Report presenting a flight test of pentaborane fuel in an air-launched ramjet engine with a design free-stream Mach number of 1.8. The ramjet used in the investigation had a revised spray bar-flameholder configuration. Results regarding propulsive thrust and propulsive-thrust specific fuel consumption are provided.

Report presenting testing of gaseous hydrogen fuel burned in a connected-pipe combustor with a cross section equal to 35 degrees sector of a 28-inch diameter. Eleven shrouded fuel-injector configurations were used to obtain combustion data at specified high-altitude ramjet combustor conditions. Results regarding shroud air blockage, mixing tabs, higher equivalence-ratio burning, injector size, flameholder durability, burner length, combustion efficiency, and temperature profile are provided.

Flight investigation of pentaborane fuel in 9.75- inch-diameter ramjet engine with downstream fuel injection.

Report presenting measurements downwash angles behind a model of a high-aspect-ratio wing at points near the probable tail location at Mach numbers up to 0.89 in the high-speed tunnel. The model has an NACA 65-210 section, an aspect ratio of 9.0, a taper ratio of 2.5:1, no twist, dihedral, or sweepback. Results regarding experimental data and comparison of experimental and calculated results are provided.

Memorandum presenting the results of a wind-tunnel investigation of the low-speed characteristics of horizontal tails of aspect ratio 3 with unswept and swept-back plan forms. Two models were tested which had identical areas, aspect ratio, taper ratio, and airfoil section, differing only in the angle of sweepback and elevator area ratios. The major effect of sweepback was to increase the rate of change of hinge-moment coefficient with angle of attack, to reduce the rate of change with elevator deflection, and to reduce the elevator effectiveness.

Report presenting tests to determine the effect of sweepback angle and aspect ratio on the drag at supersonic speeds of wings of NACA 65-009 airfoil section. The current report is part of a bigger investigation and includes results for aspect ratios of 3.8 and 5.0. Results regarding the drag coefficient and general effect of aspect ratio are provided.

Memorandum presenting measurements of some of the high-speed characteristics of the D-558-1 airplane up to Mach number 0.89. The results of the tests showed that the stabilizer incidence drastically affected the longitudinal trim characteristics above a Mach number of 0.80.

Report presenting an experimental investigation to determine the vibration phenomena that occur in turbine blades of a typical jet-propulsion engine during service operation; high-temperature strain gages were used to measure the turbine-blade vibrations. Results regarding modes of vibration, centrifugal stresses, and vibration of turbine blades during operation are provided.

Report presenting the results of an experimental investigation of the dynamic stability and control of a simple ducted-fan model in hovering flight in order to provide basic information on the stability and control of jet vertically rising airplanes in hovering flight. The investigation primarily consisted of flight tests with the model hovering at altitude and near the ground.

The present investigation was made at a free-stream Mach number of 1.59 to compare the afterbody drags to a series of conical boattailed models at zero angle of attack. Afterbody drags were obtained for both the power-off and the power-on conditions. Power-on drags were obtained as a function of afterbody fineness ratio, jet pressure ratio and divergence, and jet Mach number.

An analysis of the cooling problem has been to show by what means the cooling of an air-cooled aircraft engine may be improved. Each means of improving cooling is analyzed on the basis of effectiveness in cooling with respect to power for cooling. The altitude problem is analyzed for both supercharged and unsupercharged engines. The case of ground cooling is also discussed. The heat-transfer process from the hot gases to the cylinder wall is discussed on the basis of the fundamentals of heat transfer and thermodynamics. Adiabatic air-temperature rise at a stagnation point in compressible flow is shown to depend only on the velocity of flow.

Report presenting testing of a transonic compressor rotor with double-circular-arc blade sections and inlet guide vanes turning counter to the direction of rotor whirl to determine the effect of blade-row interaction on the performance of a transonic rotor. Results regarding overall performance, guide-vane performance, rotor-inlet conditions, rotor-outlet conditions, consideration of radial equilibrium, blade-element performance, and axial asymmetry in rotor-outlet flow are provided.

Memorandum presenting an investigation of the static longitudinal stability characteristics of two wings of different construction and slightly different flexibilities in the 16-foot transonic tunnel. The wings had the same external dimensions but one had a steel construction and the other was made of plastic reinforced by a steel core.

Report presenting flight tests on an FJ-3 airplane to determine the flight characteristics of a carrier-type airplane with area-suction and blowing boundary-layer control on the trailing-edge flaps. Measurements were made of lift, drag, and bleed-air requirements for the different types of boundary-layer control systems. Results regarding lift, drag, flow requirements, performance, pilots' opinions, and approach-speed criteria are provided.

Memorandum presenting a general wave equation derived governing the propagation of sound in a stratified moving medium, the velocity of which varies only along one coordinate. A simplified equation is adopted which is satisfactory for the present application.

Tests of a PB2Y-3 flying boat were made at the U.S. Naval Air Station, Patuxent River, Md., to determine its hydrodynamic trim limits of stability. Corresponding tests were also made of a 1/8-size powered dynamic model of the same flying boat in Langley tank no. 1. During the tank tests, the full-size testing procedure was reproduced as closely as possible in order to obtain data for a direct correlation of the results. As a nominal gross load of 66,000 pounds, the lower trim limits of the full-size and model were in good agreement above a speed of 80 feet per second. As the speed decreased below 80 feet per second, the difference between the model trim limits and full-scale trim limits gradually became larger. The upper trim limit of the model with flaps deflected 0 deg was higher than that of the full-size, but the difference was small over the speed range compared. At flap deflections greater than 0 deg, it was not possible to trim either the model of the airplane to the upper limit with the center of gravity at 28 percent of the mean aerodynamic chord. The decrease in the lower trim limits with increase in flap …

Report presenting the results of deflection tests on the wing of a full-scale, swept-wing jet bomber in the form of structural influence coefficients relating the deflection of a system of points on the wing and concentrated loads applied on the wing spars. The procedures for determining the coefficients are included.

Memorandum presenting a rocket-propelled model flown to determine the effects of four wing-mounted bomb-type external stores on the trim, buffet, and drag characteristics of a wing-fuselage configuration with a 45 degree sweptback wing. The model is compared with data from a similar model without stores. Results regarding trim, buffet, lift and stability, and drag are provided.

"A linear stability analysis and flight-test investigation has been performed on a rolleron-type roll-rate stabilization system for a canard-type missile configuration through a Mach number range from 0.9 to 2.3. This type damper provides roll damping by the action of gyro-actuated uncoupled wing-tip ailerons. A dynamic roll instability predicted by the analysis was confirmed by flight testing and was subsequently eliminated by the introduction of control-surface damping about the rolleron hinge line" (p. 1).