The results of an analytical investigation of the theoretical air specific impulse performance and adiabatic combustion temperatures of several possible ram-jet fuels over a range of equivalence ratios, inlet-air temperatures, and combustion pressures, is presented herein. The fuels include octane-1, 50-percent-magnesium slurry, boron, pentaborane, diborane, hydrogen, carbon, and aluminum. Thermal effects from high combustion temperatures were found to effect considerably the combustion performance of all the fuels. An increase in combustion pressure was beneficial to air specific impulse at high combustion temperatures. The use of these theoretical data in engine operation and in the evaluation of experimental data is described.

A discussion of pertinent items related to the design of internal-flow systems for reciprocating engine, turbine engine, and pressure-jet installations in helicopters. The following items are emphasized: controllable exit and ram recovery for reciprocating-engine cooling, performance penalties possible in turbine-engine installations, the effects of high subsonic flow velocities on the performance of duct elements, and the effects of centrifugal forces on the flow in a ducted helicopter rotor.

Report presenting the first results of pressure measurements obtained on a fuselage and a 45 degree sweptback wing-fuselage combination at transonic speeds in the slotted test section of the 8-foot high-speed tunnel. The test was part of a systematic investigation of varying amounts of sweepback on wings suitable for transonic flight. Results regarding the wing, fuselage, and fuselage with wing are provided.

Report presenting the pressure distribution over a highly swept wing at supersonic speeds to provide data for a comparison of measured and predicted loadings. The wing for this investigation had 63 degrees of sweepback of the leading edge, an aspect ratio of 3.5, and a taper ratio of 0.25. Over the regions influenced by the wing tip and trailing edge, the effects of viscosity apparently are responsible for the poorer agreement between theory and experiment.

From Summary: "Lateral-stability flight tests were made over the Mach number range from 0.7 to 1.3 of models of three airplane configurations having 45 degree sweptback wings. One model had a high wing; one, a low wing; and one, a high wing with cathedral. The models were otherwise identical. The lateral oscillations of the models resulting from intermittent yawing disturbances were interpreted in terms of full-scale airplane flying qualities and were further analyzed by the time-vector method to obtain values of the lateral stability derivatives."

Report presenting an investigation of the effect of yaw and angle of attack on the total-pressure recovery and mass-flow characteristics of a rectangular supersonic scoop inlet designed to have low external drag at a Mach number of 2.7 and an angle of attack of 0 degrees. Total-pressure recovery and mass-flow data are presented for a Mach number of 2.71 at angles of yaw 0, 2.5, and 5 degrees and angles of attack of 0 and 5 degrees are provided.

Report presenting data for five diffusers tested with and without vortex-generator controls in order to determine the performance improvements attainable through the use of boundary-layer controls. Results regarding inlet conditions, axial inlet flow, and whirling inlet flow are provided.

Report presenting testing of the effectiveness of transpiration cooling of an 8 degree total angle conical body with water removed onto the surface through a porous section near the nose. Results regarding a reference test without cooling, a cooling test with 0.010 pound of water per second, a cooling test with 0.0025 pound of water per second, a hypothesis of the phenomena of liquid transpiration cooling, water consumption are provided.

Report presenting an investigation of the handling qualities of a fighter airplane that is controlled by a pilot supplying signals to a rate type of automatic control system. The handling qualities were investigated in pull-ups, aileron rolls, aerobatics, rough-air flying, and precision tasks.

"An investigation of the nature of the flow field behind a rectangular circular-arc wing has been conducted in the Langley 9-inch supersonic tunnel. Pitot- and static-pressure surveys covering a region of flow behind the wing have been made together with detailed pitot surveys throughout the region of the wake. In addition, the flow direction has been measured using a weathercocking vane measurements. Theoretical calculations of the variation of both downwash and sidewash with angle of attack using Lagerstrom's superposition method have been made" (p. 1).

Report presenting an investigation conducted with several 73-percent semispan inboard spoiler ailerons, projecting 4 percent of the local wing chord from the wing surface, and located at the 70-percent chord line of a 45 degree sweptback wing-fuselage combination. Results regarding the effect of upper-surface spoilers on basic model characteristics, effect of gap on spoiler characteristics, comparison of upper- and lower-surface spoiler characteristics, comparison of upper-surface spoiler with oppositely deflected spoilers, effect of Mach number on spoiler effectiveness, and a comparison of spoiler effectiveness with aileron effectiveness are provided.

Report presenting an investigation of a constant-area, circular 90 degree elbow of mean radius of curvature equal to its diameter with several arrangements of simple, nontwisted, rectangular vortex generators. The inlet flow had a boundary layer of about one-tenth the duct diameter. Results regarding an elbow with no vortex generators and an elbow with vortex generators are provided.

Report presenting wing buffeting data obtained from a flight loads investigation of two jet-propelled swept-wing airplanes to study the effects of Mach number and reduced frequency on the wing buffet loads. Consistent trends were noted between the flight testing and wind-tunnel testing that the results of this particular test were compared with. Results regarding variation with penetration and dynamic pressure, variation with Mach number and reduced frequency, and estimation of wing buffet loads are provided.

A determination of the variation of rolling effectiveness with spanwise aileron extent for full-chord ailerons on a sweptback wing over a range of Mach numbers. The test wings had NACA 65A006 airfoil sections, an aspect ratio of 4.0, 45 degrees sweepback at the quarter-chord line, and a taper ratio of 0.6. Results regarding ailerons and twisted wings are provided.

The performance of NACA 65-series compressor blade sections in cascade has been investigated systematically in a low-speed cascade tunnel.

Report presenting an investigation in the transonic blowdown tunnel to obtain static longitudinal force and moment characteristics of two wings, one with an aspect ratio of 1.73 and 3-percent-thick delta wing and one with an aspect-ratio-1.73 4-percent-thick clipped delta wing mounted on a slender body. Results regarding lift characteristics, drag characteristics, and pitching-moment characteristics are provided.

A Mach number measured in the subsonic diffuser was used experimentally as the inlet control parameter of a bypass control system for an axisymmetric supersonic inlet operated in combination with a J34 turbo-jet engine at Mach numbers from 1.6 to 2.0. The control maintained the inlet in either critical or supercritical operation, and, when set for critical diffuser operation, the control recovered from disturbances that placed the inlet in both subcritical buzz and supercritical operation. A slotted-rake orifice gave a more representative value of subsonic diffuser Mach number than the single total-pressure probe used as a control input.

Report presenting the static longitudinal-, lateral-, and directional-stability and control characteristics of a model of the Douglas X-3 airplane at subsonic and supersonic Mach numbers. The model was equipped with an all-movable horizontal tail, an aileron on the left wing, and a rudder on the vertical-tail surface.