Report presenting an investigation of a model of the Kingfisher XAUM-2 flying torpedo to determine the pressure recoveries within the jet engine nacelle and to determine the effects of several changes in model configuration on the aerodynamic characteristics of the model. The effectiveness of elevons and tabs as control devices was also investigated.

Report presenting airspeed and altitude data for nonscheduled cargo operations of a Douglas DC-4 airplane between Seattle, Washington and Alaska during February and March of 1947 to determine the probability of reaching or exceeding given values of airspeed and Mach number. The total probability of exceeding a placard never-exceed speed of 266 mph depends primarily on exceeding the speed in descent. The probability was found to be about once in 100 hours of descent or once in 1000 hours of general flying time.

Report presenting an investigation of a model of a tailless airplane in a high speed tunnel at a range of Mach numbers. Results are compared to those obtained from a sting-mounted model tested in the same tunnel and a semispan model tested with the wing-flow method. Information regarding basic aerodynamic characteristics, spoiler controls, lift characteristics, drag characteristics, pitching moment at zero lift, and stability and control is provided.

Report discussing tests of a scale model of the XB-51 airplane to determine its force, stability, and control characteristics in pitch and yaw at various Mach numbers. The effects of the dive breaks and the bomb bay are also described.

Report presenting a wind-tunnel investigation of a semispan delta wing with the leading-edge swept back 60 degrees. A half-delta control surface was used and testing was performed with and without fences. Results regarding the rolling effectiveness, wing characteristics, and control-surface characteristics are provided.

Memorandum presenting an analysis of selected experimental pressure-distribution data at transonic speeds for the purpose of deriving an empirical method which may be used for estimating the trailing-edge loads and bending moments at the design stage. The trailing-edge normal-force and bending-moment coefficients calculated by the derived method follow the general trend of the experimental data and appear to be a guide where specifically applicable chordwise pressure-distribution data at transonic speeds are not available.

Report presenting an investigation to determine the effects of a vertical tail with the leading edge swept back 63 degrees on the aerodynamic characteristics of a wing-fuselage combination with a wing with the leading edge swept back 63 degrees. The aerodynamic characteristics in sideslip with and without the vertical tail are also presented. Results regarding the directional stability, rudder effectiveness, and rudder hinge moments are described.

Report presenting an experimental study of the pressure fluctuations at the combustion-chamber inlets of a ramjet operating a Mach number of 1.92 in the supersonic tunnel. Results are presented for two burner configurations of different operating characteristics to indicate trends in pressure magnitude, frequency, and wave form. Results regarding the perforated conical flame holder, regenerative-type burner, and diffuser total-pressure recovery are provided.

Report discussing flow surveys made of several nozzles using two 2-dimensional steps at Mach number 6.98. Results regarding wall-pressure surveys, disturbance patterns in expansion, total-pressure survey, temperature recovery, and general nozzle characteristics are provided.

Report presenting rocket-powered flight tests from high subsonic to supersonic speeds and at high Reynolds numbers to determine the zero-lift drag of a transonic wing-body and body-alone configuration. The configuration tested featured a wing of 45 degree sweepback, aspect ratio 4, taper ratio 0.6, and an NACA 65A006 airfoil section, and a body of fineness ratio of 10 and a frontal area equal to 6.06 percent of the wing-plan-form area.

Report presenting an investigation to determine the aerodynamic characteristics in sideslip of a triangular wing of aspect ratio 2.04 in combination with a body of fineness ratio 12.5 and a vertical tail surface. The body combined with the triangular plan-form wing caused no significant changes in the lift characteristics of the wing and only a 1-percent decrease in the static margin. Results regarding the longitudinal characteristics, lateral and directional characteristics, and estimation of tail and rudder effectiveness are provided.

Report presenting a method for the preparation and purification of the intermetallic molybdenum desilicide was developed and its properties were determined. Chemical properties were found to be highly inert, unattacked by boiling hydrochloric acid, sulfuric acid, or aqueous sodium hydroxide, slightly attacked by nitric acid, and dissolved by molten sodium hydroxide. Other mechanical properties of the material were also provided.

Report presenting an investigation to determine the lift, drag, and pitching-moment characteristics of the NACA 0010 and 0010-64 airfoil sections at Mach numbers up to 0.91 and for a range of Reynolds numbers.

Report presenting an investigation to determine the possibility of delaying at moderate or large lift coefficients the onset of the abrupt supercritical drag rise of an airfoil section by the use of camber. Results indicated that the addition of camber to the NACA 0010 airfoil leads to significant improvements in the drag characteristics at moderately supercritical speeds .

Experimental study to determine the vibrational modes of several hollow turbine blades and a solid turbine blade of similar aerodynamic design. Results regarding the significance of nodal patterns, vibrational modes of six blade types, and the probability of excitation in some of the blades are provided.

From Introduction: "This paper presents the results of the investigation of the wing-alone and of the wing-fuselage configuration employing a wing with an unswept quarter-chord line, aspect ratio 4, taper ratio 0.6, and an NACA 65A006 airfoil section parallel to the air stream. The results of closely related sweptback-wing investigations, which are part of the present transonic programs, are presented in references 1 to 3."

Report presenting a wind-tunnel investigation of a semispan pointed wing of aspect ratio 1.7 with 60 degree leading-edge sweepback and 30 degree trailing-edge sweepforward with a control surface. The purpose of the investigation was to determine the effectiveness of flap-type controls at transonic and supersonic speeds. Results regarding the wing characteristics and control-surface characteristics are provided.

Report presenting an altitude-chamber investigation to determine the altitude performance characteristics of the British Rolls-Royce Nene II turbojet engine with an 18.41-inch-diameter jet nozzles. Testing occurred at a range of simulated altitudes and ram-pressure ratios. Results regarding the simulated flight performance, generalized performance, and effect of jet-nozzle area on performance are provided.

"An additional series of high-speed wind-tunnel tests of a modified 0.17-scale model of the McDonnell XF2H-1 airplane was conducted to evaluate the effects of a reduction in the thickness-to-chord ratios of the tail planes, the displacement of the horizontal tail relative to the vertical tail, and the extension of the trailing edge of the wing. Two tail-intersection fairings designed to improve the flow at the tail were also tested. The pitching-moment characteristics of the model were improved slightly by the use of the thinner tail sections" (p. 1).