The optimum hypersonic wind tunnelThe capabilities of existing hypersonic wind tunnels in the U.S. are assessed to form a basis for recommendations for a new, costly facility which would provide data for modeling the hypervelocity aerodynamics envisioned for the new generation of aerospace vehicles now undergoing early studies. Attention is given to the regimes, both entry and aerodynamic, which the new vehicles will encounter, and the shortcomings of data generated for the Orbiter before flight are discussed. The features of foreign-gas, impulse, aeroballistic range, arc-heated and combustion-heated facilities are examined, noting that in any hypersonic wind tunnel the flow must be preheated to prevent liquefaction upon expansion in the test channel. The limitations of the existing facilities and the identification of the regimes which must be studied lead to a description of the characteristics of an optimum hypersonic wind tunnel, including the operations and productivity, the instrumentation, the nozzle design and the flow quality. Three different design approaches are described, each costing at least $100 million to achieve workability.
Document ID
19860052350
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Trimmer, L. L. (Calspan Corp.; USAF, Arnold Engineering Development Center Arnold Air Force Station, TN, United States)
Cary, A., Jr. (NASA Langley Research Center Hampton, VA, United States)
Voisinet, R. L. P. (U.S. Navy, Naval Surface Weapons Center Silver Spring, MD, United States)