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Pressure distribution over a sharp-nose body of revolution at transonic speeds by the NACA wing-flow method
Report presenting an investigation to obtain the pressure distribution over a sharp-nose body of revolution with a circular-arc profile and fineness ratio 6 at transonic speeds using the NACA wing-flow method. Results regarding the variation of pressure coefficient with Mach number, pressure distributions along the body axis, pressure drag, and effects of interference and horizontal gradient are provided.
Date:
March 5, 1948
Creator:
Danforth, Edward C. B. & Johnston, J. Ford
System:
The UNT Digital Library