Report presenting a theoretical investigation of the longitudinal dynamic characteristics of an automatically stabilized supersonic canard missile configuration with a target seeker sensitive to changes in pitch altitude. Variables explored include seeker gain, time delay, and non-linearities, including dead spots in the seeker.

The static lateral- and directional-stability characteristics of a high-speed fighter-type airplane, obtained from wind-tunnel tests of a model, are presented. The model consisted of a thin, unswept wing of aspect ratio 2.3 and taper ratio 0.385, a body, and a horizontal tail mounted in a high position on a vertical tail. Rolling-moment, yawing moment, and cross-wind-force coefficients are presented for a range of sideslip angles of -5 deg. to +5 deg, for Mach numbers of 0.90, 1.45, and 1.90. Data are presented which show the effects on the lateral and directional stability of: (1) component parts of the complete model, (2) modification of the empennage so as to provide different heights of the horizontal tail above the wing plane, (3) angle of attack, and (4) dihedral of the wing.

Report describing equipment that can be used to shock-compress air by helium to 3660 degrees Rankine to generate a 6500-foot-per-second air stream with a flow duration of 40 milliseconds. The influence of yaw on rates of heat transfer to the same circular cylinders was investigated at angles of yaw up to 70 degrees.

Memorandum presenting a flight investigation to determine the thrust and pumping characteristics of a family of aircraft exhaust ejectors. Information was obtained on the variation of these characteristics with changes in engine power, flight Mach number, and ejector spacing ratio, and these results were compared to small-scale tests. Results were also obtained showing how a swinging survey probe can be used as a device for calibrating a tail-pipe pressure probe for the measurement of thrust and air flow.

Report presenting lift, drag, and pitching-moment characteristics for a wing-body combination for a range of Mach numbers. The wing had an aspect ratio of 3.1, a sweepback of the leading edge of 19.1 degrees, a taper ratio of 0.39, and a biconvex profile with a thickness of 3 percent of the chord. Results regarding aerodynamic characteristics and visual-flow studies are provided.

Report presenting the results of an investigation of the dynamic stability and controllability of a proposed supersonic-cruise, vertical-take-off-and-landing airplane configuration with a tilting wing and engines. The configuration tested was found to have satisfactory take-off, landing, and hovering characteristics. Information about transition flight, including stability and control characteristics, is provided.