Add to ORKGResults of tests to determine the aerodynamic forces and moments on bodies of revolution at angles of attack from 0 degrees to 25 degrees are presented and compared with theory. Cones and ogives of fineness ratios 3 to 7 and two blunt-nosed body shapes with fineness ratios 3 and 5 were tested at Mach numbers from 2.75 to 5.00. Reynolds numbers were from 0.5 million to 6.4 million, depending on Mach number and body fineness ratio
Values of total drag coefficient were measured for four round-nosed bodies of revolution in free fli...
For a body of revolution with afterbody side strakes, an experimental investigation was conducted in...
Experimental investigation of aerodynamic forces acting on body of revolution (NACA RM-10 missile) w...
Results of tests to determine the aerodynamic forces and moments on bodies of revolution at angles o...
Effect of nose bluntness, fineness ratio, cone angle, and model base on aerodynamic characteristics ...
High angle aerodynamic characteristics produced by nose cone of revolution in wind tunnel at superso...
An experimental investigation of the aerodynamics of a slender cone-cylinder body of revolution was ...
Aerodynamic characteristics of bodies of revolution at Mach numbers from 1.50 to 2.86 and angles of ...
The aerodnamic characteristics for several bodies of revolution have been determined from wind tunne...
An experimental investigation of the aerodynamic characteristics of a slender, square-based body of ...
Experimentally determined local flow properties and drag coefficients for family of blunt bodies at ...
Pressure distributions and force characteristics have been determined for a body of revolution consi...
An experimental investigation to determine the aerodynamic characteristics of a slender body of revo...
Experimental drag measurements at zero angle of attack for various theoretical minimum drag nose sha...
To aid in assessing effects of cross-sectional shape on body aerodynamics, the forces and moments ha...
Values of total drag coefficient were measured for four round-nosed bodies of revolution in free fli...
For a body of revolution with afterbody side strakes, an experimental investigation was conducted in...
Experimental investigation of aerodynamic forces acting on body of revolution (NACA RM-10 missile) w...
Results of tests to determine the aerodynamic forces and moments on bodies of revolution at angles o...
Effect of nose bluntness, fineness ratio, cone angle, and model base on aerodynamic characteristics ...
High angle aerodynamic characteristics produced by nose cone of revolution in wind tunnel at superso...
An experimental investigation of the aerodynamics of a slender cone-cylinder body of revolution was ...
Aerodynamic characteristics of bodies of revolution at Mach numbers from 1.50 to 2.86 and angles of ...
The aerodnamic characteristics for several bodies of revolution have been determined from wind tunne...
An experimental investigation of the aerodynamic characteristics of a slender, square-based body of ...
Experimentally determined local flow properties and drag coefficients for family of blunt bodies at ...
Pressure distributions and force characteristics have been determined for a body of revolution consi...
An experimental investigation to determine the aerodynamic characteristics of a slender body of revo...
Experimental drag measurements at zero angle of attack for various theoretical minimum drag nose sha...
To aid in assessing effects of cross-sectional shape on body aerodynamics, the forces and moments ha...
Values of total drag coefficient were measured for four round-nosed bodies of revolution in free fli...
For a body of revolution with afterbody side strakes, an experimental investigation was conducted in...
Experimental investigation of aerodynamic forces acting on body of revolution (NACA RM-10 missile) w...