Report discussing the aerodynamic characteristics in pitch and sideslip of a model of a Douglas D-558-II airplane with and without a yaw-damper vane at Mach number 2.01. A revised model was tested using a canopy and modified vertical tail. The revised configuration was found to have higher directional stability, trim lift coefficients, drag, and more positive effective dihedral than the original configuration.

Report presenting an investigation to determine the characteristics in yaw of a trapezoidal wing of aspect ratio 4 with circular-arc airfoil sections and 0.20-chord rear and drooped-nose flaps. Measurements of lift, lateral force, rolling moment, and yawing moment of four configurations were made for a range of angles of attack and yaw angles.

Report presenting the results of theoretical incompressible-flow calculations of the spanwise lift distributions, lift-curve slopes, spanwise centers of pressure, aerodynamic centers, coefficients of damping in roll, rolling-moment coefficients due to aileron deflection, and induced-drag coefficients of twenty M, W, and delta wings.

Report presenting an investigation in the high-speed tunnel to determine the pressure distribution at the 20-, 46-, and 65-percent wing semispan stations on a plug-type spoiler and a segment of a semaphore-type spoiler. The investigation was carried out at a range of Mach numbers and angles of attack. The pressure distributions and integrated section force and moment data are presented without discussion.

Memorandum presenting an evaluation of the handling qualities of the Northrop X-4 swept-wing semitailless airplane covering a speed range from stall to a Mach number of 0.92 primarily at 30,000 feet. The characteristic problems of tailless airplanes at low speeds, such as marginal longitudinal stability and control resulting in close center-of-gravity limits, were encountered. Results regarding static longitudinal stability characteristics, dynamic stability characteristics, and static lateral and directional stability and control are provided.

From Introduction: "The present paper contains the results of the investigation of the aerodynamic characteristics at Mach number of 2.01 of the two cruciform wing missiles equipped with larger canard controls and compares the result with that obtained previously with a smaller control."

From Introduction: "In this report two-stage-turbine efficiency characteristics are analyzed as a function of work and speed requirements in terms of the effect of changing the required mean-section velocity diagram. The fundamental assumptions and limits used in reference 2 and 3 are also used herein."

Report presenting the results of a free-flight investigation to determine the effect of wing warp on the lift, drag, and static longitudinal stability characteristics of a low-drag aircraft with an arrow wing of aspect ratio 1.86. Results regarding the trim, drag, lift-drag ratios, and normal force and pitching moment are provided.

Report presenting an investigation to determine the effects of initial subsonic diffusion rate, variable geometry, and throat boundary-layer control on the performance of an axisymmetric double-cone inlet. Major gains in performance at higher Mach numbers were obtained with boundary-layer control in the form of a ram scoop at the throat. Results regarding the effect of internal-area distribution, effect of spike translation, and effect of throat boundary-layer control are provided.

From Introduction: "The particular blade design, the tests of which are described in the present paper, was one necessary to the investigation of the effect of differences in blade-thickness ratios."

Report presenting flight tests over a range of Mach numbers to study the effects of a simulated afterburning turbojet engine on the gross longitudinal flight characteristics of two geometrically identical models of a swept-wing fighter-type configuration. Results regarding the trim characteristics, lift, pitching moment, dynamic stability, and drag are provided.

The spectrum concept is employed to study the selective effect of a stream contraction on the longitudinal and lateral turbulent velocity fluctuations of the stream. By a consideration of the effect of the stream contraction on a single plane sinusoidal disturbance wave, mathematically not dissimilar to a triply periodic disturbance treated by G. I. Taylor, the effect on the spectrum tensor of the turbulence and hence on the correlation tensor is determined.

"The lateral- and directional-stability and -control characteristics of a twin-engine patrol airplane as predicted from the results of wind-tunnel tests of a powered model and as measured in flight are compared in this report. The predictions from wind-tunnel-test data were in good agreement with the flight-test results. The results show that such predicted flying-qualities characteristics are sufficiently accurate to indicate the unsatisfactory lateral- and directional-stability and -control characteristics of airplanes in the preliminary design stage" (p. 1).

"Internal performance of an XJ79-GE-1 variable ejector was experimentally determined with the primary nozzle in a representative nonafterburning position. Jet-thrust and air-handling data were obtained in quiescent air for 11 selected ejector configurations over a wide range of operation. Additional data, at specific operating conditions, were obtained which indicate the ejector diameter ratio for peak jet-thrust performance. The experimental ejector data are presented in both graphical and tabulated form" (p. 1).

"An investigation has been made in the Langley 4 by 4-foot supersonic pressure tunnel at Mach numbers of 1.82 and 2.01 to determine the longitudinal and lateral static-stability characteristics of a 0.04-scale model of the Lockheed F-104A airplane. The effects of a modified vertical tail, several ventral-fin arrangements, and several external store arrangements were also determined. The tests were made at Reynolds numbers of 1.02 (exp 6) and 1.382 (exp 6), respectively, based on the wing mean geometric chord" (p. 1).

Report presenting an investigation in the 19-foot pressure tunnel to determine the effects of leading-edge stall-control devices and trailing-edge flaps on the longitudinal stability characteristics of a 47.7 degree sweptback wing that could have aspect ratios of 5.1 and 6.0 by using interchangeable wing tips. The effects of wing fences, roughness, and a fuselage were also determined. Results regarding the lift characteristics and lift-drag ratios are also provided.

Report discussing an experimental and analytical investigation in order to study the pressure-rise and leakage-loss characteristics of rotating cowlings. A comparison of the theoretical and experimental results indicated that pressure-rise characteristics can be predicted if internal-flow losses and internal-flow angle at the cowling-vane trailing edge are known.

Report presenting an experimental investigation at low speed to determine the pressure-recovery and drag characteristics of an NACA submerged intake and deflector installation on the rearward portion of the fuselage of a model.

Results of a free-flight investigation at supersonic speeds to determine zero-lift drag of a series of bodies of revolution are presented. Configurations tested included two parabolic bodies with fineness ratios of 17.78 and 24.5 and two 8 degree cone-cylinder bodies with fineness ratios of 17.2 and 21.2. Results of previous tests of similar parabolic bodies but with lower fineness ratios are included in this paper for comparison. All bodies for which data are presented in this paper had a base-to-maximum-diameter ratio of 0.437. Calculated drag coefficients are shown for all bodies for which data are presented. (author).