Report presenting an investigation of an NACA 1-80-100 nose inlet fitted alternately with an elliptical, a parabolic, a 14 degree-inch conical, and a 22 degree-inch conical central body at subsonic and transonic speeds in the 8-foot transonic tunnel. Drag, surface-pressure, and pressure-recovery measurements were obtained at 0 degrees angle of attack through a range of Mach numbers. Results regarding tunnel boundary interference, surface-pressure distribution, external drag, pressure recovery, and propulsive thrust comparison are provided.

Report presenting an investigation in the transonic tunnel to determine the dynamic and static stability characteristics of the Mark-6, Mark-4, TX-13, and Mark-5 special weapons and the effects of modifications of them for a range of Mach numbers.

Report presenting a concept for interrelating the wave drag of wing-body combinations at moderate supersonic speeds with axial distributions of cross-sectional area has been developed. Details of preliminary experiments meant to test the concept are also provided.

"Convective heat-transfer coefficients in dry air were obtained for an ellipsoidal spinner of 30-inch maximum diameter for both stationary and rotating operation over a range of conditions including airspeeds up to 275 miles per hour, rotational speeds up to 1200 rpm, and angles of attack of zero and 4 degrees. The results are presented in terms of Nusselt numbers, Reynolds numbers, and convective heat-transfer coefficients. The studies included both uniform heating densities over the spinner and uniform surface temperatures" (p. 1).

Memorandum presenting techniques for the measurement of the energy spectrum of flow fluctuations in both axial and lateral flow directions. A simple spectrum analysis is presented by which quantitative distinction may be made between turbulence and the flow disturbances associated with sound waves in ducts. Results regarding the measurement and analysis of turbulent-flow fields containing random and periodic flow fluctuations, effect of random sound disturbances on turbulence spectrum, and effect of combustion on combustor approach-stream spectrum are provided.

Memorandum presenting an investigation of the starting characteristics of mixed oxides of nitrogen - liquid ammonia rocket engines with light metal additives in the ammonia flow line for ignition. The oxidant consisted of 70 percent by weight nitrogen tetroxide and 30 percent nitric oxide. Results regarding the ignition experiments with 100-pound-thrust engine, 1000-pound-thrust engine experiments, and low-temperature experiments are provided.

From Introduction: "As part of a comprehensive investigation of the J40 turbojet engine conducted at the NACA Lewis altitude wind tunnel, the steady-state engine performance of the prototype J40-WE-8 turbojet engine without afterburner was obtained and is presented herein. A basic redesign of the compressor and other modifications in the compressor and the combustor were incorporated in the XJ40-WE-6 turbojet engine (references 2 and 3). In this report the modified engine is designated "the prototype J40-WE-8 without afterburner."

The performance of a turbojet engine with a two-stage turbine, an adjustable first-stage turbine stator, and a variable-area exhaust nozzle was investigated at selected constant engine speeds and two simulated flight conditions. For the particular component characteristics of the engine investigated, little improvement in thrust levels of interest by use of an adjustable rather than an optimum fixed first-stage turbine stator.

Report presenting the results of strength tests on thick-skin wing structures. Some of the factors that were found to have influence on the buckling behavior and strength are shown with data and the conditions under which a combination of multiweb and multipost construction may be used are discussed. Results regarding circular-arc airfoils, multiweb beams, and multipost stiffened beams are provided.

From Summary: "Pressure distributions and force characteristics have been determined for a body of revolution consisting of a fineness ratio 5.75, circular-arc, ogival nose tangent to a cylindrical afterbody for an angle-of-attack range of 0 degrees to 35.5 degrees. The free-stream Mach number was 1.98 and the free-stream Reynolds number was approximately 0.5 x 10 sup 6, based on body diameter. Comparison of the theoretical and experimental pressure distributions shows that for zero lift, either slender-body theory or higher-order theories yield results which are in good agreement with experiment."

Memorandum compiling summaries from NACA reports on fuel that were published between July 1945 and 1952. The summaries are intended to be detailed enough to eliminate the need to obtain the complete report.

The variation of the intensity of buffeting experienced throughout the operational region of the semitailless Northrop X-4 airplane and the values of maximum and peak normal-force coefficients in the Mach number range from 0.42 to 0.92 have been determined. The results are compared with data obtained with the swept-wing Douglas D-558-II airplane.

Report presenting an investigation in the transonic tunnel to determine the aerodynamic characteristics of a wing-fuselage combination with a 45 degree sweptback wing with NACA 65A006 airfoil sections, an aspect ratio of 4, taper ratio of 0.6, and incorporating outboard leading-edge slats. Results lift characteristics, influence of slats on wing pressure distribution, drag characteristics, lift-drag ratio characteristics, and pitching-moment characteristics are provided.

Report presenting an investigation to determine the effects on lift, drag, and pitching moment of a reduction of the thickness ratio of a triangular wing at a range of Mach numbers and Reynolds numbers. Removing the outer 24.9 percent of the span of a wing was also explored.

Report presenting a flight investigation of the aerodynamic loads of a partial-span extended leading-edge slat on the 35-degree sweptback wing of the Douglas D-558-II research airplane. The slat normal-force coefficient was found to increase with airplane normal-force coefficient until peak slat normal-force-coefficient was reached at approximately 2.2 to 2.4.

Report presenting an investigation of a model of the Convair MX-1554 airplane in the 4- by 4-foot supersonic pressure tunnel to evaluate the effects of extending the length of the fuselage afterbody and to provide longitudinal and lateral stability and control data. Results indicated that extension of the fuselage afterbody length caused little change in the minimum longitudinal force coefficient and drag due to lift.

Report presenting a Bendix-Friez Aerovane Anenometer oscillated in the streamwise direction at several frequencies for each of several low wind-tunnel airspeeds. Records of the displacement of the anenometer and velocity indicated by the instrument during oscillation are provided. The over-registration of this anenometer was found to be much smaller than predicted by theory.

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.

Report presenting the development and use of a chart for use in estimating the combustion efficiency of a turbojet at altitude flight conditions. The combustion efficiency chart is based on the assumption that the corrected gas flows, pressures, and temperatures of engine components other than the combustor are unique functions of corrected engine speed.

Report presenting an investigation to determine the lateral control characteristics of constant-percent-chord trailing-edge elevons on a tailless wing-body combination with a pointed wing of aspect ratio 2. The effectiveness of inset tabs in reducing the elevon hinge moment was also determined. Results include the lift, drag, pitching moment, rolling moment, elevon hinge moment, tab moment, elevon load, and center of pressure of elevon load.

Report presenting an investigation in the transonic tunnel to determine the influence of a change in body shape on the effects of twist and camber. Twist and camber were found to greatly improve the maximum lift-drag ratios of the wing-modified fuselage configuration through the speed range, but reduced the ratios for a wing-curved fuselage configuration. Results regarding basic aerodynamic data are also provided.

Report presenting formulas for fifteen elastic constants associated with bending, stretching, twisting, and shearing of plates with closely spaced integral ribbing in a variety of configurations and proportions. Four coefficients are provided for each rib and the experimental means of determining them are described.

Report presenting an investigation of the feasibility of modifying the transient portion of the stick force in abrupt maneuvers in order to eliminate inadvertent normal-acceleration overshoots. The modification consists of additional stick force proportional to a quantity which leads the normal acceleration. The characteristics introduced by the inclusion of the force were considered to be very desirable by pilots.

Report presenting an experimental investigation performed to determine the effect on base and forebody pressures of using a sting modified with varying length splitter plates and fins instead of a conventional sting to support a cone-cylinder body of revolution.