NASA Logo, External Link
Facebook icon, External Link to NASA STI page on Facebook Twitter icon, External Link to NASA STI on Twitter YouTube icon, External Link to NASA STI Channel on YouTube RSS icon, External Link to New NASA STI RSS Feed AddThis share icon
 

Record Details

Record 1 of 11809
The optimum hypersonic wind tunnel
Author and Affiliation:
Trimmer, L. L.(Calspan Corp., USAF, Arnold Engineering Development Center)
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)
Abstract: The 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.
Publication Date: Mar 01, 1986
Document ID:
19860052350
(Acquired Nov 28, 1995)
Accession Number: 86A37088
Subject Category: RESEARCH AND SUPPORT FACILITIES (AIR)
Report/Patent Number: AIAA PAPER 86-0739
Document Type: Preprint
Publisher Information: United States
Financial Sponsor: NASA; United States
Organization Source: Calspan Field Services, Inc.; Arnold AFS, TN, United States
NASA Langley Research Center; Hampton, VA, United States
Naval Surface Weapons Center; Silver Spring, MD, United States
Arnold Engineering Development Center; Arnold AFS, TN, United States
Description: 10p; In English
Distribution Limits: Unclassified; Publicly available; Unlimited
Rights: Copyright
NASA Terms: HYPERSONIC FLOW; HYPERSONIC WIND TUNNELS; ARC HEATING; FLOW CHARACTERISTICS; MACH NUMBER; NOZZLE DESIGN; PRODUCTIVITY; RANGES (FACILITIES); REAL GASES
Imprint And Other Notes: AIAA, Aerodynamic Testing Conference, 14th, West Palm Beach, FL, Mar. 5-7, 1986. 10 p.
Availability Source: Other Sources
› Back to Top
Find Similar Records
NASA Logo, External Link
NASA Official: Gerald Steeman
Site Curator: STI Program
Last Modified: August 18, 2011
Contact Us