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- Theoretical wave drags and pressure distributions for axially symmetric open-nose bodies
- Aerodynamic characteristics of a slender cone-cylinder body of revolution at a Mach number of 3.85
- Aerodynamics of slender bodies at Mach number of 3.12 and Reynolds numbers from 2 x 10(exp 6) to 15 x 10(exp 6) : body of revolution with near-parabolic forebody and cylindrical afterbody
- Aerodynamics of slender bodies at Mach number of 3.12 and Reynolds numbers from 2 x 10(exp 6) to 15 x 10(exp 6) II : aerodynamic load distributions of series of five bodies having conical noses and cylindrical afterbodies
- Theoretical pressure distribution and wave drags for conical boattails
- Aerodynamics of slender bodies at Mach number of 3.12 and Reynolds numbers from 2 x 10(exp 6) to 15 x 10(exp 6) III : boundary layer and force measurements on a slender cone-cylinder body of revolution
- Experimental investigation of temperature recovery factors on a 10 degree cone at angle of attack at a Mach number of 3.12
- Aerodynamics of slender bodies at Mach number of 3.12 and Reynolds numbers from 2 x 10(exp 6) to 15 x 10(exp 6) IV : aerodynamic characteristics of series of four bodies having near-parabolic noses and cylindrical afterbodies
- Variation of boundary-layer transition with heat transfer on two bodies of revolution at a Mach number of 3.12
- Heat-transfer measurements on two bodies of revolution at a Mach number of 3.12
- Boundary-layer transition at Mach 3.12 as affected by cooling and nose blunting
- Effects of extreme surface cooling on boundary-layer transition
- Effect of favorable pressure gradients on transition for several bodies of revolution at Mach 3.12