Results of tests conducted in Ames low density wind tunnel and surface pressures measured for Mach number of 5.7 and Reynolds number per inch of 20,000; pressure distributions evidenced no appreciable 3-dimensional effects and were predicted qualitatively by method described for calculation in 2-dimensional flow.
Surface pressure distribution at hypersonic speeds for blunt Delta wings at angle of attack
NASA -- Memo
National Aeronautics and Space Administration -- Memorandums ; Memo n 5-12-58A
1959
15 pages
Report
English
© Metadata Copyright Elsevier B. V. All rights reserved.
Aerodynamics of delta wings with flaps at hypersonic speeds
Online Contents | 2002
|Lee-side vortices on delta wings at hypersonic speeds.
AIAA | 1972
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