Wind tunnel tests were conducted to determine the characteristics of sonic booms. A theoretical examination of nonlinear effects in near and far flow fields, as well as sonic boom shock strength, is reported. A study of the Mach lines and bicharacteristics in three dimensional flow was pursued. The direction derivatives if the bicharacteristics were calculated in a general three dimensional flow field. A second order theory for supersonic flow past slender bodies was developed. Formulas relating flow deflections to the Whitham F-function were derived, which permitted determination of the sonic boom strength from wind tunnel measurements fairly close to the body
A High-Speed Sonic Boom Workshop was held at NASA Langley Research Center on February 25-27, 1992. T...
An improvement in sonic boom extrapolation techniques has been the desire of aerospace designers for...
AbstractBased on bodies of revolution, several flight and shape parameters are considered for invest...
A second-order theory for supersonic flow past slender bodies is presented. Through the introduction...
An experimental investigation has been carried out in a wind tunnel to test some of the results of L...
The results of sonic boom research studies are presented. The purpose of the studies was as follows:...
Wind tunnel investigation of lift-induced sonic boom characteristics of two simple wing models at Ma...
This paper describes the NASA ARC program in sonic boom prediction methodologies. This activity supp...
An experimental and theoretical study has shown that the applicability of far-field sonic-boom theor...
Mach number and geometry effects on level of sonic boom overpressure and applicability of Whitham th...
The Langley unitary plan unitary plan wind tunnel was used to determine the validity of a sonic-boom...
The sonic boom flight test program conducted at Jackass Flats, Nevada, during the summer and fall of...
Calculations of shock wave pattern in field surrounding arbitrary aircraft configurations at superso...
A 3-D parabolized Navier-Stokes (PNS) code was used to calculate the supersonic overpressures from t...
Wind tunnel investigation of delta-wing-body combination sonic boom at Mach 1.41 and 2.0
A High-Speed Sonic Boom Workshop was held at NASA Langley Research Center on February 25-27, 1992. T...
An improvement in sonic boom extrapolation techniques has been the desire of aerospace designers for...
AbstractBased on bodies of revolution, several flight and shape parameters are considered for invest...
A second-order theory for supersonic flow past slender bodies is presented. Through the introduction...
An experimental investigation has been carried out in a wind tunnel to test some of the results of L...
The results of sonic boom research studies are presented. The purpose of the studies was as follows:...
Wind tunnel investigation of lift-induced sonic boom characteristics of two simple wing models at Ma...
This paper describes the NASA ARC program in sonic boom prediction methodologies. This activity supp...
An experimental and theoretical study has shown that the applicability of far-field sonic-boom theor...
Mach number and geometry effects on level of sonic boom overpressure and applicability of Whitham th...
The Langley unitary plan unitary plan wind tunnel was used to determine the validity of a sonic-boom...
The sonic boom flight test program conducted at Jackass Flats, Nevada, during the summer and fall of...
Calculations of shock wave pattern in field surrounding arbitrary aircraft configurations at superso...
A 3-D parabolized Navier-Stokes (PNS) code was used to calculate the supersonic overpressures from t...
Wind tunnel investigation of delta-wing-body combination sonic boom at Mach 1.41 and 2.0
A High-Speed Sonic Boom Workshop was held at NASA Langley Research Center on February 25-27, 1992. T...
An improvement in sonic boom extrapolation techniques has been the desire of aerospace designers for...
AbstractBased on bodies of revolution, several flight and shape parameters are considered for invest...