The following properties have been determined for a sample of dimethylaminodiborane : (1) maximum fundamental flame velocity for fuel and air at 35 degrees C, 115 +/- 5 centimeters per second ; (2) net (lower) heat of combustion of liquid fuel to gaseous nitrogen, carbon dioxide, and water, and to solid boric oxide, 19,225 +/- 100 Btu per pound ; and (3) spontaneous ignition temperature, 240 degrees +/- 10 degrees F.

Report presenting lift, drag, and static-stability characteristics of a triangular-wing airplane over a range of Mach numbers, angles of attack, and angles of sideslip. The basic test configuration had values of maximum lift-drag ratios that were comparable to those obtained in previous tests of several airplane configurations designed primarily from considerations of flight at high supersonic speeds.

The effects of various afterbody changes on the base pressure of a nacelle-type isentropic plug nozzle installation operating at lower-than-design jet pressure ratios were investigated at a Mach number of 0.9. Although the estimates of the net propulsive force contain some uncertainties, the results indicate that both a plain-ring base shroud and a circular-arc boattail fairing reduced the loss in net propulsive force experienced with a cylindrical nacelle installation of the plug nozzle.

Report presenting a tank investigation to determine the effects of hydro-skis as load-alleviation devices for landing a seaplane in waves. Results regarding the basic model without hydro-ski, effect of longitudinal location of hydro-ski, effect of landing trim, effect of hydro-ski dimensions, effect of landing speed, effect of vertical location of hydro-ski, effect of wave height, effect of angle of incidence, effect of aerodynamic stability, and consideration of hydro-skis as a ditching aid are provided.

"The thermal stability of pentaborane has been determined in the temperature range 329 degrees to 419 degrees Fahrenheit by measuring the increase with time in the formation of nonvolatile residue. A relationship was established between the thermal stability and the temperature. The expression permitted extrapolation to obtain the stability of pentaborane at either high temperatures and short times or at ambient temperatures and long times" (p. 1).

Report presenting an investigation conducted in the 4- by 4-foot supersonic pressure tunnel at Mach number 1.41 and 2.01 to determine the static lateral and directional stability and control characteristics of a scale model of the Republic F-105 airplane. Results regarding the static lateral and directional stability and lateral and directional control are provided.

Report presenting an investigation of the aerodynamic characteristics of two full-scale supersonic propellers with a 6000-horsepower propeller dynamometer. One propeller had symmetrical NACA 16-series airfoil sections and the other was similar except for a blade-section camber and a slight difference in pitch distribution.

Memorandum presenting an investigation to determine the effect of camber on the drag of a body of revolution. The drag of a straight body of revolution was measured and compared with that of a body that differed only in that its center line was cambered in the form of a parabola. The addition of a small amount of camber was found to cause very little increase in the minimum foredrag of the model tested.

From Summary: "Linearized theory is used to estimate the order of magnitude of the beneficial effects that can be obtained by shaping the body of a wing-body configuration to generate lift indirectly at supersonic speeds. The analysis applies to a class of wing-body configurations which is believed to exhibit the essential features of this type of interference; the body is cylindrical upstream of a wing which has supersonic edges and the parts of the body above and below the wing are each semicircular and of different radii. Calculations are presented for a Mach number of the square root of 2 for a particular family of bodies and a sonic-edge delta wing."

Report presenting an investigation of a model of the Convair B-58 airplane weapons system in the transonic tunnel for a range of Mach and Reynolds numbers. Results regarding drag characteristics, lift-curve slope, and longitudinal stability parameter are provided.

Report presenting an investigation of a model of the Convair B-58 airplane weapons system, including under conditions of long-range subsonic cruise and a supersonic dash. Results regarding drag characteristics, lift-curve slope, and longitudinal stability parameter are provided.

"A ditching investigation was made of a l/l2-scale dynamically similar model of the Douglas F4D-1 airplane to study its behavior when ditched. The model was landed in calm water at the Langley tank no. 2 monorail. Various landing attitudes, speeds, and configurations were investigated. The behavior of the model was determined from visual observations, acceleration records, and motion-picture records of the ditchings. Data are presented in tables, sequence photographs, time-history acceleration curves, and attitude curves" (p. 1).

Report presenting data from which the effects of transpiration air flow on average skin-friction coefficients and pressure drag of a conical model were evaluated. The model consisted of a truncated porous nose cone with a solid ogival nose section. Results regarding the pressure distribution, base pressure drag, average skin-friction coefficients, effects of transpiration air, and comparison with theory.

Memorandum presenting an investigation to determine the roll effectiveness of a differentially deflected horizontal tail of a 42 degree swept-wing model. The model was tested through an angle-of-attack range of 0 degrees through the stall in the clean and landing configurations with the horizontal tail in a low position. Results regarding the longitudinal characteristics and lateral characteristics are provided.

Report discussing testing of a cruciform missile with a low-aspect-ratio wing and flap-type controls to determine the stability and control characteristics while rolling. Longitudinal stability and control effectiveness for this particular configuration were examined. The data obtained was compared to results from a similar model that was rolling significantly less.

Report presenting flight testing of a model of a cruciform missile configuration with a low-aspect-ratio wing equipped with flap-type controls in order to determine the stability and control characteristics while rolling at about 5 radians per second. Results indicated that if the ratio of roll rate to natural circular frequency in pitch is not greater than about 0.3, the motion following a step disturbance in pitch essentially remains in a plane in space. Results regarding time histories, normal force due to angle of attack, pitching moment due to angle of attack, damping, and control effectiveness are provided.

Report presenting an investigation in the 4- by 4-foot supersonic pressure tunnel at Mach numbers of 1.41, 1.61, and 2.01 of a model of a 45 degree swept-wing fighter airplane. Results regarding the static stability characteristics and lateral and directional control are provided.

From Summary: "Surveys were made through a turbulent boundary layer on a flat plate by means of a pitot probe, an x-ray densitometer, and hot-wire and cold-wire probes. Results from these surveys were analyzed to determine (a) the reliability of the basic data and hence the methods by which they were obtained, and (b) how well the actual distributions of properties in the boundary layer compare with those commonly assumed in semiempirical and theoretical analyses. All surveys were made at the same longitudinal station on the flat plate. The tests were conducted in a an 8- by 8-inch supersonic nozzle. The free-stream Mach number was 3.03 and the Reynolds number was approximately 210,000 based on boundary-layer thickness."

Memorandum presenting results of three-component force tests of a cylindrical body with an ogival nose equipped with panel-type drag brakes each covering approximately 21 percent of the body circumference and located on opposite sides of the body at the rear end. Results regarding the drag brakes in the horizontal plane, drag brakes in the vertical plane, comparison of drag brakes, and minimum drag are provided.

Report presenting tests on two 60 degree sweptback wings of aspect ratios 2 and 3 to provide information on the influence of leading-edge radius on the static longitudinal stability characteristics of swept wings.

Report presenting flutter data obtained with the use of rocket-propelled vehicles in the transonic and low supersonic speed ranges for three low-aspect-ratio, highly tapered, swept wings. Structural influence coefficients were obtained for each of the three plan forms and calculated mode shapes and frequencies are provided. Time histories for each of the configurations also demonstrate the flutter pattern of each wing.