Report presenting flight measurements of the lateral control characteristics of the Douglas D-558-II airplane in abrupt rudder-fixed aileron rolls. Results regarding the aileron rolling effectiveness, time histories, and aileron effectiveness variation with Mach number are provided.

This paper contains a detailed description of a 2,000-horsepower propeller dynamometer used to make wind-tunnel tests of a two-blade NACA 10-(3)(08)-03 propeller for a range of blade angles from 20 degrees to 55 degrees at airspeeds up to 500 miles per hour. The results of these tests and comparisons with results obtained from a theoretical analysis and from previous tests made in other wind tunnels are presented.

Experimental investigation of flow about a slender body of revolution (NACA RM-10 missile) aligned and inclined to a supersonic stream was conducted at Mach numbers from 1.49 to 1.98 at a Reynolds number of approximately 30,000,000. Boundary-layer measurements at zero angle of attack are correlated with subsonic formulations for predicting boundary-layer thickness and profile. Comparison of pressure coefficients predicted by theory with experimental values showed close agreement at zero angle of attack and angle of attack except over the aft leeward side of body. At angle of attack, pitot pressure measurements in plane of model base indicated a pair of symmetrically disposed vortices on leeward side of body.

From Introduction: "This paper presents the results of the investigation of the wing-alone and wing-fuselage configurations employing a wing with the quarter-chord line swept back 45^o, aspect ratio 4, taper ratio 0.3, and an NACA 65A006 airfoil section parallel to the stream."

"The production-model 333-A-23 turbojet-engine compressor with a 17-blade impeller was operated at ambient and 0 F inlet temperatures and at inlet pressures of 14 and 5 inches mercury absolute for equivalent impeller speeds from 6000 to 12,750 rpm. The results of this investigation are compared with those of the 533-A-21 compressor. At the design equivalent speed of 11,750 rpm the maximum pressure ratio was 4.39" (p. 1).

Based on results of longitudinal trim and tumble tests of a 0.057-scale model of the Chance Vought XF7U-1 airplane, the following conclusions regarding the trim and tumble characteristics of the airplane have been drawn: 1. The airplane will not trim at any unusual or uncontrolled angles of attack. 2. The airplane will not tumble with the center of gravity located forward of 24 percent of the mean aerodynamic chord. When the center of gravity is located at 24 percent of the mean aerodynamic chord and slats are extended and elevators are deflected full up, the airplane may tumble if given an external positive pitching moment.

Memorandum presenting a systematic transonic zero-lift drag investigation utilizing a swept-wing configuration with three different ratios of wing to fuselage size utilizing a 6-inch helium gun. The experiments and comparisons with other results indicated that the reduction of pressure drag obtainable from partial indentation is approximately proportional to the amount of indentation employed up to a Mach number of 1.3. Results regarding the basic data, total drag, pressure drag, equivalent bodies, and special projections are provided.

Report presenting testing of a low-acceleration transonic flutter test vehicle to obtain flutter data on two similar sweptback wings which indicated that wing flutter was symmetrical in mode. Results regarding flight and flutter characteristics for the FR-1-B are provided.

Memorandum presenting an investigation of flow deflectors which extend forward of an open-nose inlet for improving positive angle-of-attack performance and auxiliary scoops for use at off-design engine air-flow conditions at low angles of attack to determine their effect on net inlet performance. The results show that a deflector inlet and a basic open-nose inlet have about the same net performance at low angles of attack although the flow steadiness characteristics of the deflector inlet are the less desirable.

Report presenting lift and drag characteristics of the Convair YF-102 airplane for symmetrical wing configuration and for the cambered wing configuration. Data were obtained for a variety of lift coefficients, altitudes, and Mach numbers. Results regarding lift, drag, and some flight-tunnel comparisons are provided.

Report presenting an investigation in the full-scale tunnel to determine the effects of the low-speed aerodynamic characteristics of blowing air over the trailing-edge flap of a large-scale wing-body-tail model. Results regarding half-span flaps and full-span flaps, pitching-moment and longitudinal trim characteristics, drag characteristics, lift-drag ratio, and lateral control are provided.

Memorandum presenting an investigation made in the stability tunnel with a model of a low-speed slowly spinning fin-stabilized rocket to determine the effectiveness of a nose ring spoiler in reducing the unstable Magnus moments on a sting-mounted completely spinning model and, if possible, to find the effect of a nonspinning center section, used in a previous investigation, on the unstable Magnus moment.

Report presenting an investigation of heat transfer and pressure distribution on flared bodies under laminar, transitional, and turbulent boundary-layer conditions at Mach number 6.8. Information about flow characteristics, flare drag, and the relationship between flare drag and flare heating is provided.

Memorandum presenting a flight investigation to determine the effect of a propulsive jet on the zero-lift drag characteristics of two twin-exit boat-tailed bodies at transonic speeds. The two models had ratios of jet area to base area of 0.394 and 0.590 and covered a Mach number range of 0.8 to 1.15. A slight reduction in drag coefficients from power-off values are obtained during power-on flight for both models.