Report presenting the results of flight testing to determine the zero-lift drag of an NACA 65-009 airfoil at a specified aspect ratio. The results are compared to previous testing of unswept and swept-back arrangements. The swept-forward and swept-back airfoils were found to produce lower values of zero-drag lift than the unswept airfoil.

"A solution is presented for the coupled modes and frequencies of swept wings mounted on a fuselage. The energy method is used in conjunction with power series to obtain the characteristic equations for both symmetrical and asymmetrical vibration. A numerical example which is susceptible to exact solution is presented, and the results for the exact solution and the solution presented in this paper show excellent agreement" (p. 1).

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 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.

"This report presents preliminary data obtained in the Langley supersonic sphere. The supersonic sphere is essentially a whirling mechanism enclosed in a steel shell which can be filled with either air or Freon gas. The test models for two-dimensional study are of propeller form having the same plan form and diameter but varying only in the airfoil shape and thickness ratio. Torque coefficients for the 16-006, 65-110, and the 15 percent thick ellipse models are presented, as well as pressure distributions on a circular-arc supersonic airfoil section having a maximum thickness of 10 percent chord at the 1/3-chord position" (p. 1).

The variation of the intensity of buffeting experienced throughout the operational region of the semitailless Northrop X-4 airplane and the values of maximum and peak normal-force coefficients in the Mach number range from 0.42 to 0.92 have been determined. The results are compared with data obtained with the swept-wing Douglas D-558-II airplane.

Report presenting a flight investigation of the variation of the intensity of buffeting with lift and Mach number using a Douglas D-558-II research airplane over a range of Mach numbers and altitudes. Buffeting was encountered during flight at all Mach numbers attained and during level flight at Mach numbers above 0.9. Results regarding the relationship between lift, angle of attack, and buffeting, buffet frequencies, and intensity of buffeting are provided.

Report presenting the X-3 airplane, which has a straight 4.5-percent-thick wing of modified hexagonal section, which has been flown to maximum wing normal-force coefficients in the Mach number range from 0.7 to 1.1 at an average altitude of 30,000 feet. Measurements were made of airplane and wing-panel maximum normal-force coefficients and of some buffeting characteristics.

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.

"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).

Supersonic performance of variable two-dimensional inlets designed for engine-inlet matching.

Report presenting an investigation of the effects of rocket-armament-exhaust-gas ingestion on the performance of a supersonic-inlet J34-turbojet-engine installation at Mach 2. Rockets were fired from two different spike positions and with the engine at high or low speed. Results regarding engine air flow, temperature, and flame-out are provided.

Report presenting a program to investigate the aerodynamic characteristics of a family of delta wings with a blunt double-wedge section in the hypersonic tunnel at Mach number 6.9. The wings varied at semiapex angle and were tested over a range of angles of attack and Reynolds numbers. Results regarding lift and drag characteristics, center of pressure and moment coefficient, Schlieren photographs, and surface film flow studies are presented.

From Summary: "Hydrodynamic characteristics have been determined for a 1/13.33-scale jet-powered dynamic model of the Martin XP6M-1 flying boat with the forebody modified so as to increase the depth of step and the angle between the forebody and afterbody keels. Longitudinal stability during takeoff and landing in smooth water and resistance of the complete model in smooth water and in waves are presented."

Report presenting wind-tunnel studies of the wake behind eight types of canard control surfaces of equal span mounted on a missile body at Mach number 1.93. The effect of simulated external rocket boosters on the pressure field was also determined for three control-surface plan forms. The investigation also included the effect of end plates attached to the tips of one of the controls surfaces.

A determination of the manner in which the lift and pitching-moment characteristics of a 45 degree sweptback wing are influenced by high-lift and stall-control devices by using detailed pressure-distribution measurements. The results indicate that the instability of the basic wing was due to flow separation which originated over the outer 4 percent of the wing semispan. The stability of the wing was improved through the use of upper-surface fences or leading-edge flaps.

"A flight test of the Aero jet Engineering Corporation's 7KS-6000 T-27 Jato rocket motor was conducted at the Langley Pilotless Aircraft Research Station at Wallops Island, Va, to determine the flight performance characteristics of the motor. The flight test imposed an absolute longitudinal acceleration of 9.8 g upon the rocket motor at 2.8 seconds after launching. The total impulse developed by the motor was 43,400 pound-seconds, and the thrusting time was 7.58 seconds" (p. 1).

Report presenting summaries of full-scale engine tests of pentaborane, pentaborane-JP-4 fuel mixtures, and trimethylborate-methyl-alcohol-azeotrope fuels. Tests were conducted at an altitude of 50,000 feet and Mach number of 0.8. Results regarding the fuel effects on overall performance, effects on component performance, effect of turbine-outlet temperature on engine performance, and miscellaneous observations are provided.

This report summarizes the full-scale engine tests of pentaborane, pentaborane - JP-4 fuel mixtures, and trimethylborate azeotrope fuel. The tests were conducted in a full-scale turbojet engine at a simulated altitude of 50,000 feet and Mach number of 0.08. Engine speeds were 90 to 100 percent of rated speed. Pentaborane reduced the the specific fuel consumption to two-thirds that of JP-4 fuel. However, because boron oxide collected in the engine, the performance deteriorated with continued operation of pentaborane in each of the short-duration tests reported.

Report presenting an analytical investigation to determine primarily the reduction in cooling-air requirement and the increase in effective gas temperature for the same quantity of cooling air resulting from the use of an insert in the cooling-air passage of a hollow air-cooled turbine blade.

Memorandum presenting an investigation of the effect of a 60 degree sweptback horizontal tail at two vertical locations on the static longitudinal stability of two 60 degree sweptback wing-body configurations with aspect ratios of 2.67 and 4.00 in the 8-foot transonic pressure tunnel. Tests were made at Mach numbers from 0.80 to 1.18 for angles of attack from -3 degrees to about 15 degrees.

Report presenting a flight investigation using rocket-powered models to determine some of the effects of wing-to-tail distance on the stability and control characteristics of a canard-missile configuration with 60 degree delta wings and control surfaces. Both models were tested over a range of Mach numbers from 0.8 to 2.0, and canard hinge moment and model drag data are presented. Testing indicated that additional fuselage length increases the lift-curve slope slightly and has very little effect on minimum drag.

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.

"A summary has been made of available data on the characteristics of airfoil sections with trailing-edge high-lift devices. Data for plain, split, and slotted flaps are collected and analyzed. The effects of each of the variables involved in the design of the various types of flap are examined and, in cases where sufficient data are given, optimum configurations are deduced" (p. 1).