Investigation of a thin wing of aspect ratio 4 in the Ames 12-foot pressure wind tunnel V : static longitudinal stability and control throughout the subsonic speed range of a semispan model of a supersonic airplane

Ben H. Johnson, Jr., Francis W. Rollins
naca-rm-a9i01
Dec 1949


Wind-tunnel tests have been made of a semispan model of a hypothetical supersonic airplane to determine the static longitudinal-stability and -control characteristics of the airplane throughout the range of subsonic Mach numbers up to 0.95. The semispan model had a long slender fuselage and a wing and horizontal tail of aspect ratio 4 and taper ratio 0.5.

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