Memorandum presenting the results of wind-tunnel oscillation tests to measure the rotary derivatives of a research airplane configuration at supersonic speeds. Measurements were made of the damping in yaw, pitch, and roll, the static longitudinal and directional stability derivatives, the effective-dihedral derivative, the rolling moment due to yawing, and the yawing moment due to rolling. The configuration was found to be statistically stable throughout the Mach number range, although its stability was becoming marginal at high angles of attack at Mach number 3.5.

"A supplementary investigation has been conducted in the Langley 20-foot free-spinning tunnel on a l/24-scale model of the Grumman F11F-1 airplane to determine the spin and recovery characteristics with alternate nose configurations, the production version and the elongated APS-67 version, with and without empty and full wing tanks. When spins were obtained with either alternate nose configuration, they were oscillatory and recovery characteristics were considered unsatisfactory on the basis of the fact that very slow recoveries were indicated to be possible. The simultaneous extension of canards near the nose of the model with rudder reversal was effective in rapidly terminating the spin" (p. 1).

Report presenting an investigation to determine the effect of a distributed granular-type roughness on boundary-layer transition at several temperatures. The roughness was not found to introduce any disturbances of significant magnitude to influence transition. Surface cooling did not increase the value of the critical roughness Reynolds number for a distributed granular-type roughness either.

Memorandum presenting a fineness-ratio-2.71 right circular cylinder and a fineness-ratio-4.0 circular cylinder with a rounded nose and a flared afterbody tested in free flight over a range of Mach and Reynolds numbers. Time histories, cross plots of force coefficients, rolling velocity, and longitudinal-force coefficient are presented for both cylinders.

Report presenting testing of a fineness-ratio-2.71 right circular cylinder and a fineness-ratio-4.0 circular cylinder with a rounded nose and flared afterbody over a range of Mach and Reynolds numbers. Time histories, cross plots of force coefficients, rolling velocity, and longitudinal-force coefficient are provided for the two cylinders.

"A summary of the locations, extents, and intensities of turbulent areas encountered during a flight investigation of the jet stream is presented. The data were obtained from NACA VGH time-history records" (p. 1).

Report presenting an experimental investigation of several airplane configurations at Mach 3.0 in a continuous flow tunnel. The configurations had circular fuselage cross sections and a sweptback wing and either two nacelles or two side inlets.

Report presenting a two-dimensional high-speed cascade investigation of thin low-cambered NACA 65-series blade shapes at operating conditions typical of compressor tip sections. Testing occurred with porous walls and solid walls. Results regarding the variation of turning angle with Mach number, variation of turning angle with angle of attack, momentum loss, and schileren photographs are provided.

Report discussing testing on a high-thrust turbojet engine capable of operation at high flight speeds. The report presents the overall performance and blade-element performance of the engine at a specified hub-tip radius ratio and specific weight flow of air.

Report presenting an investigation in the supersonic pressure tunnel to determine the effects of various vertical positions of a wing and horizontal tail on the static longitudinal aerodynamic characteristics of a trapezoidal wing model. Results regarding effect of wing vertical position and tail-on characteristics are provided.

"Static longitudinal and lateral stability characteristics of a swept-wing fighter-bomber airplane model with a top inlet have been determined experimentally. In addition, vertical-tail effectiveness, spoiler effectiveness, effects of several store configurations, and effects of mass flow were investigated. Tests were made at Mach numbers of 1.6, 1.8, 2.0, 2.2, and 2.35 and Reynolds numbers, based upon mean aerodynamic chord, of between 2.0x10(exp 6) and 2.5x10(exp 6)" (p. 1).

Report discussing heat data obtained on concave and convex hemispherical nose shapes and hemispherical depressions on a blunted 30-degree nose cone at a variety of Mach numbers. Both hot-jet tests and flight tests were carried out.

Memorandum presenting experimental force and moment characteristics, including lift-drag ratios, which have been measured and briefly studied for two families of wing-body combinations. One family consisted of essentially arrow wings with half conical bodies. The other consisted of a fineness-ratio-12 body of revolution alone and with flat-plate triangular wings of aspect ratios ranging from 0.375 to 1.8.

Report presenting an investigation in a chemical jet at a stagnation temperature of 4,000 degrees Fahrenheit at a Mach number of 2.8 to determine the feasibility of cooling models by the ejection of a solid coolant at the stagnation point. A series of conical models were tested with glass, Lucite, nylon, Teflon, and Texolite rods as coolants. Results regarding the cooling properties of each of the materials are provided, and all materials performed adequately with the exception of Teflon.

Some of the significant interference fields that may affect stability of aircraft at supersonic speeds are briefly summarized. Illustrations and calculations are presented to indicate the importance of interference fields created by wings, bodies, wing-body combinations, jets, and nacelles.

Report presenting flight tests with an airplane equipped to vary the longitudinal-control-system dynamic characteristics over a wide range. Control is obtained through a stabilizer force-command position-feedback longitudinal-control system. Results at a Mach number of 0.80 at 35,000 feet altitude, Mach number of 0.35 at 5,000 feet altitude, and normal-acceleration response are provided.

Memorandum presenting an investigation made with an electrical heat-flow analog to determine the effect of internal modifications to a wing leading edge on the surface-temperature rise and temperature distribution for conditions of transient aerodynamic heating at high supersonic speeds. Results regarding the leading-edge temperature rise, influence of conduction on leading-edge temperature for skins of uniform thickness, and surface-temperature distribution are provided.

Memorandum presenting a technique for predicting the influence of body vortices and the wing shock-expansion field on the pitch-up characteristics of supersonic airplanes to supplement the calculative methods for wing vortices which are well known. The method is applied to the prediction of the pitch-up characteristics of four airplanes with high tails, of which one serves as a calculative example.

Memorandum describing a calculative technique for predicting the influence of body vortices and the wing shock-expansion field on the pitch-up characteristics of supersonic airplanes to supplement calculative methods for wing vortices which are well known. The method is applied to the prediction of the pitch-up characteristics of four airplanes with high tails, of which one serves as a calculative example.

Report presenting an investigation of the jet effects on several afterbody shapes of a single-engine fighter-airplane model in the 16-foot transonic tunnel at a range of Mach numbers and angles of attack. The afterbody-geometry variables were boattail angle, afterbody length, and base area. Results regarding evaluation of support interference, afterbody-pressure-distribution characteristics, and drag characteristics are provided.

Report presenting an investigation of a rocket-powered model to study the heat transfer to wing leading edges in the vicinity of their juncture with a cylindrical body. Information about heat-transfer measurements, average heat transfer on cylindrical portions of leading edges, and local heat transfer is provided.

Report presenting the results of an investigation of the static lateral-directional stability characteristics of a canard airplane configuration without analysis for a range of Mach numbers. Data are presented for various combinations of the canard, body, wing, and vertical tail. Data were obtained at a variety of angles of attack, sideslip angles, and canard angles.

Report presenting an investigation of three cone-cylinder bodies to obtain boundary-layer-transition data at very low ratios of wall to local stream temperature. Surface finishes at several levels of roughness height were tested. Results regarding the smooth body and rough bodies are provided.

Memorandum presenting an investigation of the performance of a five-stage transonic research compressor with distorted inlet flow. Both overall performance and individual blade-row performance results over a range of compressor speeds and equivalent weight flows were obtained with three circumferential inlet flow-distortion patterns covering annular extents of 60, 120, and 180 degrees. Results regarding compressor-inlet conditions and overall performance and individual blade-row performance are provided.