Shock-wave ground-pressure measurements have been made for supersonic bomber airplanes in the Mach number range from 1.24 to 1.52, for altitudes from about 30,000 to 50,000 feet, and for a gross-weight range from about 83,000 to 120,000 pounds. The measured overpressures were generally higher than would be predicted by the theory which accounts only for volume effects. There is thus a suggestion that lift effects on sonic-boom intensity may be significant for this type of airplane for the altitude range of the present tests.
Ground Measurements of the Shock-Wave Noise from Supersonic Bomber Airplanes in the Altitude Range from 30,000 to 50,000 Feet
1961-07-01
Miscellaneous
No indication
English
Engineering Index Backfile | 1941
|High-Altitude Turbulence For Supersonic Airplanes
NTRS | 1989
|SUPERSONIC BOMBER PROPULSION PROBLEMS
SAE Technical Papers | 1956
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