Increase in operating speeds and altitudes of pilotless aircraft has created need for basic aerodynamic data in hypersonic speed range; flow surveys show that single-expansion nozzle produces reasonably uniform flow with average free stream Mach number of 6.86. See also Engineering Index 1950 p 1302.
Investigation of flow through single-stage two-dimensional nozzle in Langley 11-inch hypersonic tunnel
Nat Advisory Committee Aeronautics -- Tech Note
1950
30 pages
Illus, Diagrs
Article (Journal)
English
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Investigation of two-step nozzle in Langley 11-inch hypersonic tunnel
Engineering Index Backfile | 1950
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