Report presenting a correlation of combustion-efficiency data obtained in experimental investigations with 14 aircraft gas-turbine combustors. The precision is not good for some combustors, but can help in predicting the efficiency at different operating conditions and in comparing the performance of different combustors from data obtained in unrelated tests.

Report presenting an investigation of the cooling effectiveness of water films on the inner surface of a well-insulated, 4-inch-diameter duct with air flowing through the duct at a range of temperature and Reynolds numbers. Results regarding the effect of the gas temperature and mass velocity on liquid-cooled length, effect of coolant flow on liquid-cooled length, and some suggestions for further investigation are provided. Equations for correlation are created from the data.

Report presenting a study of data from wind-tunnel investigations to determine the effects of thin chordwise fences on some of the aerodynamic characteristics of four moderately sweptback wings at a low-lift range. The fences caused no large detrimental effects on lift or pitching moment at transonic or supersonic speeds. Results regarding the increment of drag coefficient due to fences, effect of fences on the lift coefficient and longitudinal stability, and effects on aileron effectiveness are provided.

Experimental investigation of aerodynamic forces acting on body of revolution (NACA RM-10 missile) with and without stabilizing fins was conducted at Mach numbers from 1.49 to 1.98 at angles of attack from 0 to 9 degrees and at Reynolds number of approximately 30,000,000. Comparison of experimental lift, drag, and pitching-moment coefficients and center of pressure location for body alone is made with linearized potential theory and a semiempirical method. Results indicate that aerodynamic characteristics were predicted more accurately by semiempirical method than by potential theory. Breakdown of measured drag coefficients into components of friction, pressure, and base-pressure drag is presented for body alone at zero angle of attack.

Report presenting an analytical method for calculating the maximum wall temperature of a tail-pipe burner or a ramjet combustion chamber cooled by air or gas flowing through a surrounding annular passage.

From Introduction: "Performance data are presented in this report to show the characteristics of the turbine operating as an integral part of the engine. Typical results are graphically presented to show the effects of changes in altitude, flight Mach number, and exhaust-nozzle-outlet area on turbine performance. All turbine-performance data obtained are given in tabular form."

"An investigation by the transonic-bump method conducted in the Langley high-speed 7- by 10-foot tunnel to determine the effect of an end plate on the aerodynamic characteristics of a 20.55 degree sweptback wing with an aspect ratio of 2.67 and a taper ratio of 0.5 indicated that the end plate affected the aerodynamic characteristics of the wing at transonic Mach numbers in the same manner as has been observed for swept and unswept wings at low speeds" (p. 1).

Report discusses the result of tests determining the longitudinal-stability characteristics and spanwise distribution of load of a wing model with the leading edge swept back 63 degrees, a thickened tip section, and a twisted and cambered shape. The wing was tested with a fuselage and various devices for altering stall and spanwise boundary-layer flow. Measurements of force, pressure-distribution, and span load distribution are described.

Report presenting an investigation at transonic speeds to determine the maximum lift characteristics of a wing model of the X-1 airplane. Lift, drag, and pitching-moment data for a lift range and range of Mach numbers was collected. Maximum lift was found to be obtained at progressively higher angles of attack as the Mach number was increased.

"Thermocouple probes have been designed to measure with small error the total temperature of gas moving at high velocities. Two major designed are presented: one is applicable to the construction of rakes and the other, of which there are two variations, can be used where exceptional accuracy is desired. The probes were calibrated in two jets; one jet exhausted into the atmosphere and the other into a pressure-controlled receiver" (p. 1).

Report discussing testing to obtain data on booster drag estimates and to investigate the drag of various booster fin configurations. Several tie-rod-braced fin assemblies were investigated with various types and arrangement of tie rods as well as a cantilever fin assembly. The cantilever fin assembly was found to have roughly the same drag coefficients as the most efficient tie-rod-braced assembly.

An investigation was conducted to determine the effect of the inlet Mach number and entrance-boundary-layer thickness on the performance of a 23 degree 21-inch conical-diffuser - tail-pipe combination with a 2:1 area ratio. The air flows used in this investigation covered an inlet Mach number range from 0.17 to 0.89 and corresponding Reynolds numbers of 1,700,000 to 7,070,000. Results are reported for two inlet-boundary-layer thicknesses.

Report presenting static lateral- and longitudinal-stability tests of a scale model of a projected, low-aspect-ratio, supersonic airplane at low and high subsonic Mach numbers. The wing was equipped with leading-edge flaps and had a modified double-wedge airfoil with sharp leading and trailing edges. Results regarding lift characteristics, static longitudinal stability and control, lateral and directional stability, drag characteristics, and wing and fuselage tuft studies are provided.

"An investigation of the static and dynamic longitudinal stability characteristics of 1/3.7 scale rocket-powered model of the Bell MX-776A has been made for a Mach number range from 0.8 to 1.6. Two models were tested with all control surfaces at 0 degree deflection and centers of gravity located 1/4 and 1/2 body diameters, respectively, ahead of the equivalent design location. Both models were stable about the trim conditions but did not trim at 0 degree angle of attack because of slight constructional asymmetries" (p. 1).