Report presenting an investigation in the 4- by 4-foot supersonic pressure tunnel to determine the effects on the static longitudinal stability and control characteristics of various modifications to a 0.065-scale model of the Chance Vought Regulus II missile. Some of the modifications included control housing on top of the fuselage, two sizes of canard surfaces with fixed incidence angles, various angles of nose droop, and two types of inlet boundary-layer bleed diverters.

Report presenting a flight test conducted to determine the minimum drag of a 0.11-scale rocket-boosted model of the Chance Vought XF8U-1 airplane with a transonic-area-rule fuselage-cross-sectional-area development. Results regarding the trim normal-force coefficient and measured drag are provided.

Memorandum presenting a wing-root inlet configuration in which inlet components were varied and was tested in the 4- by 4-foot supersonic pressure tunnel at 3 Mach numbers. Angles of attack and sideslip ranges were also varied. Inlet performance and engine-flow distortions as affected by pitch, sideslip, inlet-lip sweep, contraction ratio, boundary-layer control, and engine bypass are presented and discussed.

Report presenting the lift and drag characteristics of a 60-degree delta-wing interceptor airplane with fuselage extension and indentation at a range of Mach numbers and altitudes. A comparison with a prototype airplane and a comparison of the flight results with the model tests are provided.

"An investigation has been conducted in the Langley 4- by 4-foot supersonic pressure tunnel to determine the effects on the static longitudinal stability and control characteristics of various modifications to a 0.065-scale model of the Chance Vought Regulus II missile. The modifications consisted of a control housing on top of the fuselage, two sizes of canard surfaces with fixed incidence angles, various angles of nose droop, and two types of inlet boundary-layer bleed diverters. The tests were made at a Mach number of 2.01 and a Reynolds number, based on the mean aerodynamic chord of 1.54 x 10(exp 6)" (p. 1).

Memorandum presenting an analysis of a system consisting of a mercury turbine-driven air compressor a mercury condenser wherein heat was added to the compressed air. The heat addition to the mercury is accomplished in an intermediate heat exchanger (mercury boiler) which has a liquid metal, other than mercury, circulating through the opposite side and through a nuclear reactor. Results regarding the turbine-exhaust pressure, turbine-inlet pressure, condenser-inlet Mach number, effect of nacelle drag, and some general data are provided.

Report presenting measurements of the thermal distortion of a stainless-steel clad, cadmium-silver reactor control rod. The temperature pattern of the rod is described. The maximum reduction in clearance obtained in the tests was 0.203 inch.

Skin temperature and surface pressure of blunted cone-cylinder-flare configuration free flight test vehicle to hypersonic speeds.

Report presenting the results of a wind-tunnel investigation of the effects of variation of trailing-edge angle and leading-edge radius on the aerodynamic characteristics of a 10-percent-chord-thick airfoil section at a range of Mach numbers.

Thermal distortion tests were made on a stainless steel clad, cadmium-silver control rod furnished by the Argonne National Laboratory. Two temperature patterns supplied by the Argonne National Laboratory were simulated in these tests; one represented the shim-rod-out condition and the other the shim-rod-50-percent-inserted condition. The greatest reduction in clearance effected by thermal distortion was 0.076 inch. No permanent set of the control rod was observed after repeated heating and cooling cycles.

An arbitrary weak spatial distribution of vorticity can be represented in terms of plane sinusoidal shear waves of all orientations and wave lengths (Fourier integral). The analysis treats the passage of a single representative weak shear wave through a plane shock and shows refraction and modification of the shear wave with simultaneous generation of an acoustically intense sound wave. Applications to turbulence and to noise in supersonic wind tunnels are indicated.

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.

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.

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 the lift and drag characteristics of a 60 degree delta-wing interceptor airplane with a fuselage extension and indentation. The data was obtained over a range of Mach numbers and altitudes. Results regarding a comparison with a prototype airplane with similar wings and a comparison of the flight tests with model tests are provided.

"Tests were performed on a partial span of the wing of a McDonnell XFD-1 airplane to determine a combination of sealed internal balance and spring-tab stiffness for the aileron that would give satisfactory stick-force characteristics for the airplane. Two sealed internal balances were tested in combination with spring tabs of various stiffnesses. One of the combinations was tested at several speeds to determine the variation of stick force with speed" (p. 1).

Report presenting an investigation of resistance screens for the purpose of obtaining uniform flow in ducts. The new screen designs consisted of several different screen shapes with the elements set at oblique angles (swept) to the flow. Results regarding a rectangular channel and diffuser investigation are provided.

Report presenting the aerodynamic load characteristics for a wing-body combination for a range of Mach numbers and angles of attack. Two wings with the same dimensions but different types of construction (one of solid steel, one of plastic with an inner steel core) were tested. Results regarding flow studies, chordwise pressure distributions, spanwise load distributions, panel loads, center of loads, and twist distribution are provided.

Memorandum presenting tests conducted to determine the flight characteristics of an F-86F airplane equipped with an area-suction-type boundary-layer control installation on the trailing-edge flaps. Measurements were made of the lift, drag, and engine bleed-air requirements. Results regarding the aerodynamic characteristics as well as some miscellaneous characteristics are provided.

Report presenting the static and dynamic-rotary stability derivatives for an airplane with an unswept wing and a high horizontal tail as determined in wind-tunnel tests at 3 Mach numbers. The tail contribution to stability was found to not be predicted by the simplified theoretical methods used in this report. Results regarding the longitudinal derivatives, sideslip derivatives, yawing derivatives, rolling derivatives, and variation of static derivatives with Mach number.

From Introduction: "Wind-tunnel and flight tests have shown that conical leading-edge camber on a thin low-aspect-ratio delta wing results in increasing the lift-drag ratio at transonic and low supersonic speeds (refs. 1 and 2). References 3 and 4 present the results of two previous investigations of this general program. A more detailed analysis of the pressure distributions of reference 5 is presented herein in terms of total section loads and overall wing-body characteristics."

From Summary: "An investigation was conducted to determine the longitudinal characteristics of an airplane model with a 35 degree swept wing of aspect ratio 7 and four pylon-mounted nacelles. Several leading-edge configurations were studied in conjunction with double-slotted trailing-edge flaps. Three-component longitudinal data are presented. In general, the test Reynolds number was about 4.8 x 10(exp 6), but for selected configurations, data for Reynolds number ranges from 2.8 to 8 x 10(exp 6) are included."