Report presenting turbulent-heat-transfer measurements obtained through the use of an axially symmetric annular nozzle consisting of an inner shaped center body and an outer cylindrical sleeve. Results regarding the wall temperatures, variation of local Nusselt number with Reynolds number, density, velocity, and local temperature-recovery factor are provided.

Note presenting a theoretical analysis of laminar separation in compressible flow over a transpiration-cooled surface maintained at a uniform wall temperature. The method should be sufficiently accurate for most practical purposes. To show the effects of the parameters on the separation point, a numerical example is worked out in detail.

Report presenting an investigation of the effects of plan-form taper on the aerodynamic characteristics of a series of wings with various tapers, aspect ratios, and thicknesses in the 16-foot high-speed wind tunnel utilizing the transonic-bump method. Testing occurred over a range of Mach and Reynolds numbers. Lift, drag, and pitching-moment data are presented for wings with a variety of aspect ratios, taper ratios, and thickness-to-chord ratios.

Note presenting a study of the gliding of one metal crystal with respect to another parallel to their mutual grain boundary in pure aluminum bicrystals during isothermal creep at a range of temperatures and static stresses. Results regarding induction period, cyclic motion, influence of time on rate of grain-boundary displacement, influence of temperature on rate of grain-boundary displacement, influence of stress on rate of grain-boundary displacement, influence of relative crystal orientations on rate of grain-boundary displacement, and microstructural observations are provided.

Report presenting experimental heat-transfer data for the turbulent flow of fluids through stationary vertical tubes with both small and large length-to-diameter ratios compared for the case where the acceleration of gravity is opposite in direction to the mean velocity in the tube and where the heat flows from the tube wall into the fluid.

Report presenting a summary of exact solutions of the laminar-boundary-layer equations for wedge-type flow, which are useful in estimating heat transfer to arbitrarily shaped bodies like turbine blades. The solutions are determined for small Mach numbers and for two cases: small temperature changes in the boundary layer along a constant- and variable-temperature wall, and large temperature changes in the boundary layer along a constant-temperature wall. Results regarding boundary-layer profiles and friction and heat transfer are provided.

Report presenting information about the distance required to decelerate a high-speed jet transport from the normal operating speed to the design speed for maximum gust intensity (rough-air speed). The use of aerodynamic brakes, thrust reversal, or a climbing maneuver can help reduce the distance required to reach the rough-air speed, but deceleration distance is likely to be considerably greater for jet transports than present-day piston-engine transports.

From Summary: "Some recent contributions to the problem of shock-induced separation of the boundary layer are examined, and additional analytical and experimental results are presented. The probable ranges of pressure rises and flow deflections associated with separation are indicated. Consideration is given to the effects of Mach number, adverse pressure gradient, and Reynolds number for laminar boundary layers and to the effects of Mach number, Reynolds number, and ratio of specific heats for turbulent boundary layers."

Report presenting values of total-drag coefficient for two fin-stabilized, blunt-nose bodies of revolution in free flight at a range of Mach numbers. Within the accuracy and range of the present tests, rounding off the sharp noses produced no increase in the total drag of either configuration.

Report presenting an experimental investigation at low speed to determine the effects of fuselage cross section on the static longitudinal and lateral stability characteristics of midwing airplane models with 0 and 45 degrees sweptback surfaces. The results indicated that the main effect of fuselage cross section on the longitudinal and directional stability characteristics of the modles at low angles of attack are caused by the direction contributions of the fuselage.

Note presenting an investigation of the roll automatic pilot system, which operates on a nonlinear principle whereby a dead spot is incorporated in the servomotor feedback linkage to obtain an effective rate signal by reducing the phase lag of the servomotor. Results regarding some preliminary considerations, autopilot amplitude and phase response, and roll-simulator tests are provided.