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A pressure-distribution investigation of a supersonic-aircraft fuselage and calibration of the Mach number 1.40 nozzle of the Langley 4- by 4-foot supersonic tunnel

A pressure-distribution investigation of a fineness-ratio-12.2 parabolic body of revolution (NACA RM-10) at M = 1.59 and angles of attack up to 36©�

Preliminary investigation of the drag characteristics of the NACA RM-10 missile at Mach numbers of 1.40 and 1.59 in the Langley 4- by 4-foot tunnel

Investigation of a Half-Conical Scoop Inlet Mounted at Five Alternate Circumferential Locations Around a Circular Fuselage: Pressure-Recovery Results at a Mach Number 2.01

Investigation of Static Pressures and Boundary-Layer Characteristics on the Forward Parts of Nine Fuselages of Various Cross-Sectional Shapes at M Infinity Equal 2.01


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