Abstract
A technique is described for the measurement of aerodynamic drag in a hypervelocity expansion tube in which the test flow period may be as short as 50 μs. The technique is an application of the stress wave force balance first proposed by Sanderson and Simmons (1991). The experiments were conducted in a test flow of partially dissociated Carbon Dioxide where the flow speed was in excess of 7 kms−1. The validity of the technique is first demonstrated by comparing the forces measured on a range of sharp cones with those expected theoretically. Agreement to within 10% is achieved. Two re-entry type heat shield geometries were then tested with the experimental drag forces being compared with a Modified-Newtonian prediction. In both cases agreement to within 11% was obtained.
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Sanderson SR, Simmons JM (1991) Drag balance for hypervelocity impulse facilities. AIAA Journal 29(12):2185–2191
Neely AJ, Stalker RJ, Paull A (1991) High enthalpy, hypervelocity flows of air and argon in an expansion tube. The Aeronautical Journal, 175–186, June/July
Neely AJ, Morgan RG (1994) The Superorbital Expansion Tube concept, experiment and analysis. The Aeronautical Journal, 97–105, March
Tuttle SL, Mee DJ, Simmons JM (1995) Drag measurements at Mach 5 using a stress wave force balance. Experiments in Fluids 19(5):336–341
Porter LM, Paull A, Mee DJ, Simmons JM (1994) Shock tunnel measurements of hypervelocity blunted cone drag. AIAA 32(12):2476–2477
Paull A, Stalker RJ, Mee DJ (1995) Scramjet thrust measurement in a shock tunnel. The Aeronautical Journal, 161–163, May
Park C (1990) Nonequlibrium Hypersonic aerothermodynamics. John Wiley and Sons, New York
Miller CG (1975) Shock shapes on blunt bodies in hypersonic-hypervelocity helium, air and CO2 flows, and calibration results in Langley 6-inch expansion tube, NASA TN D-7800
Taylor GI, Maccoll JW (1932) The air pressure on a cone moving at high speed. Proc. Royal Society (London) Series A 139:278–297
Davies L (1964) Bow-shock establishment and stagnation-point pressure measurements for a blunt-nosed body at supersonic speeds. NPL Aero Report 1098
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Smith, A.L., Mee, D.J. Drag measurements in a hypervelocity expansion tube. Shock Waves 6, 161–166 (1996). https://doi.org/10.1007/BF02510997
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DOI: https://doi.org/10.1007/BF02510997