An experimental investigation has been carried out in a wind tunnel to test some of the results of Landahl's second order theory. The slender models consisted of a parabolic spindle, tested at M = 3, and a wing body configuration, suggested by Ferri, and tested at M = 2.7. The theory indicates that shock position and strength at an arbitrary distance can be calculated by means of near field measurements. The results show that this method is an appropriate one for simple bodies and for bodies with complicated geometries as well
The sonic boom flight test program conducted at Jackass Flats, Nevada, during the summer and fall of...
A configuration designed to produce near field signature has been tested at M = 2.71 and the results...
A computer method has been developed to calculate the flow field associated with sonic boom focusing...
Wind tunnel tests were conducted to determine the characteristics of sonic booms. A theoretical exam...
A second-order theory for supersonic flow past slender bodies is presented. Through the introduction...
A 3-D parabolized Navier-Stokes (PNS) code was used to calculate the supersonic overpressures from t...
Wind tunnel investigation of lift-induced sonic boom characteristics of two simple wing models at Ma...
Calculations of shock wave pattern in field surrounding arbitrary aircraft configurations at superso...
Estimated supersonic flow field shock waves and sonic boom effects for cones and axisymmetric bodie
A method is developed for theoretically predicting the loading on pylon-mounted stores in supersonic...
Wind tunnel measurements on effect of slender body shape on sonic boom pressure distribution
Unexpected shocks on wind-tunnel-measured pressure signatures prompted questions about design method...
The Langley unitary plan unitary plan wind tunnel was used to determine the validity of a sonic-boom...
This paper first describes the numerical simulation and shape optimization of the Lockheed SEEB-ALR ...
The Euler code, designated AIRPLANE, which uses an unstructured tetrahedral mesh was used to compute...
The sonic boom flight test program conducted at Jackass Flats, Nevada, during the summer and fall of...
A configuration designed to produce near field signature has been tested at M = 2.71 and the results...
A computer method has been developed to calculate the flow field associated with sonic boom focusing...
Wind tunnel tests were conducted to determine the characteristics of sonic booms. A theoretical exam...
A second-order theory for supersonic flow past slender bodies is presented. Through the introduction...
A 3-D parabolized Navier-Stokes (PNS) code was used to calculate the supersonic overpressures from t...
Wind tunnel investigation of lift-induced sonic boom characteristics of two simple wing models at Ma...
Calculations of shock wave pattern in field surrounding arbitrary aircraft configurations at superso...
Estimated supersonic flow field shock waves and sonic boom effects for cones and axisymmetric bodie
A method is developed for theoretically predicting the loading on pylon-mounted stores in supersonic...
Wind tunnel measurements on effect of slender body shape on sonic boom pressure distribution
Unexpected shocks on wind-tunnel-measured pressure signatures prompted questions about design method...
The Langley unitary plan unitary plan wind tunnel was used to determine the validity of a sonic-boom...
This paper first describes the numerical simulation and shape optimization of the Lockheed SEEB-ALR ...
The Euler code, designated AIRPLANE, which uses an unstructured tetrahedral mesh was used to compute...
The sonic boom flight test program conducted at Jackass Flats, Nevada, during the summer and fall of...
A configuration designed to produce near field signature has been tested at M = 2.71 and the results...
A computer method has been developed to calculate the flow field associated with sonic boom focusing...