June 2014 Atlanta Georgia. Michael S. Holden Timothy Wadhams Matthew MacLean
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1 MEASUREMENTS IN REGIONS OF SHOCK WAVE/TURBULENT BOUNDARY LAYER INTERACTION ON DOUBLE CONE AND HOLLOW CYLINDER/FLARE CONFIGURATIONS FROM MACH 5 TO 8 AT FLIGHT VELOCITIES FOR OPEN AND BLIND CODE EVALUATION/VALIDATION June 2014 Atlanta Georgia Michael S. Holden Timothy Wadhams Matthew MacLean Sponsored by CUBRC Internal Research, NSSEFF grant with University of Minnesota, AFOSR, and NASA
2 Outline of Presentation Program Objectives and Design of Experimental Program Double Cone and Hollow Cylinder/Flare Configuration used in Studies Experimental Facilities and Test Conditions for Blind Validation Studies Measurements in Shock Interaction Regions over Cone/Flare Configuration and Effects of Major Flow Parameters Measurements on the Hollow Cylinder/Flare Configuration and Effects of Major Flow Parameters Summary of Results
3 Program Objectives and Experimental Program Design Obtain Detailed Heat Transfer and Pressure Measurements in Regions of Shock Wave/ Fully Turbulent Boundary Layer Interactions to Evaluate Models of Turbulence Employed in RANS and LES Codes. Conduct Program at Duplicated Mach 5, 6, 7 and 8 Flight Velocities and in Cold Flows on Models the Size of Typical Flight Vehicles. Employ Axisymmetric Models and Flow Conditions to Obtain Well-Defined Interaction Regions and Well Defined Boundary Conditions Upstream and Downstream of the Interactions. Flows which are Tripped to obtain Turbulent Boundary Layer on Two Dimensional Models or on Tunnel Walls are Poorly Defined and do not make Good Evaluation Cases
4 Large Double Cone and Hollow Cylinder/Flare Models Employed in Experimental Studies to Produce Measurements for Blind Validation Test Cases
5 Summary of Performance of LENS II Hypervelocity Ground Test Facilities
6 Velocity/Altitude of LENS Tunnels showing Cold and Velocity Matching Test Points for Blind Validation Studies Large Cone Flare Flight (Velocity) Matching Conditions Large Cone Flare Cold Flow Conditions Large Hollow Cylinder Flare Flight (Velocity) Matching Conditions Large Hollow Cylinder Flare Cold Flow Conditions
7 Cold and Velocity Matching Flight Test Points for Blind Validation Studies on Mach Number/Reynolds Number Plot for LENS Tunnels Large Cone Flare Flight (Velocity) Matching Conditions Large Cone Flare Cold Flow Conditions Large Hollow Cylinder Flare Flight (Velocity) Matching Conditions Large Hollow Cylinder Flare Cold Flow Conditions LENS II LENS I 48 Tunnel
8 Cone Flare and Hollow Cylinder Flare Configurations and Heat Transfer and Pressure Instrumentation Employed in Experimental Program Heat Transfer Pressure
9 Large Cone Flare Time Establishment Example Steady Flow Flow initiated through tunnel at 56 milliseconds. Each Line Represents the Average of 4 milliseconds. Mean data for the test case was taken from 72 to 92 milliseconds. Standard deviation will be provided with dataset.
10 Flight Matching and Cold Flow Freestream Conditions Employed in SWTBLI Studies on Large Cone Flare Configuration
11 Cone/Flare Mach 5 Cold Flow, Re L 120x10 6 Mach 5.1, U 2923, Tw/To 0.63, Re# 120x10 6
12 Cone/Flare Mach 5 Flight Velocity Flow, Re L 35x10 6 Mach 5.0, U 4844, Tw/To 0.24, Re# 35x10 6
13 Cone/Flare Mach 6 Cold Flow, Re L 45x10 6 Mach 6.0, U 3055, Tw/To 0.61, Re# 45x10 6
14 Cone/Flare Mach 6 Warm Flow, Re L 24x10 6 Mach 6.0, U 5177, Tw/To 0.22, Re# 24x10 6
15 Cone/Flare Mach 6 Flight Velocity Flow, Re L 37x10 6 Mach 6.0, U 6077, Tw/To 0.17, Re# 37x10 6
16 Effect of Velocity / T w /T o on Magnitude of Interaction Large Cone Flare Run 33, 3055 ft/sec Run 45, 6076 ft/sec
17 Effect of Mach Number on Magnitude of Interaction Flight Matching Flow Large Cone Flare Run 28, Mach 5 Run 34, Mach 6
18 Cone/Flare Mach 7 Cold Flow, Re L 37x10 6 Mach 7.0, U 3863, Tw/To 0.40, Re# 37x10 6
19 Cone/Flare Mach 7 Flight Velocity Flow, Re L 12x10 6 Mach 7.0, U 7209, Tw/To 0.13, Re# 12x10 6
20 Cone/Flare Mach 8 Cold Flow, Re L 34x10 6 Mach 8.0, U 4206, Tw/To 0.35, Re# 34x10 6
21 Cone/Flare Mach 8 Warm Flow, Re L 12x10 6 Mach 8.0, U 5737, Tw/To 0.25, Re# 12x10 6
22 Cone/Flare Mach 8 Flight Velocity Flow, Re L 11x10 6 Mach 8.0, U 6898, Tw/To 0.14, Re# 11x10 6
23 Effect of Velocity / T w /T o on Magnitude of Interaction Large Cone Flare Run 37, 4205 ft/sec Run 40, 5736 ft/sec Run 41, 7898 ft/sec
24 Large Hollow Cylinder Flare Test Cases for Flight Matching and Cold Flow Freestream Conditions
25 Hollow Cylinder/Flare Mach 5 Flight Velocity Flow, Re L 32x10 6 Mach 5.0, U 4774, Tw/To 0.25, Re# 32x10 6
26 Hollow Cylinder/Flare Mach 5 Flight Velocity Flow, Re L 63x10 6 Mach 5.0, U 4766, Tw/To 0.25, Re# 63x10 6
27 Hollow Cylinder/Flare Mach 6 Flight Velocity Flow, Re L 17x10 6 Mach 6.0, U 5578, Tw/To 0.20, Re# 17x10 6
28 Hollow Cylinder/Flare Mach 6 Flight Velocity Flow, Re L 53x10 6 Mach 6.0, U 5496, Tw/To 0.20, Re# 53x10 6
29 Reynolds Number Effect - Large Hollow Cylinder Flare Run 11, 17x10 6 Run 13, 53x10 6
30 Hollow Cylinder/Flare Mach 7 Flight Velocity Flow, Re L 17x10 6 Mach 7.0, U 6869, Tw/To 0.14, Re# 17x10 6
31 Hollow Cylinder/Flare Mach 8 Flight Velocity Flow, Re L 11x10 6 Mach 8.0, U 7115, Tw/To 0.14, Re# 11x10 6
32 Summary of Results Unique Sets of Detailed Surface Measurements in Regions of Shock Wave Boundary Layer/ Fully Turbulent Boundary Layers have been obtained to Evaluate RANS and LES Prediction Methods at Flight Velocities for Mach numbers from 5 to 8 and in Cold Flows. Axi-symmetric Cone/Flare and Hollow Cylinder/ Flare Models the size of typical flight vehicles were employed to produce welldefined turbulent flows well upstream of the interactions and well-defined boundary conditions for the Computations. Measurements where made for a range of flow parameters over both Configurations to evaluate whether the large effects of Velocity / Tw/To, and Mach number and the small effect of Reynolds number observed in the program could be replicated by the prediction methods.
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