Memorandum presenting an altitude investigation to determine the basic mechanism by which J65-W-4 turbine rotor-blade failures were occurring in service. The engine was installed in an altitude test chamber and a series of controlled engine throttle bursts, with and without inlet-air distortion, over a range of altitudes, flight Mach numbers, and inlet-air temperatures. An examination of the data obtained during the investigation indicated that the danger of turbine failure could be eliminated without any appreciable sacrifice in engine acceleration time.

Memorandum presenting tests conducted with four specific versions of a swept-wing fighter airplane, which indicate that a large reduction in external-drag coefficient was accomplished by redesigning the original configuration. The forebody modifications, which consisted of a smaller canopy, slimmer nose, and sharper inlet lip, reduced the value of the external-drag coefficient from 0.044 to 0.042 at a Mach number of 1.05 and from 0.042 to 0.040 at a Mach number of 1.28.

Memorandum presenting a free-flight investigation to determine the lift, drag, static stability, and hinge-moment characteristics of a rocket-powered model of a rocket-powered model of a ballistic-missile configuration at supersonic speeds. The model consisted essentially of a body of fineness ratio 16.9 and a cruciform set of small 60 degree delta fins located approximately 1 body diameter from the base of the body. The model lift and pitching-moment coefficients were nonlinear with angle of attack.

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.

Memorandum presenting a low-speed investigation to determine the effect of a fuselage on the longitudinal aerodynamic characteristics of a 45 degree sweptback wing equipped with 0.35-semispan double slotted flaps. The wing had an aspect ratio of 3.7, a taper ratio of 0.41, and a streamwise thickness ratio of 0.086.

Data were calculated for equivalence ratios of 1 to 3, chamber pressures of 300 and 600 pounds per square inch absolute, and pressure ratios of 1 to 1500. Parameters included are specific impulse, combustion and exit temperature, molecular weight, characteristic velocity, coefficient of thrust, ratio of nozzle-exit area to throat area, specific heat at constant pressure, isentropic exponent, viscosity, and thermal conductivity. A correlation is given which permits determination of performance for a wide range of chamber pressures.

Report presenting a wind-tunnel investigation at low speed to determine the effects of sideslip on the static longitudinal trim characteristics of three fighter-type airplane models. The three models consisted of a 45 degree swept-wing model with a horizontal tail geometrically similar to the wing and mounted slightly below the wing, a clipped-delta-wing model with a horizontal tail mounted in a moderately high position, and a 60 degree delta-wing with no horizontal tail. Results regarding static longitudinal stability, variation of pitching-moment coefficient with sideslip, effect of modifications to Model B on static longitudinal stability and variation of pitching-moment coefficient with sideslip, and static lateral stability are presented.

Report presenting a brief study utilizing pilots to fly a simulator of some longitudinal stability and control problems of an assumed aircraft capable of flights to altitudes essentially out of the atmosphere. The results show that more than the inherent longitudinal damping of the aircraft is necessary to affect a safe flight, particularly during entry into the atmosphere. Results regarding some preliminary considerations, entry, and control in ascent and the ballistics trajectory are provided.

From Introduction: "The results of tests in which area suction was applied near the leading edge of the wing or the knee of a leading-edge flap are reported in references 1 through 5."

Report presenting an examination of the limitations of the use of jet momentum coefficient as a correlating factor in comparing tests of blowing-type boundary-layer control. Theoretical and experimental data indicate that it should be an acceptable parameter where the duct pressures are large.

Report presenting exploratory measurements of the fluctuations of wing bending moment during normal performance and wind-tunnel testing of a model of the Douglas D-558-II from Mach numbers 0.60 to 0.96. The effects of leading-edge chord-extensions and pylon-mounted underwing external stores were investigated. Results regarding the general nature of buffeting measurements, frequency distribution of buffeting response, interpretation of model buffeting measurements, and effects of changes in model configuration are provided.

Report presenting an investigation made in the 7- by 10-foot tunnel of the static lateral and directional stability and some tail-load characteristics of a model with a highly tapered swept wing and two horizontal-tail positions. Testing were made with the horizontal tail located at the tip of the swept vertical tail and with the horizontal tail located in the wing-chord plane extended. Results regarding static lateral and directional stability and vertical-tail loads 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.

From Summary: "A wind-tunnel investigation has been made in the Langley high-speed 7- by 10-foot wind tunnel by use of the transonic-bump technique to study the effectiveness of spoiler-type controls on 9 unswept untapered wings. Full-span spoilers, projected to 7.5 percent wing chord along the 40-, 60-, 80-, and 100-percent wing chord lines, were tested on wings of aspect ratio 1 to 6 at Mach numbers from 0.6 to 1.10. Most of the data are presented without analysis."

Memorandum presenting an investigation of the location of transition from laminar to turbulent flow in the boundary layer on two bodies of revolution at zero angle of attack in a low-turbulence wind tunnel. One body was a prolate spheroid of fineness ratio 9.0 made out of aluminum and the other was a modified prolate spheroid of fineness ratio 7.5 made out of steel and covered with fiberglass and resin.

From Introduction: "The primary purpose of the wing instrumentation was to obtain data for use in design of NACA research missiles; however, it is believed that the wing is representative of typical supersonic designs and that the data will be of general use and interest. Only the wing data are reported herein."

Experimental values of damping in roll at zero angle of attack of the Douglas D-558-II research airplane and its components have been obtained at five different Mach numbers. Large effects of Reynolds number, boundary layer, and wing-incidence angle on the damping in roll were obtained.

From Introduction: "Presented in this report are the basic data obtained from investigation. The data are presented with limited analysis in order to expedite their availability to those concerned with jet-exit-afterbody design."

Memorandum presenting a high-flow sonic-inlet compressor rotor employing double-circular-arc blade sections that was designed and tested in Freon-12. Results regarding overall performance, radial distribution, and blade-element performance are provided.

From Summary: "An analysis is given of the oscillating motion of a ballistic missile which upon entering the atmosphere is angularly misaligned with respect to the flight path. The history of the motion for some example missiles is discussed from the point of view of the effect of the motion on the aerodynamic heating and loading. The miss distance at the target due to misalignment and to small accidental trim angles is treated. The stability problem is also discussed for the case where the missile is tumbling prior to atmospheric entry."

Report presenting the aerodynamic heat-transfer properties and zero-lift drag of a typical pilot's canopy as determined by a rocket-model flight test through a range of Mach and Reynolds numbers. The canopy had a 63 degree sweptback flat windshield, circular cross section, and an equivalent body fineness ratio of 7.0. Results regarding the canopy temperature distribution, canopy pressure distribution, heat-transfer coefficient, and drag are provided.

Report presenting a free-flight investigation over a range of Mach numbers at a range of lift coefficients to determine the aerodynamic characteristics of an airplane-configuration model with a 52.5 degree delta wing and a low, swept horizontal tail. Results regarding time history, longitudinal trim, lift, drag, longitudinal static stability, side-force characteristics, and theoretical comparisons are provided.

Report presenting a free-flight investigation to determine the lift, drag, static stability, and hinge-moment characteristics of a rocket-powered model of a ballistic-missile configuration. The purpose of this particular investigation was to determine these characteristics with a long run of boundary layer ahead of small 60 degree delta stabilizing fins.

Report presenting an investigation in the transonic tunnel to determine the characteristics of several flap-type spoiler ailerons, lower-surface deflector ailerons, and spoiler-slot-deflector ailerons. Six-component force and moment data were obtained at a range of Mach numbers and angles of attack.