed when a low pressure region is created in the attachment of a counter-rotating LEV on the lee side of the plate while a high pressure region is observed from the previously formed LEV s attachment to the windward side. For higher frequency ratios (less rigid hinges) an oscillation in both lift and drag coefficients occurs at midstroke. This is caused by the break down of the attached vortices upon their interaction with the previously shed vortices. For more rigid hinges, which display a stronger downwash, this secondary force oscillation at midstroke does not occur because there is less interaction between attached and shed vortices. It is also noted that for all frequency ratios at or above f n = 15 f, slightly more lift is generated in the upstroke than in the downstroke. At n = 16, which was the most stiff hinge that was simulated, more lift is generated in the downstroke. However, for all frequency ratios at or below f n = 15, drag was higher in the upstroke. Any hinge that was less rigid than this cutoff has an even split of drag in both the up and downstroke.
6 Figure 4 shows the glide ratio ( C L CD ) as an aerodynamic performance metric across a range of frequency ratios for three different Reynolds numbers. This value is determined by cycleaveraged lift and drag coefficients. It was observed that at low Re and low frequency ratios (i.e. more rigid hinges), Reynolds numbers have very little effects on the performance of the hovering plate. However, for less rigid hinges, the Re effects are more noticeable. The trends in performance are similar across all of the chosen Reynolds numbers. A peak in performance was found for f = 1 4, where more lift was generated in the upstroke than in the downstroke, but the drag followed the same trends for both strokes. Figure 4. Glide ratio versus frequency ratio Hinges that were more rigid than this optimum cases had a stronger downwash but also had higher drag coefficients as those plates had a large angle of attack at midstroke. B. Stroke-to-chord Ratio Effects In the second study, stroke amplitude of the prescribed hover kinematic profile is examined using the same hinge model for all cases, f n = 1 6, and Re = based on maximum LE velocity. Various stroke-to-chord ratios are used, ranging from A x c = 0.5 to 4. Figure 5 shows a comparison of vorticity contour snapshots at varying instances of a characteristic stroke for A x c = 2 and A x c = 4. It is noted that this hinge is relatively rigid in comparison to the other hinges modeled in the above results. At t/t = 3.0, the plate begins at the right extreme with the larger stroke to chord ratio having more stored energy in the torsional spring, given by the delayed inclination of the plate. This is contrary to the smaller stroke amplitude, which is barely inclined at the start. It should be noted that this is a qualitative comparison of stored energy, however, because the hinge stiffness is equivalent in both cases, a greater inclination corresponds to a higher stored energy in the torsional spring hinge. The smaller stroke amplitude case has a vortex sheet comprised of the shedding TEV and a LEV that has begun to separate from the plate. The larger stroke s LEV has separate and the TEV sheet has completely detached prior to the stroke with a new TEV forming in its place. As the stroke moves to t/t = 3.25, a pair of LEVs form on the plate, with the lee-side attached on the larger stroke ratio. This yields a low pressure on the back of the plate, causing a more dramatic increase in lift at midstroke as the stroke-to-chord ratio increases. The plate is inclined at approximately the same angle through midstroke in both cases. As the downstroke completes at t/t = 3.5, a TEV sheet is still strongly attached to the smaller stroke ratio and the stored energy is decreased. However, a new TEV is formed for the larger stroke ratio, with more stored energy present in the hinge. After stroke reversal, at t/t = 3.75, a larger vortex is attached to the back of the larger stroke ratio case, alluding to a lower pressure on the back of the plate, resulting in a higher lift at the midpoint of the upstroke. For the smaller stroke amplitude case, a previously shed vortex is left behind to interact with plate as the stroke increases, possibly causing a rise in drag during the upstroke.
7 (a) (f) t/t = 3.0 (g) t/t = 3.25 (c) (h) t/t = 3.5 (d) (i) t/t = 3.75 (e) (j) t/t = 4.0 Figure 5. Vorticity comparisons for f = 1 6 and Re = between A x /c=2 (a-e) and A x /c=4 (i-j) Figure 6 shows the force coefficient histories from the simulations with varying stroke-to-chord ratios. For a relatively rigid plate such as the one used for this study, it is noted that the deflection angle is low in comparison to less-stiff hinges, causing a higher angle of attack during the stroke cycle, which results in higher drag. For hover, with no incoming flow, low stroke-to-chord ratios are not able to generate positive lift with ease, and the drag is very high, as overcoming the momentum of the fluid at stroke reversal requires a great deal of force. At and beyond A x /c = 2, lift coefficients follow similar trends to one another in both the down and upstrokes, but it is noted that as stroke-to-chord ratio increases, the drag is significantly decreased. Since St is a function solely of stroke-to-chord
8 ratio, it goes to say that as St decreases, so does drag, while it has little affect on lift production in hovering conditions. (a) Figure 6. Force history for varying dimensionless stroke amplitudes for f = 1 6 and Re = coefficient (a) and drag coefficient. A x c = 1 (green), 2 (blue), 3 (orange), and 4 (black). Lift Figure 7. amplitude Glide ratio versus dimensionless stroke Figure 7 shows a plot of glide ratio across the various stroke-to-chord ratios used in this study. Comparing the glide ratio as a function of dimensionless stroke amplitude shows that as stroke-to-chord ratio increase, the plate becomes more aerodynamically effective. One thing to note with this study is that input power and efficiency from such a metric has not been considered yet, so this increase in effectiveness may come at the cost of an increase in input power. This type of study will have to be further investigated to better explain the role of stroketo-chord ratio for a hovering, torsional spring hinged connected plate. IV. Conclusion Hovering hinged plates with torsional spring hinges were simulated as a fluid-body interaction problem to better understand passive deflection of a flapping plate. All simulations used membrane plates with prescribed kinematics given to a torsional spring hinge mechanism located at the leading edge of the plate. The leading edge motion was coupled with the fluid solver allowing the body to deflect naturally through its interaction with the surrounding fluid. The effects of hinge stiffness were studied by exploring the force-to-natural frequency of the plate. It was determined that the hinge stiffness plays a role in controlling flow, with more rigid plates creating a stronger downwash. The stored energy in the spring is able to direct the flow in a passive, but effective manner. It was also determined that a definitive peak in performance for the prescribed kinematics was observed from the glide ratio. Beyond this peak, as the hinge became more rigid, no benefits were observed. The effects of stroke-to-chord ratio in flapping amplitude was also studied for one particular hinge. It was determined that as stroke-to-chord ratio increased beyond a minimum range required to overcome the fluid momentum in hover conditions and provide
9 positive lift, the lift production remained consistent over the tested flapping amplitudes. However, as stroke increased, the drag began to decrease, causing a notable increase in performance. Through these studies, it is noted that a leading edge hinged plate with some torsional stiffness is effective in passively controlling flow and promoting a better aerodynamic performance. Further studies on the effects of stroke amplitude and hinge stiffness could provide a better model for a simple, replicable flapping mechanism in hover. Acknowledgments This work is supported by AFOSR FA monitored by Dr. Douglas Smith, 2011 DAGSI program monitored by Dr. Michael Ol at AFRL and 2011 AFRL/RB summer faculty program monitored by Dr. Philip Beran at AFRL/RBSD. References 1. J. D. Eldredge, "Dynamically coupled fluid-body interactions in vorticity-based numerical simulations," Journal of Computational Physics 227 (21), (2008). 2. E. Kanso, J. E. Marsden, C. W. Rowley, and J. B. Melli-Huber, "Locomotion of articulated bodies in a perfect fluid," J Nonlinear Sci 15 (4), (2005). 3. D. Ishihara, T. Horie, and M. Denda, "A two-dimensional computational study on the fluid-structure interaction cause of wing pitch changes in dipteran flapping flight," Journal of Experimental Biology 212 (1), 1-10 (2009). 4. M. Vanella, T. Fitzgerald, S. Preidikman, E. Balaras, and B. Balachandran, "Influence of flexibility on the aerodynamic performance of a hovering wing," Journal of Experimental Biology 212 (1), (2009). 5. L. Zhao, Q. Huang, X. Deng, and S. Sane, "The effect of chord-wise flexibility on the aerodynamic force generation of flapping wings: experimental studies", in 2009 IEEE International Conference on Robotics and Automation (Kobe, Japan, 2009). 6. K. Granlund, Michael OL, L. Bernal, and S. Kast, "Experiments on free-to-pivot hover motions of flat pates", 49th AIAA Aerospace Sciences Meeting Orlando, FL, Hui Wan, Haibo Dong, and George P. Huang Computational Fluid-Body Interaction of Hinge Connected Flapping Plate in Hover, 49th AIAA Aerospace Sciences Meeting, , Mittal, R., Dong, H., Bozkurttas, M., Najjar, F. M., Vargas, A., and von Loebbecke, A. "A versatile sharp interface immersed boundary method for incompressible flows with complex boundaries," Journal of Computational Physics Vol. 227, No. 10, 2008, pp Dong, H., Mittal, R., and Najjar, F. M. "Wake topology and hydrodynamic performance of low-aspect-ratio flapping foils," Journal of Fluid Mechanics Vol. 566, 2006, pp Ishihara, D., Horie, T., and Denda, M. "A two-dimensional computational study on the fluid-structure interaction cause of wing pitch changes in dipteran flapping flight," Journal of Experimental Biology Vol. 212, No. 1, 2009, pp Chen, J. S., Chen, J. Y., and Chou, Y. F. "On the natural frequencies and mode shapes of dragonfly wings," Journal of Sound and Vibration Vol. 313, No. 3-5, 2008, pp
Computational Analysis of Hovering Hummingbird Flight
Computational Analysis of Hovering Hummingbird Flight Zongxian Liang 1 and Haibo Dong 2 Department of Mechanical & Materials Engineering, Wright State University, Dayton, OH 45435 Mingjun Wei 3 Department
More informationComputational Analysis of Hovering Hummingbird Flight
48th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition 4-7 January 2010, Orlando, Florida AIAA 2010-555 Computational Analysis of Hovering Hummingbird Flight Zongxian
More information(This is a sample cover image for this issue. The actual cover is not yet available at this time.)
(This is a sample cover image for this issue. The actual cover is not yet available at this time.) This is an open access article which appeared in a ournal published by Elsevier. This article is free
More informationSENSITIVITY ANALYSIS OF THE FACTORS AFFECTING FORCE GENERATION BY WING FLAPPING MOTION
Proceedings of the ASME 2013 International Mechanical Engineering Congress and Exposition IMECE2013 November 15-21, 2013, San Diego, California, USA IMECE2013-65472 SENSITIVITY ANALYSIS OF THE FACTORS
More informationLift Enhancement by Dynamically Changing Wingspan. in Forward Flapping Flight (09/10/2013)
Lift Enhancement by Dynamically Changing Wingspan in Forward Flapping Flight Shizhao Wang 1, Xing Zhang 1, Guowei He 1a), ianshu Liu 2,1 (09/10/2013) 1 he State Key Laboratory of Nonlinear Mechanics, Institute
More informationFig. 1. Bending-Torsion Foil Flutter
27 TH INTERNATIONAL CONGRESS OF THE AERONAUTICAL SCIENCES EXTRACTING POWER IN JET STREAMS: PUSHING THE PERFORMANCE OF FLAPPING WING TECHNOLOGY M.F. Platzer*, M.A. Ashraf**, J. Young**, and J.C.S. Lai**
More informationRESEARCH ARTICLE Aerodynamic effects of corrugation in flapping insect wings in hovering flight
3 The Journal of Experimental iology, 3-. Published by The Company of iologists Ltd doi:./jeb.6375 RESERCH RTIE erodynamic effects of corrugation in flapping insect wings in hovering flight Xue Guang Meng*,
More informationSTUDY OF THREE-DIMENSIONAL SYNTHETIC JET FLOWFIELDS USING DIRECT NUMERICAL SIMULATION.
42 nd AIAA Aerospace Sciences Meeting and Exhibit 5-8 January 2004/Reno, NV STUDY OF THREE-DIMENSIONAL SYNTHETIC JET FLOWFIELDS USING DIRECT NUMERICAL SIMULATION. B.R.Ravi * and R. Mittal, Department of
More informationA COMPUTATIONAL FLUID DYNAMICS STUDY OF CLAP AND FLING IN THE SMALLEST INSECTS. Laura A. Miller* and Charles S. Peskin**
A COMPUTATIONAL FLUID DYNAMICS STUDY OF CLAP AND FLING IN THE SMALLEST INSECTS Laura A. Miller* and Charles S. Peskin** *Department of Mathematics, University of Utah, 155 South 1400 East, Salt Lake City,
More informationA Biologically Inspired Computational Study of Flow Past Tandem Flapping Foils
A Biologically Inspired Computational Study of Flow Past andem Flapping Foils I. Akhtar * and R. Mittal Department of Mechanical & Aerospace Engineering he George Washington University, Washington DC 20052
More information1. Fluid Dynamics Around Airfoils
1. Fluid Dynamics Around Airfoils Two-dimensional flow around a streamlined shape Foces on an airfoil Distribution of pressue coefficient over an airfoil The variation of the lift coefficient with the
More informationDynamic pitching of an elastic rectangular wing in hovering motion
Under consideration for publication in J. Fluid Mech. Dynamic pitching of an elastic rectangular wing in hovering motion Hu Dai, Haoxiang Luo, and James F. Doyle 2 Department of Mechanical Engineering,
More informationEffects of Flexibility on the Aerodynamic Performance of Flapping Wings
6th AIAA Theoretical Fluid Mechanics Conference 27-30 June 2011, Honolulu, Hawaii AIAA 2011-3121 Effects of Flexibility on the Aerodynamic Performance of Flapping Wings Chang-kwon Kang 1, Hikaru Aono 2,
More informationModeling of Instantaneous Passive Pitch of Flexible Flapping Wings
Fluid Dynamics and Co-located Conferences June 24-27, 2013, San Diego, CA 43rd Fluid Dynamics Conference AIAA 2013-2469 Modeling of Instantaneous Passive Pitch of Flexible Flapping Wings Chang-kwon Kang
More informationImplementing a Partitioned Algorithm for Fluid-Structure Interaction of Flexible Flapping Wings within Overture
10 th Symposimum on Overset Composite Grids and Solution Technology, NASA Ames Research Center Moffett Field, California, USA 1 Implementing a Partitioned Algorithm for Fluid-Structure Interaction of Flexible
More informationABSTRACT PARAMETRIC INVESTIGATIONS INTO FLUID-STRUCTURE INTERACTIONS IN HOVERING FLAPPING FLIGHT. Jesse Maxwell, 2013
ABSTRACT Title of Thesis: PARAMETRIC INVESTIGATIONS INTO FLUID-STRUCTURE INTERACTIONS IN HOVERING FLAPPING FLIGHT Jesse Maxwell, 2013 Thesis Directed By: Professor Balakumar Balachandran Department of
More informationWhen vortices stick: an aerodynamic transition in tiny insect flight
The Journal of Experimental Biology 7, 7-88 Published by The Company of Biologists 4 doi:.4/jeb.8 7 When vortices stick: an aerodynamic transition in tiny insect flight Laura A. Miller* and Charles S.
More informationTwo-Dimensional Aerodynamic Models of Insect Flight for Robotic Flapping Wing Mechanisms of Maximum Efficiency
Journal of Bionic Engineering 5 (2008) 1 11 Two-Dimensional Aerodynamic Models of Insect Flight for Robotic Flapping Wing Mechanisms of Maximum Efficiency Thien-Tong Nguyen 1, Doyoung Byun 2 1. Department
More informationA computational fluid dynamics of clap and fling in the smallest insects
The Journal of Experimental Biology 8, 95- Published by The Company of Biologists 5 doi:.4/jeb.376 95 A computational fluid dynamics of clap and fling in the smallest insects Laura A. Miller, * and Charles
More informationUnsteady Force Generation and Vortex Dynamics of Pitching and Plunging Flat Plates at Low Reynolds Number
49th AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition 4-7 January 2011, Orlando, Florida AIAA 2011-220 Unsteady Force Generation and Vortex Dynamics of Pitching
More informationEffect of Pivot Point on Aerodynamic Force and Vortical Structure of Pitching Flat Plate Wings
5st AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition 7 - January 23, Grapevine (Dallas/Ft. Worth Region), Texas AIAA 23-792 Effect of Pivot Point on Aerodynamic
More informationAerodynamic force analysis in high Reynolds number flows by Lamb vector integration
Aerodynamic force analysis in high Reynolds number flows by Lamb vector integration Claudio Marongiu, Renato Tognaccini 2 CIRA, Italian Center for Aerospace Research, Capua (CE), Italy E-mail: c.marongiu@cira.it
More informationAeroelastic Analysis Of Membrane Wings
Aeroelastic Analysis Of Membrane Wings Soumitra P. Banerjee and Mayuresh J. Patil Virginia Polytechnic Institute and State University, Blacksburg, Virginia 46-3 The physics of flapping is very important
More informationNUMERICAL SIMULATION OF SELF-PROPELLED FLYING OF A THREE-DIMENSIONAL BIRD WITH FLAPPING WINGS
NUMERICAL SIMULATION OF SELF-PROPELLED FLYING OF A THREE-DIMENSIONAL BIRD WITH FLAPPING WINGS WU Chui-Jie, ZHU Lin-Lin State Key Laboratory of Structural Analysis for Industrial Equipment, School of Aeronautics
More informationMotion Kinematics vs. Angle of Attack Effects in High-Frequency Airfoil Pitch/Plunge
Motion Kinematics vs. Angle of Attack Effects in High-Frequency Airfoil Pitch/Plunge Michael V. OL 1 Air Force Research Laboratory Wright-Patterson AFB, OH 45433 Haibo Dong 2 and Charles Webb 3 Department
More informationOptimization of Flapping Airfoils for Maximum Thrust and Propulsive Efficiency I. H. Tuncer, M. Kay
Czech Technical University in Prague Acta Polytechnica Vol. 44 No. 1/2004 Optimization of Flapping Airfoils for Maximum Thrust and Propulsive Efficiency I. H. Tuncer, M. Kay A numerical optimization algorithm
More informationUnsteady Flow and Aerodynamic Effect of a Dynamic Trailing-Edge Flap in Flapping Flight
Unsteady Flow and Aerodynamic Effect of a Dynamic Trailing-Edge Flap in Flapping Flight A Thesis Presented to the faculty of the School of Engineering and Applied Science University of Virginia In Partial
More informationMestrado Integrado em Engenharia Mecânica Aerodynamics 1 st Semester 2012/13
Mestrado Integrado em Engenharia Mecânica Aerodynamics 1 st Semester 212/13 Exam 2ª época, 2 February 213 Name : Time : 8: Number: Duration : 3 hours 1 st Part : No textbooks/notes allowed 2 nd Part :
More informationThe wings and the body shape of Manduca sexta and Agrius convolvuli are compared in
1 Wing and body shape of Manduca sexta and Agrius convolvuli The wings and the body shape of Manduca sexta and Agrius convolvuli are compared in terms of the aspect ratio of forewing AR fw (wing length
More informationThe Dynamics of Passive Wing-Pitching in Hovering Flight of Flapping Micro Air Vehicles Using Three-Dimensional Aerodynamic Simulations
AIAA SciTech 4-8 January 216, San Diego, California, USA AIAA Atmospheric Flight Mechanics Conference AIAA 216-13 The Dynamics of Passive Wing-Pitching in Hovering Flight of Flapping Micro Air Vehicles
More informationCOMPUTATIONAL SIMULATION OF THE FLOW PAST AN AIRFOIL FOR AN UNMANNED AERIAL VEHICLE
COMPUTATIONAL SIMULATION OF THE FLOW PAST AN AIRFOIL FOR AN UNMANNED AERIAL VEHICLE L. Velázquez-Araque 1 and J. Nožička 2 1 Division of Thermal fluids, Department of Mechanical Engineering, National University
More informationA wing characterization method for flapping-wing robotic insects
213 IEEE/RSJ International Conference on Intelligent Robots and Systems (IROS) November 3-7, 213. Tokyo, Japan A wing characterization method for flapping-wing robotic insects Alexis Lussier Desbiens*,
More informationLow Reynolds Number Flow Dynamics and Control of a Pitching. Airfoil with Elastically Mounted Flap Actuator
Low Reynolds Number Flow Dynamics and Control of a Pitching Airfoil with Elastically Mounted Flap Actuator Final Report by Sourabh V. Apte School of Mechanical Industrial Manufacturing Engineering Oregon
More informationEffects of Unequal Pitch and Plunge Airfoil Motion Frequency on Aerodynamic Response
Effects of Unequal Pitch and Plunge Airfoil Motion Frequency on Aerodynamic Response C. Webb *, H. Dong Department of Mechanical & Materials Engineering, Wright State University Dayton, OH 45435, Michael
More informationModeling of Pitching and Plunging Airfoils at Reynolds Number between and
27th AIAA Applied Aerodynamics Conference 22-25 June 2009, San Antonio, Texas AIAA 2009-4100 Modeling of Pitching and Plunging Airfoils at Reynolds Number between 1 10 4 and 6 10 4 Chang-kwon Kang 1 *,
More informationThrust and Efficiency of Propulsion by Oscillating Foils
Thrust and Efficiency of Propulsion by Oscillating Foils J. Young, J.C.S. Lai, M.Kaya 2 and I.H. Tuncer 2 School of Aerospace, Civil and Mechanical Engineering, UNSW@ADFA, Australian Defence Force Academy,
More informationEnclosure enhancement of flight performance
THEORETICAL & APPLIED MECHANICS LETTERS, 23 (21) Enclosure enhancement of flight performance Mehdi Ghommem, 1, a) Daniel Garcia, 2 Victor M. Calo 3 1) Center for Numerical Porous Media (NumPor), King Abdullah
More informationNumerical and experimental investigation of the role of flexibility in flapping wing flight
36th AIAA Fluid Dynamics Conference and Exhibit 5-8 June 26, San Francisco, California AIAA 26-3211 Numerical and experimental investigation ohe role of flexibility in flapping wing flight Jonathan Toomey
More informationREPORT DOCUMENTATION PAGE
REPORT DOCUMENTATION PAGE Form Approved OMB NO. 0704-0188 The public reporting burden for this collection of information is estimated to average 1 hour per response, including the time for reviewing instructions,
More informationABSTRACT. travels through the wing reducing the drag forces generated. When the wings are in
ABSTRACT Tiny insects use a process called clap and fling to augment the lift forces generated during flight. The one disadvantage to using this method is the drag forces created when the wings fling apart
More informationOn the Aerodynamic Performance of Dragonfly Wing Section in Gliding Mode
Advances in Aerospace Science and Applications. ISSN 2277-3223 Volume 3, Number 3 (2013), pp. 227-234 Research India Publications http://www.ripublication.com/aasa.htm On the Aerodynamic Performance of
More informationA flow control mechanism in wing flapping with stroke asymmetry during insect forward flight
Acta Mech Sinica (2005) 21, 218 227 DOI 10.1007/s10409-005-0032-z RESEARCH PAPER Yongliang Yu Binggang Tong A flow control mechanism in wing flapping with stroke asymmetry during insect forward flight
More informationViscous investigation of a flapping foil propulsor
IOP Conference Series: Materials Science and Engineering PAPER OPEN ACCESS Viscous investigation of a flapping foil propulsor To cite this article: Attapol Posri et al 2018 IOP Conf. Ser.: Mater. Sci.
More informationSIMULATION OF GAS FLOW OVER MICRO-SCALE AIRFOILS USING A HYBRID CONTINUUM-PARTICLE APPROACH
33rd AIAA Fluid Dynamics Conference and Exhibit 3-6 June 3, Orlando, Florida AIAA 3-44 33 rd AIAA Fluid Dynamics Conference and Exhibit / Orlando, Florida / 3-6 Jun 3 SIMULATION OF GAS FLOW OVER MICRO-SCALE
More informationUnsteady aerodynamic forces of a flapping wing
The Journal of Experimental Biology 7, 37-5 Published by The Company of Biologists 4 doi:.4/jeb.868 37 Unsteady aerodynamic forces of a flapping wing Jiang Hao Wu and Mao Sun* Institute of Fluid Mechanics,
More informationSimulation of Aeroelastic System with Aerodynamic Nonlinearity
Simulation of Aeroelastic System with Aerodynamic Nonlinearity Muhamad Khairil Hafizi Mohd Zorkipli School of Aerospace Engineering, Universiti Sains Malaysia, Penang, MALAYSIA Norizham Abdul Razak School
More informationComputation of Inertial Forces and Torques Associated with. Flapping Wings
AIAA Guidance, Navigation, and Control Conference 3-6 August, Minneapolis, Minnesota AIAA -498 Computation of Forces and Torques Associated with Flapping Wings Michael W. Oppenheimer Downloaded by UNIVERSITY
More informationSuppression of vortex-induced vibration of a circular cylinder using
Suppression of vortex-induced vibration of a circular cylinder using thermal effects Hui Wan 1,2, a) 1 1, b) and Soumya S. Patnaik 1 Power and Control Division, Aerospace Systems Directorate, Air Force
More informationFlexible clap and fling in tiny insect flight
376 The Journal of Experimental Biology, 376-39 Published by The Company of Biologists 9 doi:./jeb.866 Flexible clap and fling in tiny insect flight Laura A. Miller* and Charles S. Peskin Department of
More informationBLUFF-BODY AERODYNAMICS
International Advanced School on WIND-EXCITED AND AEROELASTIC VIBRATIONS OF STRUCTURES Genoa, Italy, June 12-16, 2000 BLUFF-BODY AERODYNAMICS Lecture Notes by Guido Buresti Department of Aerospace Engineering
More informationNUMERICAL INVESTIGATION OF THE FLOW OVER A GOLF BALL IN THE SUBCRITICAL AND SUPERCRITICAL REGIMES
NUMERICAL INVESTIGATION OF THE FLOW OVER A GOLF BALL IN THE SUBCRITICAL AND SUPERCRITICAL REGIMES Clinton Smith 1, Nikolaos Beratlis 2, Elias Balaras 2, Kyle Squires 1, and Masaya Tsunoda 3 ABSTRACT Direct
More informationComputational Fluid Dynamics Study Of Fluid Flow And Aerodynamic Forces On An Airfoil S.Kandwal 1, Dr. S. Singh 2
Computational Fluid Dynamics Study Of Fluid Flow And Aerodynamic Forces On An Airfoil S.Kandwal 1, Dr. S. Singh 2 1 M. Tech Scholar, 2 Associate Professor Department of Mechanical Engineering, Bipin Tripathi
More informationLift and power requirements of hovering flight in Drosophila virilis
The Journal of Experimental Biology 5, 37 () Printed in Great Britain The ompany of Biologists Limited JEB6 3 Lift and power requirements of hovering flight in Drosophila virilis Mao Sun* and Jian Tang
More informationNumerical Study on Performance of Innovative Wind Turbine Blade for Load Reduction
Numerical Study on Performance of Innovative Wind Turbine Blade for Load Reduction T. Maggio F. Grasso D.P. Coiro This paper has been presented at the EWEA 011, Brussels, Belgium, 14-17 March 011 ECN-M-11-036
More informationA combined application of the integral wall model and the rough wall rescaling-recycling method
AIAA 25-299 A combined application of the integral wall model and the rough wall rescaling-recycling method X.I.A. Yang J. Sadique R. Mittal C. Meneveau Johns Hopkins University, Baltimore, MD, 228, USA
More informationContents. I Introduction 1. Preface. xiii
Contents Preface xiii I Introduction 1 1 Continuous matter 3 1.1 Molecules................................ 4 1.2 The continuum approximation.................... 6 1.3 Newtonian mechanics.........................
More informationWe are IntechOpen, the world s leading publisher of Open Access books Built by scientists, for scientists. International authors and editors
We are IntechOpen, the world s leading publisher of Open Access books Built by scientists, for scientists 3,800 116,000 120M Open access books available International authors and editors Downloads Our
More informationAFRL-VA-WP-TM
AFRL-VA-WP-TM-2007-3080 UNSTEADY LOW-REYNOLDS NUMBER AERODYNAMICS FOR MICRO AIR VEHICLES (MAVs) Dr. Michael V. OL Aeroconfigurations Branch (AFRL/VAAA) Aeronautical Sciences Division Air Vehicles Directorate,
More informationFluid transport and coherent structures of translating and flapping wings
Manuscript submitted to Chaos for special issue on Lagrangian Coherent Structures Fluid transport and coherent structures of translating and flapping wings Jeff D. Eldredge and Kwitae Chong Mechanical
More informationNumerical Investigation of Vortex Induced Vibration of Two Cylinders in Side by Side Arrangement
Numerical Investigation of Vortex Induced Vibration of Two Cylinders in Side by Side Arrangement Sourav Kumar Kar a, 1,, Harshit Mishra a, 2, Rishitosh Ranjan b, 3 Undergraduate Student a, Assitant Proffessor
More informationVortex structures in the wake of a buoyant tethered cylinder at moderate to high reduced velocities
European Journal of Mechanics B/Fluids 23 (2004) 127 135 Vortex structures in the wake of a buoyant tethered cylinder at moderate to high reduced velocities K. Ryan, M.C. Thompson, K. Hourigan Fluids Laboratory
More informationAN ABSTRACT OF THE THESIS OF
AN ABSTRACT OF THE THESIS OF Kevin J. Drost for the degree of Honors Baccalaureate of Science in Mechanical Engineering presented May 21, 2010. Title: Direct Numerical Simulation of a Flat Wing with a
More informationFLUID MECHANICS. Atmosphere, Ocean. Aerodynamics. Energy conversion. Transport of heat/other. Numerous industrial processes
SG2214 Anders Dahlkild Luca Brandt FLUID MECHANICS : SG2214 Course requirements (7.5 cr.) INL 1 (3 cr.) 3 sets of home work problems (for 10 p. on written exam) 1 laboration TEN1 (4.5 cr.) 1 written exam
More informationINFLUENCE OF ACOUSTIC EXCITATION ON AIRFOIL PERFORMANCE AT LOW REYNOLDS NUMBERS
ICAS 2002 CONGRESS INFLUENCE OF ACOUSTIC EXCITATION ON AIRFOIL PERFORMANCE AT LOW REYNOLDS NUMBERS S. Yarusevych*, J.G. Kawall** and P. Sullivan* *Department of Mechanical and Industrial Engineering, University
More informationTHE PERFORMANCE OF A NEW IMMERSED BOUNDARY METHOD ON SIMULATING UNDERWATER LOCOMOTION AND SWIMMING
THE PERFORMANCE OF A NEW IMMERSED BOUNDARY METHOD ON SIMULATING UNDERWATER LOCOMOTION AND SWIMMING Arman Hemmati, Utku Şentürk, Tyler Van Buren, Alexander J. Smits,, Department of Mechanical and Aerospace
More informationDIRECT NUMERICAL SIMULATIONS OF HIGH SPEED FLOW OVER CAVITY. Abstract
3 rd AFOSR International Conference on DNS/LES (TAICDL), August 5-9 th, 2001, Arlington, Texas. DIRECT NUMERICAL SIMULATIONS OF HIGH SPEED FLOW OVER CAVITY A. HAMED, D. BASU, A. MOHAMED AND K. DAS Department
More informationCoupling of the wings and the body dynamics enhances damselfly maneuverability
Coupling of the wings and the body dynamics enhances damselfly maneuverability Samane Zeyghami, Haibo Dong Mechanical and Aerospace Engineering, University of Virginia, Charlottesville, VA, 22904 In flapping
More informationOn the generation of a reverse Von Karman street for the controlled cylinder wake in the laminar regime
On the generation of a reverse Von Karman street for the controlled cylinder wake in the laminar regime Michel Bergmann, Laurent Cordier, Jean-Pierre Brancher To cite this version: Michel Bergmann, Laurent
More informationExperimental characterization of flow field around a square prism with a small triangular prism
Journal of Mechanical Science and Technology 29 (4) (2015) 1649~1656 www.springerlink.com/content/1738-494x OI 10.1007/s12206-015-0336-2 Experimental characterization of flow field around a square prism
More informationK. M. Isaac, P. Shivaram + University of Missouri-Rolla Rolla, MO T. DalBello NASA Glenn Research Center
Low Re, High α Aerodynamics with Controlled Wing Kinematics K. M. Isaac, P. Shivaram + University of Missouri-Rolla Rolla, MO 65409 isaac@umr.edu T. DalBello NASA Glenn Research Center ABSTRACT Numerical
More informationLecture 7 Boundary Layer
SPC 307 Introduction to Aerodynamics Lecture 7 Boundary Layer April 9, 2017 Sep. 18, 2016 1 Character of the steady, viscous flow past a flat plate parallel to the upstream velocity Inertia force = ma
More informationWing Kinematics in a Hovering Dronefly Minimize Power Expenditure
Wing Kinematics in a Hovering Dronefly Minimize Power Expenditure Authors: J. H. Wu, and M. Sun Source: Journal of Insect Science, 14(159) : 1-8 Published By: Entomological Society of America URL: https://doi.org/10.1093/jisesa/ieu021
More informationA fundamental study of the flow past a circular cylinder using Abaqus/CFD
A fundamental study of the flow past a circular cylinder using Abaqus/CFD Masami Sato, and Takaya Kobayashi Mechanical Design & Analysis Corporation Abstract: The latest release of Abaqus version 6.10
More informationLow Reynolds Number Flow Dynamics of a Thin, Flat Airfoil with Elastically Mounted Trailing Edge
Low Reynolds Number Flow Dynamics of a Thin, Flat Airfoil with Elastically Mounted Trailing Edge Sourabh V. Apte and James A. Liburdy School of Mechanical, Industrial and Manufacturing Engineering, Oregon
More informationApplication of 2D URANS in fluid structure interaction problems of rectangular cylinders
Advances in Fluid Mechanics X 85 Application of 2D URANS in fluid structure interaction problems of rectangular cylinders F. Nieto, D. Hargreaves 2, J. Owen 2 & S. Hernández School of Civil Engineering,
More informationMechanics of Flight. Warren F. Phillips. John Wiley & Sons, Inc. Professor Mechanical and Aerospace Engineering Utah State University WILEY
Mechanics of Flight Warren F. Phillips Professor Mechanical and Aerospace Engineering Utah State University WILEY John Wiley & Sons, Inc. CONTENTS Preface Acknowledgments xi xiii 1. Overview of Aerodynamics
More informationAPS Flapping flight from flexible wings : tuning of wing stiffness for flight? Tom Daniel, Stacey Combes,, & Sanjay Sane
APS 2004 Flapping flight from flexible wings : tuning of wing stiffness for flight? Tom Daniel, Stacey Combes,, & Sanjay Sane CNS SENSORY INPUT MOTOR OUTPUT FLIGHT MUSCLES FORCE, STRAIN WING HINGE How
More informationDirect Numerical Simulations of Plunging Airfoils
48th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition 4-7 January 010, Orlando, Florida AIAA 010-78 Direct Numerical Simulations of Plunging Airfoils Yves Allaneau
More informationNumerical Analysis of Unsteady Viscous Flow through a Weis-Fogh-Type Water Turbine
International Conference on Emerging Trends in Computer and Image Processing (ICETCIP'014) Dec. 15-16, 014 Pattaya (Thailand) Numerical Analysis of Unsteady Viscous Flow through a Weis-Fogh-Type Water
More informationDrag Computation (1)
Drag Computation (1) Why drag so concerned Its effects on aircraft performances On the Concorde, one count drag increase ( C D =.0001) requires two passengers, out of the 90 ~ 100 passenger capacity, be
More informationFLUID MECHANICS. ! Atmosphere, Ocean. ! Aerodynamics. ! Energy conversion. ! Transport of heat/other. ! Numerous industrial processes
SG2214 Anders Dahlkild Luca Brandt FLUID MECHANICS : SG2214 Course requirements (7.5 cr.)! INL 1 (3 cr.)! 3 sets of home work problems (for 10 p. on written exam)! 1 laboration! TEN1 (4.5 cr.)! 1 written
More informationAeroelastic Analysis of Engine Nacelle Strake Considering Geometric Nonlinear Behavior
Aeroelastic Analysis of Engine Nacelle Strake Considering Geometric Nonlinear Behavior N. Manoj Abstract The aeroelastic behavior of engine nacelle strake when subjected to unsteady aerodynamic flows is
More informationUnsteady aerodynamics of fluttering and tumbling plates
J. Fluid Mech. (25), vol. 541, pp. 65 9. c 25 Cambridge University Press doi:1.117/s221125594x Printed in the United Kingdom 65 Unsteady aerodynamics of fluttering and tumbling plates By A. ANDERSEN 1,
More informationNear-Hover Dynamics and Attitude Stabilization of an Insect Model
21 American Control Conference Marriott Waterfront, Baltimore, MD, USA June 3-July 2, 21 WeA1.4 Near-Hover Dynamics and Attitude Stabilization of an Insect Model B. Cheng and X. Deng Abstract In this paper,
More informationEnergy harvesting through flow-induced oscillations of a foil
Energy harvesting through flow-induced oscillations of a foil Zhangli Peng and Qiang Zhu Citation: Physics of Fluids (1994-present) 21, 12362 (29); doi: 1.163/1.3275852 View online: http://dx.doi.org/1.163/1.3275852
More informationMany of the smallest flying insects clap their wings together at the end of each upstroke
DRAFT Miller, L. A. and Peskin, C. S. Title: Flexible clap and fling in tiny insect flight. Abstract Many of the smallest flying insects clap their wings together at the end of each upstroke and fling
More informationGiven the water behaves as shown above, which direction will the cylinder rotate?
water stream fixed but free to rotate Given the water behaves as shown above, which direction will the cylinder rotate? ) Clockwise 2) Counter-clockwise 3) Not enough information F y U 0 U F x V=0 V=0
More informationCOMPUTATIONAL STUDY OF SEPARATION CONTROL MECHANISM WITH THE IMAGINARY BODY FORCE ADDED TO THE FLOWS OVER AN AIRFOIL
COMPUTATIONAL STUDY OF SEPARATION CONTROL MECHANISM WITH THE IMAGINARY BODY FORCE ADDED TO THE FLOWS OVER AN AIRFOIL Kengo Asada 1 and Kozo Fujii 2 ABSTRACT The effects of body force distribution on the
More informationNumerical Investigation of Thermal Performance in Cross Flow Around Square Array of Circular Cylinders
Numerical Investigation of Thermal Performance in Cross Flow Around Square Array of Circular Cylinders A. Jugal M. Panchal, B. A M Lakdawala 2 A. M. Tech student, Mechanical Engineering Department, Institute
More informationDEPARTMENT OF AEROSPACE ENGINEERING, IIT MADRAS M.Tech. Curriculum
DEPARTMENT OF AEROSPACE ENGINEERING, IIT MADRAS M.Tech. Curriculum SEMESTER I AS5010 Engg. Aerodyn. & Flt. Mech. 3 0 0 3 AS5020 Elements of Gas Dyn. & Propln. 3 0 0 3 AS5030 Aircraft and Aerospace Structures
More informationSHEAR LAYER REATTACHMENT ON A SQUARE CYLINDER WITH INCIDENCE ANGLE VARIATION
Seventh International Conference on CFD in the Minerals and Process Industries CSIRO, Melbourne, Australia 9- December 9 SHEAR LAYER REATTACHMENT ON A SQUARE CYLINDER WITH INCIDENCE ANGLE VARIATION Priyanka
More informationFLOW SEPARATION. Aerodynamics Bridge-Pier Design Combustion Chambers Human Blood Flow Building Design Etc.
FLOW SEPARATION Aerodynamics Bridge-Pier Design Combustion Chambers Human Blood Flow Building Design Etc. (Form Drag, Pressure Distribution, Forces and Moments, Heat And Mass Transfer, Vortex Shedding)
More information344 JAXA Special Publication JAXA-SP E 2. Prediction by the CFD Approach 2.1 Numerical Procedure The plane shape of the thin delta wing of the r
5th Symposium on Integrating CFD and Experiments in Aerodynamics (Integration 2012) 343 Aerodynamic Characteristics of a Delta Wing with Arc Camber for Mars Exploration Takao Unoguchi,* 1 Shogo Aoyama,*
More informationNumerical Simulation of Unsteady Flow with Vortex Shedding Around Circular Cylinder
Numerical Simulation of Unsteady Flow with Vortex Shedding Around Circular Cylinder Ali Kianifar, Edris Yousefi Rad Abstract In many applications the flow that past bluff bodies have frequency nature (oscillated)
More informationUNIT IV BOUNDARY LAYER AND FLOW THROUGH PIPES Definition of boundary layer Thickness and classification Displacement and momentum thickness Development of laminar and turbulent flows in circular pipes
More informationIntroduction to Aerospace Engineering
4. Basic Fluid (Aero) Dynamics Introduction to Aerospace Engineering Here, we will try and look at a few basic ideas from the complicated field of fluid dynamics. The general area includes studies of incompressible,
More informationFluid Dynamics: Theory, Computation, and Numerical Simulation Second Edition
Fluid Dynamics: Theory, Computation, and Numerical Simulation Second Edition C. Pozrikidis m Springer Contents Preface v 1 Introduction to Kinematics 1 1.1 Fluids and solids 1 1.2 Fluid parcels and flow
More informationStall Suppression of a Low-Reynolds-Number Airfoil with a Dynamic Burst Control Plate
49th AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition 4-7 January 2011, Orlando, Florida AIAA 2011-1180 Stall Suppression of a Low-Reynolds-Number Airfoil with
More informationScienceDirect. Experimental Validation on Lift Increment of a Flapping Rotary Wing with Boring-hole Design
Available online at www.sciencedirect.com ScienceDirect Procedia Engineering 99 (2015 ) 1543 1547 APISAT2014, 2014 Asia-Pacific International Symposium on Aerospace Technology, APISAT2014 Experimental
More information1. Introduction, tensors, kinematics
1. Introduction, tensors, kinematics Content: Introduction to fluids, Cartesian tensors, vector algebra using tensor notation, operators in tensor form, Eulerian and Lagrangian description of scalar and
More information