Memorandum presenting a technique for predicting the influence of body vortices and the wing shock-expansion field on the pitch-up characteristics of supersonic airplanes to supplement the calculative methods for wing vortices which are well known. The method is applied to the prediction of the pitch-up characteristics of four airplanes with high tails, of which one serves as a calculative example.

Data are presented showing compliance of C-54D with Army and Navy lateral and directional stability and control specifications. The airplane met requirements except for the rolling effectiveness pb/2V, the aileron forces in rolling, and the rudder forces in the asymmetric power conditions which were marginal. Also, the results of special tests concerning asymmetric power, asymmetric loading, and pitch due to yaw requested by the Airplane Handling Qualities Subcommittee of the Air Transport Association are presented.

Report discusses the results of an analysis of available data to determine what measured characteristics are significant in defining satisfactory flying qualities, what characteristics are reasonable to require of an airplane, and what influence the various design features have on the observed flying qualities.

Experimental frequency-response characteristics of engine speed for a typical turbine-propeller engine are presented. These data were obtained by subjecting the engine to sinusoidal variations of fuel flow and propeller-blade-angle inputs. Correlation is made between these experimental data and analytical frequency-response characteristics obtained from a linear differential equation derived from steady-state torque-speed relations.

From Summary: "Long-range hypervelocity vehicles are studied in terms of their motion in powered flight, and their motion and aerodynamic heating in unpowered flight. Powered flight is analyzed for an idealized propulsion system which rather closely approaches present-day rocket motors. Unpowered flight is characterized by a return to earth along a ballistic, skip, or glide trajectory. Only those trajectories are treated which yield the maximum range for a given velocity at the end of powered flight. Aerodynamic heating is treated in a manner similar to that employed previously by the senior authors is studying ballistic missiles (NACA RM A53D28), with the exception that radiant as well as convective heat transfer is considered in connection with glide and skip vehicles."

Tests were conducted to find the effects of compressibility on the longitudinal stability and control of a 1/7-scale semispan model of the Northrop YB-49 airplane. Lift, drag, pitching moment, and elevon hinge moments were measured and are presented in graphical form. The results show that, due to a loss of lift on the outboard portion of the wing, the longitudinal static stability decreased rapidly as the Mach numbers increased above 0.735 the model experienced a climbing moment at positive lift coefficients. Also, a longitudinal-control effectiveness began to decrease at a Mach number of about 0.725.

Results obtained from gust and draft velocity measurements within thunderstorms for the period August 17, 1946 to August 19, 1946 at Orlando, Florida are presented herein. These data are summarized in tables I and II and are of the type presented in reference 1 for previous flights. Inspection of photo-observer records taken on the present flights indicated that mo ambient-air temperature data were obtained.

"Investigations were conducted of a 12 degree 21-inch conical diffuser of 2:1 area ratio to determine the interrelation of boundary layer growth and performance characteristics. Surveys were made of inlet and exit from, longitudinal static pressures were recorded, and velocity profiles were obtained through an inlet Reynolds number range, determined from mass flows and based on inlet diameter of 1.45 x 10(exp 6) to 7.45 x 10(exp 6) and a Mach number range of 0.11 to approximately choking. These investigations were made to two thicknesses of inlet boundary layer" (p. 1).

Report presenting wind-tunnel flutter testing at a range of Mach numbers conducted on a swept-wing towed airplane model equipped with an autopilot system. Results regarding the towed model tests, fixed-root tests, and a comparison between the calculated and experimental flutter characteristics are provided.

Report presenting time histories of rolling and yawing moments on inclined bodies of revolution with vertical-tail surfaces at several Mach numbers and Reynolds numbers. Three ogival-nose bodies with three overall fineness ratios and a conical-nosed body with a fineness ratio of 12.0 were tested. Results regarding the visual-flow studies, rolling- and yawing-moment measurements, and pressure measurements are provided.

"An investigation of a single-annulus turbojet combustor with slot-type air admission was conducted to demonstrate the application of certain design principles to the control of outlet-gas temperature distributions. Comparisons of performance of a one-quarter-annulus combustor (duct-type installation) and a full-annulus combustor (obtained in a full-scale turbojet engine) are presented to indicate the applicability of results obtained from combustion studies conducted in duct-type installations. A reasonable correlation existed between the performance of the one-quarter-annulus and full-annulus combustors except for temperature distribution" (p. 1).

Report presenting an investigation in the high-speed tunnel to determine the hinge-moment, lift, and pitching-moment characteristics of a 4-percent-thick 60 degree delta wing with a trailing-edge flap-type control. The purpose of this investigation is to determine the ideal aerodynamic balance of a large part of the control force in order to make aircraft easier to control in the event of power failure.

Report presenting a series of flight tests to determine the flying qualities of a man standing on a platform supported by a teetering rotor. The machine was tested with a free-teetering rotor, a spring-restrained rotor, and a rotor and foot platform isolated from the framework by rubber connections. Results of the different configurations during indoor and outdoor flights are presented.

Report presenting a low-speed investigation of the aerodynamic and control characteristics of a 3-percent-thick, 60 degree delta-wing-fuselage configuration in the full-scale tunnel to obtain data at large scale on control configurations of general interest and to determine whether significant Reynolds number effects existed for a very thin wing subject to leading-edge vortex-type flow. Aerodynamic forces, moments, and hinge moments were obtained for several types of controls and flap deflections.

Report presenting a determination of aerodynamic lift and moment flutter derivatives at high subsonic speeds for a series of two-dimensional airfoils varying in thickness and thickness distribution. An evaluation of the results indicated that wing profile and angle of attack have major effects on flutter derivatives at speeds exceeding the Mach number for steady-state lift divergence. Results regarding lift and moment are provided.

Report presenting an investigation of the design and tests of a transonic inlet rotor with emphasis placed on increasing the design specific weight flow while maintaining reasonably high pressure ratio and efficiency. Information regarding peak efficiency and how to best achieve it through design is provided.

"The wave drag, based on linearized theory, of any lifting or non-lifting planar or nonplanar object in a steady supersonic flow is shown to be identical at a fixed Mach number to the average wave drag of a series of equivalent bodies of revolution. The streamwise gradient of area, measured normal to the free stream, at a section of each of these equivalent bodies of revolution is given by the sum of two quantities: 1. the streamwise gradient of area, measured in parallel oblique planes tangent to the Mach cones, along the given object. 2. A term proportional to the resultant force on the object measured in the same oblique planes" (p. 1).

Report presenting a wind-tunnel investigation to determine the effects of various wing-fence arrangements on the longitudinal characteristics of several wing-fuselage and wing-fuselage-tail combinations with sweptback wings with NACA four-digit thickness distributions. Testing occurred with wings of several degrees of sweepback and a horizontal tail at several tail heights. Results regarding fence development, wing-fuselage combinations, and wing-fuselage-tail combinations are provided.

Report presenting some accompanying tables and bibliography for experimental aerodynamic studies in the field of wing controls during the period between January 1946 and February 1955. The tables are grouped according to the following major classifications: trailing-edge flap controls, leading-edge flap controls, and spoiler controls.

From Introduction: "An apparatus that gives a quick and an accurate measurement of the rate of discharge has been has been designed by the NACA and is described in this report."

"The extension to a compressible fluid of Lagally's theorem on the moment on a body in an incompressible fluid and Poggi's method of treating the flow of compressible fluids are employed for the determination of the effect of compressibility on the moment of an arbitrary body. Only the case of the two-dimensional subsonic flow of an ideal compressible fluid is considered. As examples of the application of the general theory, two well-known systems of profiles are treated; namely the elliptic profile and the symmetrical Joukowski profiles with sharp trailing edges" (p. 581).

Report presenting some of the concepts and applications underlying the basic arrangement of airplane configurations with tail surfaces outboard of the wing tips. The arrangement was created to be consistent with good supersonic performance characteristics and to avoid some of the stability and trim-drag problems seen with other supersonic configurations. Results regarding stability and control characteristics, lift and drag characteristics, and an analytical study of effects of some design variables are provided.

From Introduction: "In order to obtain some insight into the relative merits of canard and outboard-tail control systems at supersonic speeds, a preliminary investigation of a generalized canard and outboard-tail model has been conducted in the Langley 4- by 4-foot supersonic pressure tunnel at a Mach number of 2.01 and the results are presented herein."

Report presenting an investigation of a rocket-powered model to study the heat transfer to wing leading edges in the vicinity of their juncture with a cylindrical body. Information about heat-transfer measurements, average heat transfer on cylindrical portions of leading edges, and local heat transfer is provided.