An investigation has been conducted in the Langley 4- by 4-foot supersonic tunnel at Mach numbers 1.40 and 1.59 to determine the effect of aileron profile on the aerodynamic characteristics of a complete model of a supersonic aircraft configuration. The model had a 40 degree sweptback tapered wing with 10-percent-thick circular-arc sections normal to the quarter-chord line. The ailerons were 20-percent chord and were located on the outboard 50 percent of the wing semispans. The various ailerons investigated included the basic circular-arc profile and three flat-sided ailerons having ratios of trailing-edge thickness to hinge-line thickness t of 0, 0.5, and 1.0. Low aileron effectiveness was obtained with the circular-arc and t = 0 profiles. Increasing the trailing-edge thickness (t = 0.5 and 1.0) resulted in increased effectiveness as well as increased hinge moments with only a slight increase in drag.

Report presenting pressure distributions, wake measurements, and tuft patterns for wings with 30 and 45 degrees of sweepback in conjunction with a midwing fuselage at Mach numbers to 0.96. The wings have an NACA 65-210 section, a taper ratio of 2.6:1, and aspect ratios of 7.5 and 5.2. The study indicated that when the Mach number reached high subsonic values at low angles of attack, the locations of peak negative pressure coefficients on the upper surfaces of the sections near the wing-fuselage junctures shifted rearward.

"Flutter tests of sweptback cantilever wing models have been made in a small intermittent two-dimensional supersonic tunnel where the testing technique involved changing the structural parameters so that the models would flutter at the tunnel design Mach number of 1.3. Data for 21 models covering sweep angles from 30 degrees to 60 degrees and with varying parameters are included" (p. 1).

From Summary: "A flight investigation was made of a supersonic twin-ram-jet test vehicle using short-flame-length burners. The test demonstrated a maximum acceleration of 3.6g and a maximum flight Mach number of 3.02. Data were obtained over a Mach number range from about 1.9 to 3.0, an altitude range from 1,800 to 40,900 feet, and a fuel-air-ratio range from 0.012 to 0.065."

Report presenting the use of Theodorsen's propeller theory to calculate the performance of a dual-rotating propeller with nonideal load distributions. Results regarding the propeller characteristics were made for several blade-angle settings and flight Mach numbers.

Report discussing the drag and pressure recovery of a model with a nose inlet with a parabolic arc at zero angle of attack. External drag coefficient and total-pressure recovery at the end of the diffuser were measured at a range of Mach numbers and mass-flow ratios.

Report presenting an investigation to determine the high altitude performance of the J57-P-1 turbojet engine and components conducted at the NACA Lewis altitude wind tunnel. Four conditions were tested: engine operation with both the compressor bleed ports closed, with the large compressor bleed port open, with both compressor bleed ports open, and normal engine operation with the automatic control.

Report presenting the effects of blunting the trailing edge or rounding the leading edge on the lift, drag, and pitching-moment characteristics of a plane tapered wing in combination with a body at a range of Mach numbers. Results regarding the effect of wing nose shape on the aerodynamic characteristics are also provided,.

Report presenting the results of an investigation of a missile model with extensible control surfaces and small-span fins. Normal-force, axial-force, and pitching-moment coefficients based on body cross-sectional area and diameter are given for various control deflections up to a maximum of 30 degrees.

Memorandum summarizing the lift and drag characteristics of a series of five low-aspect-ratio triangular-wing or modified triangular-wing airplane models. The series consists of three triangular wings of aspect ratios 2, 3, and 4 and two modified triangular wings of aspect ratio 2 with taper ratios of 0.20 and 0.33. The experimental lift and drag characteristics of the five models are compared with existing theory.

From Introduction: "The purpose of this report is (1) to describe the performance of each component over a range of altitudes, (2) to show the effect of flight conditions on operating point of each component, and (3) to summarize briefly the effects of changes in component performance with flight condition on the over-all engine performance."

From Summary: "From a theory developed on a quasi-one-dimensional-flow basis, it was found that the stability of the ram jet is dependent upon the instantaneous values of mass flow and total pressure recovery of the supersonic diffuser and immediate neighboring subsonic diffuser. Conditions for stable and unstable flow were presented. The theory developed in the report was in agreement with the experimental data of the reports both of Sterbentz and Evvard and of Ferri and Nucci."

Report presenting an investigation in which the inlet-guide-vane setting of a 10-stage compressor was reduced in order to approximate more closely the design absolute entrance flow angles to the first rotor. In order to determine the effects of these changes, the performance of the inlet stage was obtained simultaneously with the overall compressor performance for both the original and reduced incidence angles. Results regarding the compressor performance, inlet-stage performance, and effect of guide-vane resetting on compressor performance are provided.

Report presenting a flight investigation to determine the effect that inclination of the principal axis of inertia as produced by varying the wing incidence angle has on dynamic lateral stability of the Republic XF-91 airplane. Results indicated that the wing incidence angle had a negligible effect on the period of lateral oscillation.

Report presenting comparative drag and pressure recovery for an NACA submerged inlet and two side-wall modifications. One afterbody and diffuser were used for all tests and testing was conducted over a range of Mach numbers. The two modified inlets were found to be superior to the standard inlet from the standpoint of pressure recovery.

Report presenting an investigation of several wing-body combinations with wings suitable for supersonic interceptor-type aircraft at high Reynolds numbers and low Mach numbers. Nine wing-body combinations were tested with three different wing aspect ratios and three different plan forms. Results regarding the lift, drag, and pitching moment are provided.

Memorandum presenting transition tests made in free-flight on a slender body of revolution at Mach number 3.5, wall to free-stream temperature ratio of unity, and with a noiseless and zero-turbulence air stream. The parameter which was varied was surface roughness. Results regarding tests at a Reynolds number of 12 million and 24 million, bursts of turbulence, surface roughness, effect of angle of attack, and time dependence of the transition point are provided.

"The lateral-directional-stability derivatives of a body in combination with several triangular wings were determined at subsonic and supersonic speeds. The wings used in the investigation were of aspect ratios 2 and 4 and thickness ratios of 3 and 5 percent. One of the wings of aspect ratio 2 was cambered and twisted. The results indicate that at supersonic speeds the effects of plan form on the lateral-directional-stability derivatives for the plane wings were predicted satisfactorily by linearized theory and that the effects of thickness were small" (p. 1).

Report presenting an investigation in the transonic tunnel to determine the effects of varying Reynolds number on the pressure distribution on a transonic body of revolution at angles of attack through the transonic speed range. The effect of change in sting cone angle on the pressure distributions and a comparison of experimental incremental pressures with theory is also provided.

Report discussing an investigation of two 45 degree swept blades in low-speed cascade tunnels at a range of angles of attack and various combinations of inlet-air angle and solidity. The isolated wing method used to design the blade predicted the twist distribution and camber shape necessary to obtain an almost uniform spanwise loading.

Report presenting testing of a configuration with a body of fineness ratio 16.6, an unswept horizontal tail of aspect ratio 2.7, and a highly swept vertical tail, which were aeropulsed continuously in pitch during free flight with and without a sustainer rocket motor operating. Results regarding the pitching response, cross coupling, sustainer motor, angle of attack at zero normal force and tail flip, model aerodynamic center, induced jet effect are provided.

Report presenting an investigation to determine the effects of taper ratio, body indentation, fixed transition, and afterbody shape on the transonic aerodynamic characteristics of a 45 degree sweptback wing-body combination with an aspect ratio of 4. Results were obtained at a variety of Mach numbers, angles of attack, and Reynolds numbers. Drag, lift, and stability characteristics are provided.

Report presenting tests conducted on models with 45 degree sweptback wings with varying degrees of flexibility to determine the effective lift-curve slopes in order to evaluate the usefulness of a general method for predicting effective lift ratio by a comparison of predicted values with test results.

Report presenting an investigation in the transonic tunnel to study the effects of body indentation and afterbody shape on the aerodynamic characteristics of an unswept-wing-body combination. Body indentation for a boattail configuration resulted in a considerable reduction in drag up to the highest lift coefficients tested. Results regarding the lift and pitching-moment characteristics are also provided.