Report presenting a method for predicting the drag due to lift and lift-drag ratio of all-movable wing and body combinations and all-movable wings in the presence of bodies at supersonic speeds. The method is used to calculate the factors for configurations at which experimental data are available.

Report presenting an investigation in the high-speed 7- by 10-foot tunnel through a range of Mach numbers to determine the effects of external-store fineness ratio, store shape, store chordwise position, pylon thickness, pylon length, and pylon sweep angle on the aerodynamic characteristics of a number of underwing pylon-suspended external stores in combination with a 45 degree sweptback semispan wing and fuselage.

Report presenting a wing-body combination with a plane triangular wing of aspect ratio 2 with NACA 0005-63 thickness distribution in streamwise planes, which has been twisted and cambered for a trapezoidal span load distribution at subsonic and supersonic Mach numbers.

Performance of a J47D (RX1-1) turbojet engine equipped with afterburner, variable-area exhaust nozzle, and integrated electronic control was determined over a range of flight conditions. These data were obtained with the electronic control both operative and inoperative. For operation with scheduled exhaust nozzle area, the minimum specific fuel consumption of 1.15 pounds of fuel per hour per pound of net thrust occurred at about 7200 rpm at altitudes from 5000 to 25,000 feet at a flight Mach number of 0.19.

Report summarizing several experimental tail-pipe-burner investigations to indicate the effects of tail-pipe-burner design variables on the performance and operating characteristics. Most of the configurations were investigated over a wide range of altitudes and flight Mach numbers. The results indicate the desirable design features of a tail-pipe burner that will operate with high combustion efficiency and exhaust-gas temperature up to an altitude of approximately 50,000 feet.

From Introduction: "Results presented herein show the altitude performance of the turbine-propeller engine and its components and the applicability of the generalization method for predicting engine and component performance at altitudes other than the test altitude. Data from a brief investigation of windmilling and altitude starting characteristics of the engine also presented."

Report discussing an investigation into the lateral-control characteristics and the pitching-moment characteristics of a scale model of the X-1 wing-fuselage configuration. Information about the estimated variation of rolling effectiveness and wing-fuselage pitching-moment coefficient is described in detail.

Report presenting testing using rocket-powered models to provide an experimental comparison with linearized theoretical calculations for zero-lift drag of sweptback tapered wings with thin, symmetrical, double-wedge airfoil sections. The theory compared favorably with experimental results over most of the test range. Taper was generally found to increase wing drag at low supersonic speeds but reduced drag at higher speeds.

From Summary: "Experimental force, moment, and center-of-pressure variations for a large number of bodies of revolution have been compared with the calculated characteristics based on the approximate theory developed in NACA-RM-A9I26. The bodies varied in fineness ratio from 4.5 to 21.1, from blunt unboattailed bodies to airship hulls, and the experimental results are given for widely varying Mach number ranges of angle of attack. It is shown that the lift and drag characteristics are fairly accurately predicted by the theory but that the actual center of pressure is more rearward than the theory indicates."

Report presenting the flight-determined buffet boundaries of ten airplanes. Comparisons are made with five possible buffeting criteria related to airfoil-section characteristics. The primary factors that determine buffeting criteria are critical Mach number, Mach number of sonic flow at the crest, lift-divergence Mach number, lift-peak Mach number, and empirical buffeting criterion are provided.

From Introduction: "The engine evaluation of blends reported herein was conducted at the NACA Lewis laboratory. The data contained in references 2 to 14 are therefore summarized and the effect of the molecular structure of fuels on antiknock performance is shown in herein."

Memorandum presenting pressure distributions on two wing-body combinations obtained at a Mach number of 1.9 to investigate the wing-body interference. A rectangular wing, a triangular wing, and a cylindrical body with an ogive nose were studied alone and in combination. The pressure distributions over the wing-body combination compared favorably with theoretical calculations based primarily on a generalization of the method of Nielsen and Matteson, except at the root section of the wings where the boundary layer of the body modified the flow.

Report presenting testing of two two-blade propellers in the 8-foot high-speed tunnel for a range of blade angles and Mach numbers. The results show that changes in thrust loading due to compressibility effects were much smaller for the thin-blade propeller than for the thick-blade propeller.

A wind tunnel investigation has been conducted to determine the steady-state windmilling and engine speed decay characteristics of the J34-WE-32 turbo-jet over a range of altitudes from 5000 to 50,000 feet and simulated flight Mach numbers from 0.19 to 1.06. The effect of an engine accessory load on the speed decay characteristics was also determined. The accessory load was about 7.8 horsepower for engine speeds above 4000 rpm and decreased with decreasing engine speed. An analysis of the speed decay data was made and engine speed decay rates were determined for hypothetical accessory loads up to 40 horsepower.

A spark energy of 2.13 joules per spark at 1 spark per second produced ignition to an altitude of 50,000 feet at a flight Mach number of 0.6. The minimum power requirements for ignition were obtained from a combination of low spark repetition rates and high spark energy. The altitude-ignition limit was also increased by increasing spark-gap immersion, fuel temperature, inlet-air temperature, and fuel volatility, and by decreasing flight Mach number. The maximum altitude at which flame propagation was accomplished from combusters with spark plugs to combusters without spark plugs to combustors without spark plugs was increased about 5000 feet by increasing fuel volatility.

"A multiple-range potentiometer circuit is described that provides automatic measurement of temperatures or temperature differences with any one of several thermocouple-material pairs. Techniques of automatic reference junction compensation, span adjustment, and zero suppression are described that permit rapid selection of range and wire material, without the necessity for restandardization, by setting of two external tap switches" (p. 1).

An investigation was made of the variation of the pressure limits of flame propagation with tube diameter for quiescent propane with tube diameter for quiescent propane-air mixtures. Pressure limits were measured in glass tubes of six different inside diameters, with a precise apparatus. Critical diameters for flame propagation were calculated and the effect of pressure was determined. The critical diameters depended on the pressure to the -0.97 power for stoichiometric mixtures. The pressure dependence decreased with decreasing propane concentration. Critical diameters were related to quenching distance, flame speeds, and minimum ignition energy.

From Summary: "As part of an overall program for the experimental investigation of large-scale jet nozzles, a preliminary evaluation of the internal performance characteristics of several variable-throat extended-plug-type nozzles was obtained over a range of nozzle pressure rations from 2 to 15 with nozzle throat variations as great as 2:1. The extended-plug nozzle attained peak thrust coefficients as high as those which have been attained with fixed-geometry convergent-divergent nozzles. The thrust coefficients of the extended-plug nozzles were relatively insensitive to both nozzle pressure ratio and throat area over the range investigated."

Report presenting an investigation to compare the characteristics of a full-span and a semispan highly swept wing in order to evaluate the general validity of the semispan wing testing technique. Results regarding the lift, drag, and pitching-moment characteristics are provided.

"An experimental investigation of the aerodynamics of a slender cone-cylinder body of revolution was conducted at a Mach number of 3.85 for angles of attack of 0 degree to 10 degrees and a Reynolds number of 3.85x10(exp 6). Boundary-layer measurements at zero angle of attack are compared with the compressible-flow formulations for predicting laminar boundary-layer characteristics. Comparison of experimental pressure and force values with theoretical values showed relatively good agreement for small angles of attack. The measured mean skin-friction coefficients agreed well with theoretical values obtained for laminar flow over cones" (p. 1).

Report presenting the results of a wind-tunnel investigation to determine the control effectiveness and variations of forces and moments as functions of angles of attack and sideslip for a scale model of the MX-775A missile at a range of Mach and Reynolds numbers. Results regarding the static longitudinal stability and control characteristics, Reynolds number effects, lateral-control characteristics, and clipped-wing configuration characteristics are provided.

Memorandum presenting an investigation of the effect on load-range performance of various combinations of compressor pressure ratio and turbine-inlet temperature for the turbine-propeller engine and to provide a means for comparing the load range of turbine-propeller and turbojet engines for a range of flight speeds.

Report presenting an investigation to determine the effects of a simplified form of boundary-layer control on the low-speed longitudinal characteristics of a sweptback wing. The primary objective was to improve the longitudinal characteristics of the sweptback wing at lift coefficients below the maximum. Results regarding the characteristics of the wing without boundary-layer control and effects of boundary-layer control are provided.

"An investigation of the performance of a 16-inch ram jet engine having a single oblique-shock all-external compression inlet designed for a flight Mach number of 1.8, was conducted in the NACA Lewis 8-by 6-foot supersonic wind tunnel. Data were obtained at Mach numbers from 1.5 to 2.0 and angles of attack from 0 degrees to 10 degrees. Three exit nozzles were used; a cylindrical extension of the combustion chamber, a 4 degrees half-angle converging nozzle with a 0.71 contraction ratio, and a graphite converging-diverging nozzle having a 0.71 contraction ratio plus reexpansion to essentially major body diameter" (p. 1).