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Data on shape and location of detached shock waves on cones and spheres / by Heberle, Juergen W.

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Experimental surface pressure data obtained on 65̊ delta wing across Reynolds number and Mach number ranges by Chu, Julio

[Flight and static exhaust flow properties of an F110-GE-129 engine in an F-16XL airplane during acoustic tests] by Holzman, Jon K.

Overview of HATP experimental aerodynamics data for the baseline F/A-18 configuration High-Angle-of-Attack Technology Conference /

Experimental investigation of base pressure on blunt-trailing-edge wings at supersonic velocities / by Chapman, Dean R.

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Cold-air investigation of first state of 4 1/2-stage, fan-drive turbine with average stage-loading factor of 4.66 / by Whitney, Warren J., Moffitt, Thomas P., Behning, Frank P.

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Some effects of density and mach number on the flutter speed of two uniform wings / by Castile, George E.

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A velocity-correction formula for the calculation of transonic Mach number distributions over diamond-shaped airfoils / by Ivey, H. Reese

Numerical determination of indicial lift of a two-dimensional sinking airfoil at subsonic Mach numbers from oscillatory lift coefficients with calculations for Mach number 0.7 / by Mazelsky, Bernard

Density fields around a sphere at Mach numbers 1.30 and 1.62 / by Gooderum, Paul B.

Effects of Mach number up to 0.34 and Reynolds number up to 8,000,000 on the maximum lift coefficient of a wing of NACA 66-series airfoil sections / by Furlong, G. Chester

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Turbulent boundary-layer temperature recovery factors in two-dimensional supersonic flow / by Tucker, Maurice

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Investigation of the flow through a single-stage two-dimensional nozzle in the Langley 11-inch hypersonic tunnel / by McLellan, Charles H.

Experimental investigation of the flow field in a transonic, axial flow compressor, with respect to the development of blockage and loss by Suder, Kenneth L.

Hypersonic pitching-moment shift for stardust reentry capsule forebody / by Wood, William A.

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Present status of information relative to the prediction of shock-induced boundary-layer separation / by Lange, Roy H.

Turbulent boundary-layer and skin-friction measurements in axial flow along cylinders at Mach numbers between 0.5 and 3.6 / by Chapman, Dean R.

Development of a flush airdata sensing system on a sharp-nosed vehicle for flight at Mach 3 to 8

Investigation of Mach number changes obtained by discharging high-pressure pulse through wind tunnel operating supersonically / by Haefeli, Rudolph C.

Aerodynamic characteristics of the NACA 64-010 and 0010-1.10 40/1.051 airfoil sections at Mach numbers from 0.30 to 0.85 and Reynolds numbers from 4,000,000 to 8,000,000 / by Loftin, Laurence K.