From Introduction: "Range in more or less steady level flight depends directly on aerodynamic lift-drag ratio at high supersonic speeds, just as it does at lower speeds. This result follows from the classical Breguet range equation in the case of powered flight, and it may be easily deduced from the equations of motion for unpowered or gliding flight (see refs. 1 and 2)."

Memorandum presenting wind tunnel tests performed on a family of missiles. This paper summarizes some of the performance and stability and control characteristics of the missiles.

Report presenting a comparison of three hypervelocity vehicles: a ballistic rocket, a skip rocket, and a rocket glider. Range efficiency, automatic heating, and problems of glide rockets are explored.

Report presenting an investigation to evaluate the external-store drag reductions obtainable by application of Baldwin's moment-of-area rule. Several wing-body combinations were investigated with and without four typical air-to-air missiles. Results regarding the total-drag measurements, wave-drag components, and effectiveness of moment-of-area rule for reducing the drag of the external-store installations are provided.

The statistical approach to the gust-load problem, which consists in considering flight through turbulent air to be a stationary random process, is extended by including the effect of lateral variation of the instantaneous gust intensity on the aerodynamic forces. The forces obtained in this manner are used in dynamic analyses of rigid and flexible airplanes free to move vertically, in pitch, and in roll. The effect of the interaction of longitudinal, normal, and lateral gusts on the wind stresses is also considered.

The time-average characteristics of boundary layers over a flat plate in nearly quasi-steady flow are determined. The plate may be either insulated or isothermal. The time averages are found without specifying the plate velocity explicitly except that it is positive and has an average value.

Memorandum presenting rudder-pulse maneuvers performed with a swept-wing fighter-type airplane at altitudes from 30,000 to 43,000 feet over a Mach number range of 0.71 to 1.48 to determine the lateral stability characteristics relative to the stability axes, in general, and the lateral derivative characteristics, in particular. Four configurations were employed; three involves different vertical tails with varying aspect ratio or area and the fourth employed a large tail with an extension of the wing tips.

Memorandum presenting an investigation to define the relationships between the extent of laminar flow and such variables as surface smoothness, wall temperature, pressure gradient, and Mach number. The purpose of this particular paper is to review briefly the results that have been obtained from research.

Memorandum presenting an investigation of the flow characteristics over a 6-percent-thick symmetrical circular-arc airfoil section with a 30-percent-chord trailing-edge flap at a Mach number of 6.90 and a Reynolds number of 1.65 x 10(sub 6). The model was tested over an angle-of-attack range of 0 to 16 degrees and a flap-deflection range of -16 degrees to 16 degrees. Results regarding pressure results and aerodynamic characteristics are provided.

Report presenting testing of a 4.5 inch by 4.5 inch tunnel with slots in two opposite walls in order to determine the effects of various slot exit shapes, mixing sections, and diffusers on power requirements. Some of the data obtained included measurements of the pressure ratio required to operate the tunnel, the effects of auxiliary bleed flow, diffuser static-pressure ratios and distributions, and diffuser total pressure distributions.

Report presenting an analysis of the blade-element performance of a highly loaded transonic rotor with double-circular-arc blades. The rotor was purposely loaded beyond the prudent level for exploratory purposes. Results regarding the radial-distribution plots, blade-element data, element blade-to-blade loss variation, and a comparison of steady-state and hot-wire measurements are provided.

Report presenting a wind tunnel investigation to determine the effects of a blowing type boundary-layer control flap on the longitudinal control and lateral stability and control of an F-86D airplane. Tests were made using the following lateral control devices: split-flap-type spoilers, differentially deflected flaps, and differential amounts of blowing over the flaps.

Report presenting calculations by the method of characteristics of 2960 boundaries of supersonic axisymmetric free jets exhausting from conically divergent nozzles into still air. The calculations covered a range of jet Mach numbers, a ratio of specific heats of the jet, divergence angles of the nozzle, and jet static-pressure ratios. Results regarding the effect of increasing the static pressure ratio, the simulation of one jet boundary by another, and interpolation and extrapolation of calculated boundaries are provided.

Memorandum presenting a survey and evaluation of flutter research and flutter engineering, with particular emphasis placed on the design of primary fixed surfaces and primary controls. Analyses are made of recent flutter occurrences to delineate past and future problems, and detailed appraisals are given of the status of the various engineering branches involved in the analytical and experimental prediction of flutter.

Memorandum presenting the subsonic and transonic longitudinal handling qualities of the Douglas D-558-II research airplane with several wing modifications designed to alleviate swept-wing instability and pitch-up. The airplane configurations investigated included the basic wing configuration and two wing-fence configurations in combination with retracted, free-floating, or extended slat,s and a wing leading-edge chord-extension configuration.

Report presenting pressure-distribution data for a drooped-nose-fuselage forebody alone and with four canopy shapes mounted on the forebody. Two canopies had the same shape and size rearward of the windshield but one had a flat and one had a v-shaped windshield, and the other two canopies were located at different body sections with smaller maximum cross-sectional areas, higher fineness ratios, and flat windshields. Results regarding the effect of windshield shape, canopy location, Mach number, sideslip, and angle of attack are provided.

Report presenting measurements in a wind tunnel of the static and dynamic-rotary stability derivatives of a model with an unswept wing of low aspect ratio and a high horizontal tail. Tests were conducted at a range of Mach numbers and angles of attack. Results regarding a variety of aerodynamic characteristics are provided.

From Introduction: "In the present investigation, lift, drag, and pitching moment were determined over a Mach number range 0.6 to 1.42. Smooth-water takeoff and landing stability and resistance were investigated. A brief check of the rough-water spray and behavior was also made."

From Summary: "The available information on the spectrum of atmospheric turbulence is first briefly reviewed. On the basis of these results, methods are developed for the conversion of available gust statistics normally given in terms of counts of gusts or acceleration peaks into a form appropriate for use in spectral calculations. The fundamental quantity for this purpose appears to be the probability distribution of the root-mean-square gust velocity. Estimates of this distribution are derived from data for a number of load histories of transport operations; also, estimates of the variation of this distribution with altitude and weather condition are derived from available data and the method of applying these results to the calculation of airplane gust-response histories in operations is also outlined."

Ignition delays of a diallylaniline-triethylamine mixture and of triethyl trithioposphite with red fuming nitric acid were measured as a function of combustor dimensions, initial propellant temperature, and initial ambient pressure. Ignition delay increased with exhaust-nozzle diameter. Ignition delay also increased as propellant temperature decreased, but did not vary with initial ambient pressure except with the largest nozzle diameter. A correlation among ignition delay, combustor dimensions, and propellant temperature is presented, and the extension of the correlation to other systems is discussed.