Pressure distribution over a sharp-nose body of revolution at transonic speeds by the NACA wing-flow method

Edward C. B. Danforth, J. Ford Johnston
naca-rm-l7k12
Mar 1948


The pressure distribution over a sharp-nose body of revolution having a circular-aro profile and fineness ratio 6 has been obtained at transonic speeds by the NACA wing-flow method. The over-all aerodynamic characteristics of fuselage-like bodies are currently being studied at transonic speeds by the free-fall method and rocket method. It is desirable to supplement these investigations by the measurement of the pressure distribution in order to obtain a more detailed understanding of the flow characteristics.

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