E80. Fluid Measurement The Wind Tunnel Lab. Experimental Engineering.
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1 Fluid Measurement The Wind Tunnel Lab Feb. 13, 2014
2 Outline Wind Tunnel Lab Objectives Why run wind tunnel experiments? How can we use WT data to help predict rocket flight path? WT Safety
3 Wind Tunnel Lab Objectives 1. Demonstrate the safe start-up and shut-down sequence for the wind tunnel. 2. Set and verify the wind speed in the wind tunnel. 3. Compare measured drag forces on standard shapes in a flow field with literature values. 4. Model and Measure the drag and lift forces on the rocket in various orientations in a flow field. 5. Calibrate the Pitot sensor in the rocket nose cone.
4 Flight modeling What key forces dictate the flight trajectory?
5 Aerodynamic Forces 1. Pressure Acts perpendicular to surface 2. Shear stress (friction) Acts tangentially to surface
6 Why causes shear stress at surface? No-slip boundary condition
7 Lift and Drag The sum of pressure and shear stress is the resultant force. It is split into two components: 1. Lift: The component of resultant force that is perpendicular to the incoming net velocity vector (effective flow direction). 2. Drag: The component of resultant force that is parallel to the incoming net velocity vector (effective flow direction). V
8 How are lift and drag modeled? Option 1: Full first-principles model (momentum balance)
9 How are lift and drag really modeled? Option 2: Empirical correlations developed in wind tunnels.
10 The HMC Wind Tunnel
11 Why wind tunnel experiments? Wind velocity has same effect as rocket velocity in stagnant air. Scale model testing. Develop correlations to predict performance under varying conditions.
12
13 Wind Tunnel Variables Independent Variables (controls) Fan RPM Test object (e.g. sphere, cylinder, rocket model) Angle of attack Dependent Variables (measured values) Drag force on test object Lift force on test object Pitot tube digital manometer pressure output
14 What info do we want from WT experiments? Resultant force (can be decomposed into drag and lift forces) as a function of velocity and attack angle for full-size rocket under launch conditions. What independent variables affect the resultant force?
15
16 2 Key Dimensionless Numbers 1. Drag/Lift coefficient 2. Reynolds Number
17 Complication #1: Reference Area Drag, lift coefficients are based on a reference area.
18 Complication #2: C D, C L = f(re) Drag, lift coefficients aren t constant during flight!
19 Complication #3: Angle of Attack
20 Complication #3: Angle of Attack
21 A note from your lab instructions: Note that the LVDTs measure the forces normal and parallel to the wind direction, and the lift and drag forces (on a rocket, not an airfoil) are normal and parallel to the rocket direction.
22 Wind Tunnel Variables Independent Variables (controls) Fan RPM Test object (e.g. sphere, cylinder, rocket model) Angle of attack Dependent Variables (measured values) Drag force on test object Lift force on test object Pitot tube digital manometer pressure output
23 Drag and Lift Measurements Dynamometer + Linear Voltage Displacement Transducers (LVDTs)
24 Wind Tunnel Variables Independent Variables (controls) Fan RPM Test object (e.g. sphere, cylinder, rocket model) Angle of attack Dependent Variables (measured values) Drag force on test object Lift force on test object Pitot tube digital manometer pressure output
25 Pitot-Static Tube
26 Bernoulli Equation: A Special Case of Conservation of Momentum Along a streamline, for:
27 Streamlines Lines tangential to velocity vectors throughout the flow field Fundamentals of Fluid Mechanics, Munson, Young, Okiishi, and Huebsch, 6 th edition.
28 Streamlines around an airfoil Fundamentals of Fluid Mechanics, Munson, Young, Okiishi, and Huebsch, 6 th edition.
29 sdfs
30 Bernoulli Equation: A Special Case of Conservation of Momentum Along a streamline, for: Inviscid flow (negligible viscosity) Steady flow Incompressible (constant density) fluid Reasonable for liquids Can be applied to gases at sufficiently low velocity (Ma < 0.3) For these conditions, the force balance (F = ma) gives:
31 Pitot-Static Tube
32 A manometer on your rocket? Maybe not.... MX053DP differential pressure sensor
33 Safety Follow the Dress Code for E80 Lab Never turn the FAN on without Checking to see that no loose objects are in the test chamber Securing the test chamber cover plate Making sure all test personnel are at a safe distance from the wind tunnel itself (at least 24 in any direction) Making sure the vent is clear Making sure the article under test is securely fastened inside the test chamber Do not run the fan at speeds higher than the posted limit.
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