Free flight test of tailless missile configuration with 45-deg sweptback wing of aspect ratio 4 - stability at transonic speeds. The longitudinal flexible-wing results indicated a gradual transonic trim change a lift-curve slope comparable with that for the same configuration with a wing of aspect ratio 5.5. Results regarding trim characteristics, lift and longitudinal stability, and side-force and lateral stability are provided.

"A formula, based on a semirational analysis, is presented for estimating the torsional stiffness necessary to prevent flutter of a sweptback or unswept uniform wing that attains supersonic speeds. Results of missile flights at speeds up to Mach number 1.4 demonstrate the usefulness of the formula" (p. 1).

Report presenting measurements of the buffet boundary and peak normal-force coefficients for the Douglas D-558-II airplane up to a Mach number of 0.90. Results regarding airplane lift curves and a comparison between the maximum normal-force coefficients and buffet boundaries for this particular aircraft and the Bell X-1 airplane are also provided.

Report presenting an investigation conducted at low speed of an air-induction system with twin scoop-type inlets on the sides of the fuselage of a model of an airplane designed for flight at supersonic Mach numbers. The leading edge of the lip of the scoop was rounded and there were provisions for control of the boundary layer ahead of the inlet. Results regarding the characteristics of the lips investigated, characteristics of the main duct with lip E, characteristics of the boundary layer control duct, and pressure coefficient distributions and boundary-layer characteristics are provided.

Memorandum presenting an investigation conducted in a modified turbojet engine to determine the cooling effectiveness of an air-cooled turbine-rotor blade employing a corrugated metal sheet brazed to the inner surface of the blade shell to increase the internal heat-transfer area. The corrugated fin blade had a lower integrated average wall temperature at the section investigated than the more promising shell-supported blade types previously investigated. Results regarding the temperature distribution investigation and pressure loss investigation are provided.

Memorandum presenting a study of the effect of free methyl radicals on the slow oxidation of both ethane and propane by means of a photochemical decomposition reaction in a static system. The introduction of methyl radicals into a mixture of propane and oxygen or ethane and oxygen substantially lowered the initiation temperature of the combustion of the hydrocarbon.

Report presenting an investigation in the high-speed tunnel to determine the hinge-moment and control-effectiveness characteristics of a tapered, 35 degree sweptback, semispan wing equipped with an outboard 43-percent-span flap. Results regarding the lift, rolling-moment, and pitching-moment characteristics are provided.

Report presenting an investigation in the high-speed tunnel to determine the static longitudinal and static lateral stability characteristics of a wing-fuselage combination with a triangular wing with an aspect ratio of 2.31 and an NACA 65A003 airfoil section. The tests occurred over a range of Mach numbers from 0.40 and 0.95 and separate testing was also conducted with small notches added to the leading edge of the wings.

Memorandum presenting an investigation of a semispan-wing-fuselage model with an 80 degree swept pointed wing with either an unbalanced constant-chord control or an overhang-balanced swept hinge-line control in the 9- by 12-inch blowdown tunnel. Control hinge moments and effectiveness characteristics were obtained over an angle-of-attack range of plus or minus 16 degrees at control deflections up to 25 degrees. Results regarding control effectiveness, control hinge moments, control drag, and evaluation of control characteristics are provided.

Memorandum presenting a flight test of a long-range missile configuration with a 45 degree sweptback wing of aspect ratio 4 conducted at a range of Mach and Reynolds numbers. The longitudinal flexible-wing results indicated a gradual transonic trim change and a lift-curve slope comparable with that for the same configuration with a wing of aspect ratio 5.5.

From Summary: "An investigation was made to determine the effects of changes in the amount and distribution of forebody and afterbody dead rise on the hydrodynamic resistance and spray characteristics of a 1/11-size model of the Bureau of Aeronautics design No. 22ADR class VPB airplane. The variations in dead rise within the range investigated had no significant effects on resistance or trim, free to trim, or on resistance or trimming moment, fixed in trim. The coordinates of the peaks of the bow-spray blisters, with reference to the model, were measured at low speeds, and it was found that the model with the low dead rise at the bow had the lowest blisters."

"An investigation of the characteristics of a wing with an aspect ratio of 9.0 and an NACA 65-210 airfoil section has been made at Mach number up to 0.925. The wing tested has a taper ratio of 2.5:1.0, no twist, dihedral, or sweepback, and 20-percent - chord 37.5-percent-semispan plain ailerons. The results showed that serious changes in the normal-force characteristics occurred when the Mach number was increased above 0.74 at angles of attack between 4 deg. and 10 deg. and above 0.80 at 0 deg. angle of attack" (p. 1).

"The results of tests made to determine the aerodynamic characteristics of a solid brake, a slotted brake, and a dive-recovery flap mounted on a high aspect ratio wing at high Mach numbers are presented. The data were obtained in the Langley 8-foot high-speed tunnel for corrected Mach numbers up to 0.940. The results have been analyzed with regard to the suitability of dive-control devices for a proposed high-speed airplane in limiting the airplane terminal Mach number by the use of dive brakes and in achieving favorable dive-recovery characteristics by the use of a dive-recovery flap" (p. 1).