Wind-tunnel investigation at a Mach number of 1.53 of an airplane with a triangular wing

Scherrer, Richard., Wimbrow, William R.
naca-rm-a7j05
1948


Models of a tailless pursuit-type supersonic airplane were tested in the Ames 1-by-3-foot supersonic wind tunnel No. 1. The basic configuration and several modifications were tested in pitch and yaw and with deflections of the constant-chord control surfaces. The control effectiveness was found to be independent of angle of attack and was found to vary linearly with control deflection. The variation of drag with lift was small. All of the configurations tested were longitudinally stable, but most were directionally unstable.

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