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Aerodynamic design guidelines and computer program for estimation of subsonic wind tunnel performance
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Author and Affiliation:
Eckert, W. T.(NASA Ames Research Center, Moffett Field, CA, United States);
Mort, K. W.(NASA Ames Research Center, Moffett Field, CA, United States);
Jope, J.(NASA Ames Research Center, Moffett Field, CA, United States)
Abstract: General guidelines are given for the design of diffusers, contractions, corners, and the inlets and exits of non-return tunnels. A system of equations, reflecting the current technology, has been compiled and assembled into a computer program (a user's manual for this program is included) for determining the total pressure losses. The formulation presented is applicable to compressible flow through most closed- or open-throat, single-, double-, or non-return wind tunnels. A comparison of estimated performance with that actually achieved by several existing facilities produced generally good agreement.
Publication Date: Oct 01, 1976
Document ID:
19770005050
(Acquired Nov 18, 1995)
Accession Number: 77N11993
Subject Category: AERODYNAMICS
Report/Patent Number: NASA-TN-D-8243, A-5944
Document Type: Technical Report
Publisher Information: Washington, United States
Contract/Grant/Task Num: RTOP 505-06-31
Financial Sponsor: NASA; United States
Organization Source: NASA Ames Research Center; Moffett Field, CA, United States
Army Air Mobility Research and Development Lab.; Moffett Field, CA, United States
Description: 196p; In English
Distribution Limits: Unclassified; Publicly available; Unlimited
Rights: No Copyright
NASA Terms: AERODYNAMIC CONFIGURATIONS; COMPUTER PROGRAMS; SUBSONIC WIND TUNNELS; SYSTEMS ENGINEERING; TECHNOLOGY ASSESSMENT; COMPRESSIBLE FLOW; COMPUTER AIDED DESIGN; PRESSURE DISTRIBUTION; STANDARDS
Miscellaneous Notes: Prepared in cooperation with Army Air Mobility R and D Lab, Moffett Field, Calif.
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