Add to ORKGHigh angle aerodynamic characteristics produced by nose cone of revolution in wind tunnel at supersonic spee
Pressure distributions and shock shapes for a series of cylindrical afterbodies having nose fineness...
Stability and control of blunt reentry configurations at angles of attack between 60 and 90 degree
The effects of free-stream unit Reynolds number, angle of attack, and nose shape on the aerothermal ...
Aerodynamic characteristics of bodies of revolution at Mach numbers from 1.50 to 2.86 and angles of ...
For a body of revolution with afterbody side strakes, an experimental investigation was conducted in...
Experimental drag measurements at zero angle of attack for various theoretical minimum drag nose sha...
Effect of nose bluntness, fineness ratio, cone angle, and model base on aerodynamic characteristics ...
Results of tests to determine the aerodynamic forces and moments on bodies of revolution at angles o...
Pressure distributions for blunt body wind tunnel models at supersonic speeds and angles of attack f...
The tabulated results of wind tunnel pressure tests are presented without analysis. The data were ob...
Five forebody models of various shapes were tested in the Ames 6- by 6-Foot Wind Tunnel to determine...
The aerodnamic characteristics for several bodies of revolution have been determined from wind tunne...
Pressure distributions and forces for a series of four bodies of revolution having nose-fineness rat...
SWWRY experimental investigation to determine the aerodynamic load distributi~ns of a series of‘five...
Experimental values of shock shapes (angles of attack of 0 deg and 10 deg) and static aerodynamic co...
Pressure distributions and shock shapes for a series of cylindrical afterbodies having nose fineness...
Stability and control of blunt reentry configurations at angles of attack between 60 and 90 degree
The effects of free-stream unit Reynolds number, angle of attack, and nose shape on the aerothermal ...
Aerodynamic characteristics of bodies of revolution at Mach numbers from 1.50 to 2.86 and angles of ...
For a body of revolution with afterbody side strakes, an experimental investigation was conducted in...
Experimental drag measurements at zero angle of attack for various theoretical minimum drag nose sha...
Effect of nose bluntness, fineness ratio, cone angle, and model base on aerodynamic characteristics ...
Results of tests to determine the aerodynamic forces and moments on bodies of revolution at angles o...
Pressure distributions for blunt body wind tunnel models at supersonic speeds and angles of attack f...
The tabulated results of wind tunnel pressure tests are presented without analysis. The data were ob...
Five forebody models of various shapes were tested in the Ames 6- by 6-Foot Wind Tunnel to determine...
The aerodnamic characteristics for several bodies of revolution have been determined from wind tunne...
Pressure distributions and forces for a series of four bodies of revolution having nose-fineness rat...
SWWRY experimental investigation to determine the aerodynamic load distributi~ns of a series of‘five...
Experimental values of shock shapes (angles of attack of 0 deg and 10 deg) and static aerodynamic co...
Pressure distributions and shock shapes for a series of cylindrical afterbodies having nose fineness...
Stability and control of blunt reentry configurations at angles of attack between 60 and 90 degree
The effects of free-stream unit Reynolds number, angle of attack, and nose shape on the aerothermal ...