An analysis of the off-design performance of shock-in rotor-type supersonic blading is presented. The over-all losses are assumed divided into two groups;normal-shock losses, and external-wave losses. Throughout the range of relative entrance Mach numbers from 1.35 to starting, the largest losses can be attributed to the normal shock. An improvement in performance would be expected with a reduction of the normal-shock losses by the introduction of external compression waves.

Report presenting the effects of a low-speed wind-tunnel investigation to determine the effects of vertical-fin location and area on the static and rotary lateral stability characteristics of semitailless airplane models. Results regarding straight flow, yawing flow, and rolling flow are provided.

Report presenting an investigation in Langley tank no. 2 to determine the hydrodynamic characteristics of the Consolidated Vultee Skate 7 seaplane with twin hydro-skis suitable for use on water or snow. Results regarding the take-off stability in smooth and rough water, landing stability, spray characteristics, and resistance are provided.

Memorandum presenting a brief account of the results of theoretical and experimental investigations of the flow fields behind lifting plane and cruciform wings. Particular attention is focused on wings of low aspect ratio.

Memorandum presenting a study of the relationship between the static and dynamic properties of heat-resistant alloys at high temperatures. An auxiliary objective is to provide a better basis for evaluating the results from the various types of fatigue machines.

Report presenting a method for calculating the path of a jettisonable nose section at any speed by means of successive approximations using static aerodynamic characteristics. Conditions for consideration, including the effect of stabilizing fins, are included in the calculations.

Report presenting an investigation in the free-flight tunnel to determine the dynamic lateral stability and control characteristics of a high-aspect-ratio bomber model with self-supporting, free-floating fuel tanks attached to the wing tips. The results showed that the flight behavior of the configuration could be made satisfactory when sufficient restoring moment was supplied. Results regarding the flight behavior, rolling motions, motions of the bomber and attached tanks, and flight records for different gearing ratios are provided.

Report presenting local coefficients of convective heat transfer as measured from skin temperature along the body of an RM-10 NACA research missile, which consisted of a parabolic body of revolution. Results regarding recovery factors, adiabatic wall temperatures, Nusselts, Prandtl, and Reynolds numbers, and boundary-layer transition are provided.

Memorandum presenting testing of an experimental Custer Channel Wing airplane in the full-scale tunnel to investigate the lift characteristics of a channel-propeller combination and the flow phenomena in and about a channel wing.

Memorandum presenting data from an investigation of the effect of curved speed brakes on the drag characteristics and on the longitudinal stability and control characteristics of a scale model of the MX-1554A airplane redesigned to incorporate a circular jet nozzle. The speed brakes were tested at several deflections,gaps, and locations on the landing configuration and the clean configuration.

Memorandum presenting a wind-tunnel investigation at low speed to determine the path and motion of a scale model of the Douglas XF4D-1 escape capsule without the drogue parachute when jettisoned by jet ejection. The investigation included determination of the vertical and horizontal accelerations of the capsule. Results regarding the ejection at zero airspeed, ejection at 570 feet per second, and at 863 feet per second are provided.

Report presenting an investigation of three NACA 1-series nose inlets at subsonic and transonic speeds in the 8-foot transonic tunnel. Drag, surface-pressure, and pressure-recovery measurements and schileren photographs were obtained at zero angle of attack through a range of Mach numbers and mass-flow-ratios. Results regarding tunnel boundary interference, surface pressure distribution, external drag, and pressure recovery are provided.

Report presenting some equations that give the interference on the trailing-vortex system of a uniformly loaded finite-span wing in a circular tunnel containing partly open and partly closed walls, with special reference to symmetrical arrangements of the open and closed portions. Methods are given for extending the equations to include tunnel shapes other than circular.

From Summary: "An analytical method for calculating the aerodynamic loading on wing-tip-tank combinations in subsonic flow is developed by using a simple horseshoe vortex-image system for the case of the tank axis in the plane of the wing. An illustrative example is given in the appendix, in which wing and tip-tank loadings are calculated for three configurations. The calculated results are shown to be in good agreement with experimental data."

This paper presents the results of an induced angle-of-attack calculation using a method applicable to a propeller with arbitrary circulation distribution. Tables of induced angles of attack and section angles of attack and curves of wake-survey results are presented for the NACA 10-(3)(066)-03, 10-(3)(049)-03, 10-(3)(090)-03, 10-(5)(066)-03, and 10-(0)(066)-03 propellers. A brief description of the method of calculating propeller induced angles of attack is given.

Memorandum presenting an investigation of the leading-edge extensions, a trailing-edge extension, and a fence on the static longitudinal stability of a wing-fuselage-tail combination with a wing with 35 degrees of sweepback and an aspect ratio of 4.5. The investigation involved the use of force measurements and tuft studies on stall progression. Results regarding a model with unmodified wing, the effect of leading-edge modifications, the effects of the fence, a summary of the effects of compressibility, and some remarks on flow separation are provided.

"An investigation of the Reynolds number for transition and the skin-friction drag at zero lift of eight cone-cylinder bodies having various fineness ratios has been made at Mach numbers of 1.62, 1.93, and 2.41 over a Reynolds number range from 0.3 x 10(exp 6) to 10 x 10(exp 6). The accuracy of the skin-friction data was not sufficient to permit any general conclusions to be drawn. The Reynolds number for transition was found to be dependent upon both the tunnel stagnation pressure and Mach number" (p. 1).

Report presenting a theoretical study of certain anomalies in the behavior of a ram-jet engine engine tip-mounted on a rotating helicopter blade that appears to be related to centrifugal effects distorting the fuel-spray pattern. Results regarding the cases calculated, results of the calculations, particle-path distortion, and limiting direction of particle paths are provided.

Report presenting an experimental wing-flutter investigation in the transonic blowdown tunnel, which is equipped with a slotted test section, in order to determine the correlation between transonic-wind-tunnel and free-fall flight flutter results. Very good agreement was observed between wind tunnel and flight flutter test results, which showed the feasibility of conducting flutter tests in transonic wind tunnels with slotted test sections.

Memorandum presenting an inlet-type axial-flow compressor rotor with a hub-tip diameter ratio of 0.4 at the rotor leading edge, which was designed, fabricated, and experimentally investigated. The results of the investigation indicated that stages with inlet hub-tip ratios as low as 0.4 can be designed within known practical aerodynamic specifications to produce satisfactory values of stage pressure ratio and efficiency at high specific weight flows.

Report presenting an investigation of the effects of slot width, depth, shape, and spacing on the center-line pressure distribution in rectangular tunnels of constant cross section with several height-to-width ratios. Results are presented in the form of center-line static-pressure distributions and calculated static-pressure and angle-of-flow distributions along the slotted boundary.

Report presenting an investigation of an ogive-cylinder nacelle in various spanwise locations in a vertically symmetric position on a small-size 45 degree sweptback wing of aspect ratio 6 with and without a fuselage. Results regarding the drag characteristics, lift-drag ratios, lift characteristics, pitch characteristics, and lateral center of pressure are provided.

Report presenting an investigation of the power requirements for slotted tunnels and methods of reducing these requirements. All pressure losses reported occurred in the region between the upstream end of the entrance ball and the entrance to the diffuser and in handling air taken in through the slotted wall. Results regarding auxiliary pumping and ejector pumping are provided.

Memorandum presenting an investigation of operation of a single-spool turbojet engine with variable exhaust-nozzle area over a range of altitudes at a constant flight Mach number. Data was obtained by subjecting the engine to approximate step disturbances in the independent variables, and the information necessary to effect a linearized first-order description of the engine's dynamic operation was obtained. Results regarding rotational speed, compressor-discharge pressure, turbine-discharge pressure, net thrust, and turbine-discharge temperature are provided.