Report discussing testing on the performance of two stator-blade shapes with and without boric oxide deposits. The deposits were found to cause total pressure losses and decreases in the blade-exit flow angle. Information about the cascade throat area, boundary-layer momentum thickness, total pressure ratio, and exit flow angle and tangential component of velocity is provided.

Report presenting an investigation of several wingless missile configurations for a range of Mach numbers to determine their lift, drag, and pitching-moment coefficients. Results for missiles having nose controls and missiles having tail controls are provided. The results were also compared to a conventional missile with wings.

Memorandum presenting the buffet characteristics of a scale model of an attack airplane over a range of Mach numbers. The wing had a modified delta plan form with an NACA 0008 airfoil section at the root and an NACA 0005 airfoil section at the tip, a leading-edge sweep of 41.11 degrees, an aspect ratio of 2.91, and a taper ratio of 0.226. Results regarding the frequency spectrum of bending moment, effect of density on root-mean-square bending moment, system damping coefficients, and buffet input force are provided.

Pressure tunnel investigation of supersonic store interference in vicinity of 22 degree swept wing fuselage configuration at Mach numbers 1.61 and 2.01.

"In order to evaluate the post combustion behavior of boric oxide, pentaborane-air mixtures, burned to completion at a combustor pressure of 3 atmospheres, were expanded through a 7.1-inch-long convergent-divergent nozzle having a 4-inch-diameter throat and an exit-to-throat area ratio of 1.68. The experimentally determined thrust performance was in good agreement with the ideal equilibrium performance at stagnation temperatures of 3300 deg R and lower. The boric oxide vapor at the combustor exit required about 400 degrees F supercooling before any condensed phase was observed" (p. 1).

Report presenting heat-transfer measurements for a flat-face cylinder-flare configuration in free flight up to Mach number 2.7. Skin temperatures were measured at 12 points along the configuration. Information about the heating rates was compared to data obtained from theoretical calculations.

Memorandum presenting a comparison of the performance of two aerodynamically similar single-stage rotors of different chord length. Results regarding short-chord-rotor performance, long-chord-rotor performance, comparison of overall performance, blade-element performance, rotating stall, and separation-parameter analysis are provided.

Report presenting a study to determine the relative importance of the factors that place an inherent limitation on the minimum obtainable miss distance for a beam-rider navigation system operating in the presence of glint noise and target evasive maneuver. The factors considered include missile natural frequencies and damping ratios, missile steady-state acceleration capabilities, target evasive maneuver characteristics, and angular scintillation noise characteristics.

Report presenting a study of the performance of a modified compressor over a range of weight flows at a constant Reynolds number. The chords of the first two stages of the eight-stage axial-flow compressor had two transonic inlet stages doubled. Results regarding the long-chord-compressor performance and a comparison of long-chord and medium-chord compressors are provided.

Report presenting an investigation of the buffet characteristics of a model of an attack airplane at a variety of Mach numbers. The wing had a modified delta plan form with two NACA airfoils, a leading-edge sweep of 41.11 degrees, an aspect ratio of 2.91, and a taper ratio of 0.226. Results regarding frequency spectrum of bending moment, effect of density on root-mean-square bending moment, system damping coefficients, and buffet input force are provided.

Report presenting an investigation in the 20-foot free-spinning tunnel to determine the erect and inverted spin and recovery characteristics of a 1/28-scale dynamic model of the North American FJ-4 airplane. Results indicated that either a flat-type or a steep-type spin maybe obtained when the airplane is spinning erect. Results regarding inverted spins, loading condition, spin-recovery rocket tests, and spin-recovery parachute tests are provided.

Report presenting a method for the rapid selection of a turbine design within specified aerodynamic limits. Tables are provided with the overall design parameters and velocity-diagram variables of each design. Detailed design information is also included for ranges of blade-speed parameter and exit radius ratio.

"Theoretical rocket performance for equilibrium composition during expansion was calculated for JP-4 fuel with several fluorine-oxygen mixtures for a range of pressure ratios and oxidant-fuel ratios. The parameters included are specific impulse, combustion-chamber temperature, nozzle-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, thermal conductivity, and equilibrium gas compositions. A correlation is given for the effect of chamber pressure on several of the parameters" (p. 1).

Report presenting an investigation to determine the effects of forging temperatures and solution treatments on the engine performance of Inconel 700 buckets. The buckets were tested in a J33-9 turbojet engine at 1625 degrees F in 20-minute cycles. Testing demonstrated that the buckets are capable of operating for more than 450 hours at rated speed.

Report presenting a wind-tunnel investigation of several wingless missile configurations. Lift, drag, and pitching-moment coefficients were measured for a range of Mach numbers. Results regarding the missiles with nose controls and missiles with tail controls are provided.

Report presenting an investigation in the 16-foot transonic tunnel at a variety of Mach numbers to determine the interference effects of a hot jet exhaust on the pressure distribution of a 60 degree delta wing. Results regarding the tabulated pressure coefficients for the wing and nacelle for the complete range of test conditions are provided.

Report discussing the aerodynamic loading characteristics of a 45 degree sweptback wing with leading-edge chord extensions, including the effects of a spoiler-slot-deflector aileron. The wing section loading, wing-panel loading, and chord-extension loading are described.

Report presenting an investigation of an axial-flow compressor rotor with a 13-percent reduction in exit annulus in Freon-12 gas at a range of tip speeds. In order to analyze the results caused by the reduction, the performance of the rotor was compared to that of the same rotor with a constant annular area. Results regarding the overall performance, radial variation of performance, and blade-element performance are also provided.

Report presenting testing of a number of materials and shapes in two supersonic free jets at stagnation temperatures of up to 4,210 degrees Fahrenheit. Some testing was conducted in a supersonic chemical jet and some was conducted in a ceramic-heated air jet. Materials tested included aluminum alloy, copper, Inconel, magnesium, mild steel, molybdenum, stainless steel, titanium, alumina, zirconia, graphite, bakelite, and nylon.

Memorandum presenting two rocket-propelled models flight tested at Mach numbers from 0.8 to 1.5 to determine the effect of a fuselage indentation on the drag of a 52.5 degree sweptback-wing-body configuration with two large strut-mounted store symmetrically located above and below the fuselage. The fuselage had a symmetrical, Mach number 1.0 indentation designed to cancel the wing area normal to the plane of symmetry. Results regarding total drag and pressure drag are provided.

Report presenting an analysis of the injection of water into the jet-engine exhaust in order to suppress noise during static ground operation of jet engines. The investigation is conducted with a simple rig which pumps high-pressure water into the exhaust of an afterburning jet engine. Results regarding the overall sound-pressure levels and frequency spectra of the noise are provided.

Report presenting an investigation of the static stability and control characteristics of a canard airplane configuration without analysis for a range of Mach numbers from 0.70 to 2.22. This configuration consisted of a triangular wing and triangular canard, a low aspect ratio vertical tail, and a modified Sears-Haack body. Data are presented for various combinations of the body, canard, wing, and vertical tail at severla angles of sideslip, angles of attack, and canard deflection angles.

Report presenting the results of an investigation of the static longitudinal stability and control characteristics of a canard airplane configuration without analysis for a range of Mach numbers. The configuration had an unswept wing, an unswept canard, a low aspect ratio vertical tail, and a Sears-Haack body. Data are presented for various combinations of the canard, wing, and vertical tail for a range of angles of attack and canard deflection angles.

Report presenting the results of an investigation of the static longitudinal stability and control characteristics of a canard airplane configuration without analysis for a range of Mach numbers from 0.70 to 2.22. The configuration consisted of a triangular wing, an unswept canard, a low aspect ratio vertical tail, and a Sears-Haack body. Data are presented for various combinations of the canard, wing, and vertical tail for a range of angles of attack and canard deflection angles.