"An investigation was conducted to determine the electric power requirements necessary for ice protection of inlet guide vanes by continuous heating and by cyclical de-icing. Data are presented to show the effect of ambient-air temperature, liquid-water content, air velocity, heat-on period, and cycle times on the power requirements for these two methods of ice protection. The results showed that for a hypothetical engine using 28 inlet guide vanes under similar icing conditions, cyclical de-icing can provide a total power saving as high as 79 percent over that required for continuous heating" (p. 1).

Report presenting measurements of elevator-stabilizer effectiveness and trim of the X-1 airplane at 40,000 feet altitude at a range of Mach numbers and normal-force coefficients.

Report presenting a rocket-powered model of the X-3 configuration flown through a range of Mach numbers to determine the response of the model to rapid deflections of the horizontal tail and its effects on lift, drag, longitudinal stability and control, and longitudinal-trim change. The model was found to remain statically and dynamically stable through the lift-coefficient and Mach number range of the test.

Report presenting an investigation of the rolling effectiveness at transonic and supersonic speeds of an inversely tapered sweptback wing with a 10-percent-thick cambered airfoil section and outboard partial-span controls made by means of rocket-propelled test vehicles.

Report presenting flight testing at high-subsonic and supersonic speeds at high Reynolds numbers to determine the zero-lift drag of a fin-stabilized body and a wing-body combination. The body was parabolic in profile, had a fineness ratio of 10, and a ratio of body frontal area to wing area to 0.306.

Effect of distributed boundary-layer suction on operating pressure ratio of a supersonic wind tunnel was investigated. Investigation was made in 3.84- by 10-inch supersonic tunnel operating at Mach number 2.0 and suction was applied in neighborhood of the normal shock to two walls of a constant-area extension of test section. A reduction of 4 percent of operating pressure ratio was attributed to improved flow conditions at subsonic-diffuser inlet. The theoretical normal shock was, in practice, replaced by a multiple-branch shock configuration across which the flow parameters changed in approximate accordance with the Rankine-Hugoniot values.

Report presenting the results of an experimental wind-tunnel investigation of the damping in pitch of two triangular wings having leading edges swept back 45 degrees are presented. The wings differed only in airfoil section. Results regarding the damping coefficients, aeroelastic effects at supersonic speeds, Reynolds number effects, and application of the results to the prediction of the dynamic behavior of full-scale aircraft are provided.

Report presenting an investigation to determine the longitudinal control characteristics of deflectable wing-tip elevators on a low-aspect-ratio, untapered, 45 degree sweptback semispan wing. The elevators had triangular and parallelogrammic plan forms and flat-plate profiles. Results include the elevator effectiveness and comparison of the elevator effectiveness of deflectable wing-tip controls and trailing-edge flap-type controls.

From Summary: "Curves are presented that show the theoretical performance of the augmentation method for various amounts of water injected and the effects of varying flight Mach number, altitude, ambient-air temperature, ambient relative humidity, compressor pressure ratio, and inlet-diffuser efficiency. Numerical examples, illustrating the use of the psychrometric chart and the Mollier diagram in calculating both compressor-inlet and compressor-outlet conditions when water is injected at the compressor inlet, are presented."

From Summary: An approximate method for determining the allowable stress-limited blade-temperature distribution is included, with brief accounts of a method for determining the maximum allowable effective gas temperatures and the cooling-air requirements. Numerical examples that illustrate the use of the various temperature-distribution equations and of the nondimensional charts are also included.

"The Navier-Stokes equations of motion and the equation of continuity are transformed so as to apply to an orthogonal curvilinear coordinate system rotating with a uniform angular velocity about an arbitrary axis in space. A usual simplification of these equations as consistent with the accepted boundary-layer theory and an integration of these equations through the boundary layer result in boundary-layer momentum-integral equations for three-dimensional flows that are applicable to either rotating or nonrotating fluid boundaries. These equations are simplified and an approximate solution in closed integral form is obtained for a generalized boundary-layer momentum-loss thickness and flow deflection at the wall in the turbulent case" (p. 1).