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A summary of available knowledge concerning skin friction and heat transfer and its application to the design of high-speed missiles

Average Skin-Friction Coefficients From Boundary-Layer Measurements in Flight on a Parabolic Body of Revolution (NACA RM-10) at Supersonic Speeds and at Large Reynolds Numbers

Flight measurements of drag and base pressure of a fin-stabilized parabolic body of revolution (NACA RM-10) at different Reynolds numbers and at Mach numbers from 0.9 to 3.3

Aerodynamic-heating data obtained from free-flight tests between Mach numbers of 1 and 5

Free-flight measurements of aerodynamic heat transfer to Mach number 3.9 and of drag to Mach number 6.9 of a fin-stabilized cone-cylinder configuration

Measurements of Aerodynamic Heat Transfer and Boundary-Layer Transition on a 10 Degree Cone in Free Flight at Supersonic Mach Numbers Up to 5.9

Measurements of Aerodynamic Heat Transfer and Boundary-Layer Transition on a 15 Degree Cone in Free Flight at Supersonic Mach Numbers Up to 5.2

Free-Flight Aerodynamic-Heating Data to a Mach Number of 15.5 on a Blunted Conical Nose With a Total Angle of 29 Degrees

Heat-transfer measurements in free flight at Mach numbers up to 14.6 on a flat-faced conical nose with a total angle of 29©�

Measurements of Aerodynamic Heat Transfer on a 15 Degree Cone-Cylinder-Flare Configuration in Free Flight at Mach Numbers Up to 4.7


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