Add to ORKGA large amount of fundamental aerodynamic missile data, which were stored for a number of years at the Applied Physics Laboratory, are reported. Data that supplements the M = 2.0 flow field data are provided. The Mach number effect by means of pressure fields only, at M = 1.5 and 2.0, and at angles of attack up to 23 deg at a mid-body station where a wing might be located is described
Wind tunnel study of flow field beneath X-15 aircraft fuselage at supersonic to hypersonic speed
Wall static, local stream static, and pitot pressure surveys were made on the windward side of a hyp...
Most of the aerodynamic configurations considered are suitable for highly maneuverable air-to-air or...
Available flow field data which can be used in validating theoretical procedures for computing flow ...
The parts of an aerodynamics research project of the Bumblebee Program, called Generalized Missile s...
Individual wing panel aerodynamic characteristics are provided for rectangular wings with aspect rat...
This report provides a brief description of those parts of an aerodynamics research project of the B...
The Bumblebee program, was designed to provide a supersonic guided missile. The aerodynamics program...
The tabulated results of wind tunnel pressure tests are presented without analysis. The data were ob...
Pitot pressure and flow angle distributions in the windward flow field of the NASA 040A space shuttl...
The results of pressure distribution tests are presented without analysis. The test Reynolds number ...
Pressure coefficients were obtained in the Langley Unitary Plan wind tunnel for a wingless missile w...
The results of pressure distribution tests conducted in the Langley Unitary Plan wind tunnel are pre...
The tabulated results of surface pressure tests conducted on the wing and fuselage of an airplane mo...
This summary document was prepared in order to facilitate dissemination of a large amount of missile...
Wind tunnel study of flow field beneath X-15 aircraft fuselage at supersonic to hypersonic speed
Wall static, local stream static, and pitot pressure surveys were made on the windward side of a hyp...
Most of the aerodynamic configurations considered are suitable for highly maneuverable air-to-air or...
Available flow field data which can be used in validating theoretical procedures for computing flow ...
The parts of an aerodynamics research project of the Bumblebee Program, called Generalized Missile s...
Individual wing panel aerodynamic characteristics are provided for rectangular wings with aspect rat...
This report provides a brief description of those parts of an aerodynamics research project of the B...
The Bumblebee program, was designed to provide a supersonic guided missile. The aerodynamics program...
The tabulated results of wind tunnel pressure tests are presented without analysis. The data were ob...
Pitot pressure and flow angle distributions in the windward flow field of the NASA 040A space shuttl...
The results of pressure distribution tests are presented without analysis. The test Reynolds number ...
Pressure coefficients were obtained in the Langley Unitary Plan wind tunnel for a wingless missile w...
The results of pressure distribution tests conducted in the Langley Unitary Plan wind tunnel are pre...
The tabulated results of surface pressure tests conducted on the wing and fuselage of an airplane mo...
This summary document was prepared in order to facilitate dissemination of a large amount of missile...
Wind tunnel study of flow field beneath X-15 aircraft fuselage at supersonic to hypersonic speed
Wall static, local stream static, and pitot pressure surveys were made on the windward side of a hyp...
Most of the aerodynamic configurations considered are suitable for highly maneuverable air-to-air or...