From Summary: "The longitudinal and lateral-directional dynamic-response characteristics of a 35 degree swept-wing fighter-type airplane determined from flight measurements are presented and compared with predictions based on theoretical studies and wind-tunnel data. Flights were made at an altitude of 35,000 feet covering the Mach number range of 0.50 to 1.04. A limited amount of lateral-directional data were also obtained at 10,000 feet. The flight consisted essentially of recording transient responses to pilot-applied pulsed motions of each of the three primary control surfaces. These transient data were converted into frequency-response form by means of the Fourier transformation and compared with predicted responses calculated from the basic equations. Experimentally determined transfer functions were used for the evaluation of the stability derivatives that have the greatest effect on the dynamic response of the airplane. The values of these derivatives, in most cases, agreed favorably with predictions over the Mach number range of the test."

Report presenting testing of a wing-fuselage configuration with a wing of 45 degrees sweepback of the 0.25-chord line, aspect ratio of 4, taper ratio of 0.6, and NACA 65A006 airfoil sections in aluminum and steel at a range of Mach numbers and angles of attack to determine effects of wing elasticity. Results regarding the relative effects of bending and torsion, wing-tip twist, aerodynamic characteristics, and some theoretical considerations are provided.

Report presenting an investigation in the supersonic wind tunnel to determine some of the base pressure characteristics of related bodies of revolution at zero angle of attack. The basic body shape was a 10-caliber tangent ogive nose with a cylindrical afterbody, while other shapes tested had either a blunt-nosed profile or a boat-tailed afterbody. Results regarding the variation of pressure over the base, variation of base pressure with Reynolds number, effect of nose and afterbody shape, variation of base pressure with Mach number, and correlation of base pressure data are provided.

Report presenting an investigation of a 1/30-scale model of the Grumman XS2F-1 airplane in the 20-foot free-spinning tunnel to determine the erect spin and recovery characteristics of the model in the design flight condition and with the center of gravity at 30 percent of the mean aerodynamic chord. Results regarding the erect spins, inverted spins, spin-recovery parachutes, influence of power, control forces, landing condition, and recommended recovery technique are provided.

Report presenting a flight investigation to determine the longitudinal stability of a scale model of the Northrop MX-775A missile at low lift coefficients through a range of Mach numbers. Results regarding the trimmed flight and model pitching are provided.

From Summary: "A comparison of optimum profiles determined by the shock-expansion method of this report with corresponding profiles determined by the linearized-theory method of a previous report shows only small differences in shape at Mach numbers up to infinity even though the linearized theory at high supersonic Mach numbers breaks down completely insofar as the drag of the profile is concerned. Curves are presented which show that for thin airfoils the use of a trailing-edge thickness considerably greater than the theoretical optimum can result in an excessive drag penalty at moderate supersonic Mach numbers, though not at hypersonic Mach numbers."