Report presenting an investigation using the NACA wing-flow method to determine the longitudinal stability and control characteristics at transonic speeds of a semispan airplane with a 45 degree sweptback wing and tail. Measurements of the lift and angle of attack for trim were made for several stabilizer and elevator settings. Testing was also performed to investigate the effects of transition wires mounted on the wing and tail, the effect of increasing the boundary-layer thickness on the test surface, and the effectiveness of a wing flap with a sweepback of 45 degrees.

Memorandum presenting some pressure-distribution and boundary-layer measurements made in flight in the presence of shock on two modifications of the local contour of the wings of a high-speed airplane. Results regarding the pressure distribution, boundary-layer surveys, and effects on test airplane are provided.

Report presenting several rectangular and tapered wing configurations with leading-edge and trailing-edge ailerons tested as part of a general investigation of an aerodynamic control at supersonic speeds. Results indicated that the use of the leading-edge aileron alone was ineffective or caused negative control until a high Mach number was attained. Results for the untapered configurations, tapered configurations, and drag measurements are provided.

An X-ray - diffraction analysis of residual surface stresses after plastic strain was introduced in a parallel-sided 3S-O aluminum disk with a central hole by two types of centrifugal overspeed is reported. Both tangential and radial stresses were generally tensile with large local variations near the hole where surface stresses may have been partly superficial. These stresses were both tensile and compressive dependent on the distance from the disk center when mass compression was effected near the hole.

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