Results are presented of a flight investigation conducted to survey the flow field generated by airplanes flying a t supersonic speeds. The pressure signatures of an F-100, an F-104, and a B-58 airplane, representing widely varying configurations, a t distances from 120 t o 425 f e e from the generating aircraft and at Mach numbers from 1.2 t o 1.8 are shown. Calculations were made by using Whitham's method and were compared with the experimental results.
Experimental and Calculated Flow Fields Produced by Airplanes Flying at Supersonic Speeds
01.11.1960
Sonstige
Keine Angabe
Englisch
Experimental and calculated flow fields produced by airplanes flying at supersonic speeds
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