Report discussing the aerodynamic characteristics of three sets of blades over as wide a range of operating conditions as possible. One set of blades was conventional, one had blades that embodied sweep, and one was a nonswept set with thinner blade sections. The sweptback blades were found to be generally inferior to the straight blades, but the Mach numbers tested were not high enough to include speeds that might benefit from sweepback.

Report regarding the results of an investigation at high Reynolds numbers and low Mach numbers in the full-scale tunnel to determine the effect of leading-edge high-lift devices and split flaps on the maximum-lift and lateral characteristics of a rectangular wing of aspect ratio 3.4 with circular-arc airfoil section. Results regarding the maximum lift and stalling characteristics on the basic wing, effect of split-flap deflection, effect of leading-edge high-lift devices, and lateral characteristics with the flaps are provided.

Report presenting an experimental investigation to determine the porosity characteristics of perforated materials for normal and parallel flow. The results indicated that the porosity of the material is primarily governed by its open ratio, but that density has a slight effect. When the material was tested under parallel-flow conditions, the effective porosity dropped markedly as the stream velocity increased.

Report presenting an investigation to determine average outside surface heat-transfer coefficients for a cascade of symmetrical impulse turbine blades. Results regarding recovery factor, heat-transfer coefficients, effective gas temperature, turbine cascades, cylinders and streamline bodies, and application to rim-cooling theory are provided.

"The effects of several wing leading-edge camber and deflected-tip modifications on the force and moment characteristics of a 1/20-scale model of the Convair F-102 airplane have been determined at Mach numbers from 0.60 to 1.14 for angles of attack up to 14 degrees in the Langley 8-foot transonic tunnel. The effects of elevator deflections from 0 deg. to -10 deg. were also obtained for a configuration incorporating favorable leading- edge and tip modifications. Leading-edge modifications which had a small amount of constant-chord camber obtained by vertically adjusting the thickness distribution over the forward (3.9 percent of the mean aerodynamic chord) portion of the wing were ineffective in reducing the drag at lifting conditions at transonic speeds" (p. 1).

"Flight tests have been made with a P-51D airplane to determine the effect of chordwise vanes on the amplitude of tail buffeting. The tests made during abrupt pull-ups to the buffeting boundary included strain measurements on wing and tail and tuft studies over the wing. The results indicate that the vanes tested have no appreciable effect on the amplitude of tail buffeting" (p. 1).

Report presenting the results of an experimental investigation to determine the downwash in the region of the trailing vortex behind a trapezoidal-wing tip in a supersonic stream. Results regarding the downwash at spanwise stations, downwash at chordwise stations, and wake survey are provided.

Memorandum presenting a bibliography of unclassified aircraft fire literature consisting of reports from a 20-year period ending January 1, 1949. The reports are separated into the following categories: aircraft fire accidents and statistics, combustibles, ignition sources, fire protection, fire prevention, fire resistance of materials, fire detecting, fire extinguishing, and passenger protection or rescue.

Report discussing the aerodynamic effects of length-beam ratios 20 and 30 as compared to length-beam ratios from 6 to 15. There was slightly more longitudinal stability and slightly less directional stability than in the lower ratios and not much change in the minimum drag coefficient.

Memorandum presenting a discussion of inlets with a circular cross section and a central body designed for high Mach numbers. The optimum proportion between external and internal supersonic compression is discussed in relation to the external drag and the maximum pressure recovery. Results and analysis regarding the maximum pressure recovery as a function of the cowling position parameter, the effect of the cone angle parameter on the maximum pressure recovery obtained, the highest pressure recovery obtained as a function of the central-body-diameter parameter, the maximum pressure recovery as a function of Mach number, and optical observations of the flow phenomena about the inlets are provided.

Report presenting an investigation to determine the static lateral control characteristics of a supersonic aircraft configuration at Mach numbers of 1.40 and 1.59. The aileron effectiveness was about half of what was predicted by calculations, which was mainly due to flow separation in the region of the aileron. Information about other aileron characteristics and characteristics in sideslip is provided.

Report presenting low-speed testing of the Republic F-105 airplane in the pressure tunnel to determine the plane's lateral control and directional stability and control characteristics. Various combinations of components were tested, including tares, spoilers, ailerons, and wing fences.