Report discussing testing of two models of the Chance Vought Regulus II missile to determine its drag characteristics for a range of Mach numbers. The measured total-drag-coefficient data was extrapolated to external-drag-coefficient data and presented.

Report presenting an evaluation of a piston-type gas-generator engine by comparing the performance of a transport airplane powered with than engine with the same airplane powered by different engines. The engines compared were a turbojet engine, a turbine-propeller engine, a compound engine, and a turbosupercharged reciprocating engine utilizing a variable-area exhaust jet nozzle. Results regarding optimum altitude and transport performance are provided.

Memorandum presenting an investigation of the change in spanwise load distribution at high Mach numbers, which is of considerable interest because lateral movement of the center of lift affects the trim, stability, and structural factors of safety of an airplane. The data is not sufficient to permit isolation of the effects of changes in wing configuration, but in a majority of cases, the tests reveal a tendency for the center of lift to shift outboard with increasing Mach number.

From Summary: "Exact solution of the laminar-boundary-layer equations for wedge-type flow with constant property values are presented for transpiration-cooled surfaces with variable wall temperatures. The difference between wall and stream temperature is assumed proportional to a power of the distance from the leading edge. Solutions are given for a Prandtl number of 0.7 and ranges of pressure-gradient, cooling-air-flow, and wall-temperature-gradient parameters. Boundary-layer profiles, dimensionless boundary-layer thicknesses, and convective heat-transfer coefficients are given in both tabular and graphical form. Corresponding results for constant wall temperature and for impermeable surfaces are included for comparison purposes."

"The Ackeret iteration process is utilized to obtain higher approximations than that of Prandtl and Glauert for the flow of a compressible fluid past a circular arc profile. The procedure is to expand the velocity potential in a power series of the camber coefficient. The first two terms of the development correspond to the Prandtl-Glauert approximation and yield the well-known correction to the circulation about the profile" (p. 385).

From Summary: "The effect on drag of positioning symmetrically mounted Douglas Aircraft Company, Inc. stores in pairs on a parabolic fuselage of fineness ratio 10.0 has been determined by flight tests of rocket-propelled, zero-lift models through a range of Mach number from 0.9 to 1.8. The stores were mounted in half-submerged positions and on pylons and were tested in three longitudinal locations on the fuselage with the forward position being located at the maximum diameter of the fuselage. The effects on drag of removing the half-submerged stores or extending them outward on pylons also was investigated by tests of models with half-submerged-store cavities on the fuselage. Two pylons differing in airfoil section and thickness were tested at the forward position of the stores on the fuselage with cavities."

The performance at inlet pressure of 21 inches mercury absolute and inlet temperature of 538 R for the 10-stage axial-flow X24C-2 compressor from the X24C-2 turbojet engine was investigated. the peak adiabatic temperature-rise efficiency for a given speed generally occurred at values of pressure coefficient fairly close to 0.35.For this compressor, the efficiency data at various speeds could be correlated on two converging curves by the use of a polytropic loss factor derived.

"An investigation has been made in the Langley Unitary Plan wind tunnel at Mach numbers of 1.60, 1.80, and 2.00 to determine the aerodynamic characteristics of a 0.03-scale model of the Avro CF-105 airplane. The investigation included the determination of the static longitudinal and lateral stability, the control and the hinge-moment characteristics of the elevator, rudder, and aileron, as well as the vertical-tail-load characteristics. Although the data are presented without analysis, a limited inspection of the longitudinal control results indicates a loss in maximum lift-drag ratio due to trimming of about 1.8 because of the large static margin" (p. 1).

Report presenting an investigation in the transonic tunnel on the effect of sweepback angle on the wing-body characteristics at a range of Mach numbers. Results regarding lift characteristics, drag characteristics, and pitching-moment characteristics are provided.

"An experimental investigation in the Langley Gas Dynamics Laboratory has been made of the flow separation from slender rods mounted to extend forward along the axes of symmetry of blunt-nosed bodies. The mechanism of the separation and its governing criteria are discussed. Drag data at a Mach number of 2.72 for various rod lengths and nose radii at an angle of attack of zero degrees are presented. It was found that the drag coefficients of blunt noses could be appreciably reduced by the use of protruding rods. Criteria for rod length which gives lowest drag are given" (p. 1).

Report presenting analytical methods to calculate average and local turbine-blade temperatures. The temperatures were compared with experimental data obtained in a forced-convection, water-cooled aluminum turbine over a range of turbine-inlet-gas temperatures and coolant-mass velocities. Results regarding comparison of calculated and experimental aluminum turbine blade temperatures, comparison of calculated and experimental stationary-blade temperatures, stationary water-cooled blade operating data, and turbine operating data are provided.

Report discussing an investigation using rocket-propelled vehicles in free flight to determine the effect of fuselage-diameter - wing-span ratio on the damping-in-roll characteristics of delta wings at a range of Mach numbers. The damping-in-roll derivative was found to decrease when the fuselage-diameter - wing-span ratio was increased. The experimental results are compared to calculated values.

Report presenting an investigation in an altitude chamber to determine the power extraction and braking characteristics of a windmilling single-spool axial-flow turbojet engine of the 5000-pound thrust class over a range of altitudes and Mach numbers. Results regarding extractable horsepower from a windmilling engine, total pressure gradient through a windmilling engine, contribution of a compressor to extracted horsepower, and braking of the windmilling engine are provided.

Report presenting an investigation to determine the characteristics of a double-shroud cooling-air ejector. The performance of a single-shroud ejector with a clamshell-type variable-area actuating nozzle was compared with that of an ejector having a conical nozzle. Results regarding the mechanics of ejector flow systems, effect of variable-area primary nozzle on ejector performance, double-shroud-ejector performance, and application of data are provided.

Report presenting a flight investigation to determine the effect that inclination of the principal axis of inertia as produced by varying the wing incidence angle has on dynamic lateral stability of the Republic XF-91 airplane. Results indicated that the wing incidence angle had a negligible effect on the period of lateral oscillation.

Report presenting the airplane drag problem at transonic and supersonic speeds. The area rule is shown to be a powerful tool that provides guidance for designers in selecting aerodynamic features compatible with low wave drag. Analytical methods have been developed that permit quantitative evaluation of the wave-drag level likely to be experienced with a given design.

Report presenting testing of six 1-series axisymmetrical nose air inlets of 8-inch maximum diameter at zero forward velocity in the 8-foot transonic tunnel. Total-pressure surveys, pressure-recovery measurements, and flow-visualization studies were made through a range of mass-flow ratio from below the normal operating range to choking. Results indicate that the performance characteristics of the inlets with differing amounts of roundness varied widely.

Memorandum presenting the performance of a variable-internal-contraction inlet without boundary-layer removal measured at Mach numbers of 2.00, 2.50, and 2.92. The total-pressure recovery at the design Mach number, 2.50, was 0.78. Results regarding total-pressure recovery and contraction ratio, flow unsteadiness and distortion, and summary data correlations are provided.

Report presenting the results of an experimental investigation on the ablation of a number of promising materials for heating conditions comparable to those which maybe encountered by unmanned reentry satellite vehicles or heating conditions associated with reentry ballistic missiles. Results regarding exploratory tests, further Teflon tests, and graphite testing are provided.

Report presenting wing loads and load distributions obtained by differential-pressure measurements between the upper and lower surfaces of the wing of the Douglas X-3 research airplane with various leading-edge-flap deflections. The load and hinge-moment characteristics of the leading-edge flap are presented for a range of Mach numbers with and without flap deflection. Results regarding chordwise load distributions, wing-section and wing-panel characteristics, span load and pitching-moment distributions, leading-edge-flap characteristics, and a comparison with wind-tunnel data are provided.

Report presenting an investigation of the effect of screens in a dump-type diffuser in the 2- by 2-foot supersonic wind tunnel at Mach number 3.85. Results of a slanted half screen of 0.41 solidity, positioned 0.263 inlet diameter from the cowl lip, are presented on a range basis, as this configuration allows for shortening of the subsonic diffuser.

The dynamic longitudinal stability characteristics of eight airplanes as defined by the period and damping of the longitudinal oscillations were measured in flight to determine the degree of stability that may be expected in conventional airplanes. An attempt was made to correlate the measured stability with pilots' opinions of the general handling characteristics of the airplanes in order to obtain an indication of the most desirable degree of dynamic stability. The results of the measurements show that the period of oscillation increases with speed. At low speeds a range of periods from 11 to 23 seconds was recorded for the different airplanes. At high speeds the periods ranged from 23 to 64 seconds. The damping showed no definite trend with speed.