"Flight tests were made to determine the total-pressure recovery of a split-wing ram-jet inlet with a fixed area exit 20 percent larger than the inlet throat over a Mach number range from 1.4 to 3.16. Total-pressure-recovery measurements at the diffuser exist station indicated abrupt pressure changes in the total-pressure profile throughout the Mach number range. Comparisons of average total-pressure recovery with the theoretical total-pressure recovery showed good agreement" (p. 1).

Memorandum presenting an investigation in the 7- by 10-foot tunnel to determine the effect of wing-root leading-edge- and scoop-type jet-engine air-inlet configurations on the static lateral stability characteristics of a scale model of the MX-1764 airplane. The addition of the inlet configurations to the model generally had only small effects on the lateral stability.

"An analysis is made of the structural response to gusts of an airplane having the degrees of freedom of vertical motion and wing bending flexibility and basic parameters are established. A convenient and accurate numerical solution of the response equations is developed for the case of discrete-gust encounter, an exact solution is made for the simpler case of continuous-sinusoidal-gust encounter, and the procedure is outlined for treating the more realistic condition of continuous random atmospheric turbulence, based on the methods of generalized harmonic analysis. Correlation studies between flight and calculated results are then given to evaluate the influence of wing bending flexibility on the structural response to gusts of two twin-engine transports and one four-engine bomber" (p. 1).

"An investigation is being conducted to determine the dynamic stability and control characteristics of a 0.13-scale flying model of Convair XFY-1 vertically rising airplane. This paper presents the results of flight and force tests to determine the stability and control characteristics of the model in vertical descent and landings in still air. The tests indicated that landings, including vertical descent from altitudes representing up to 400 feet for the full-scale airplane and at rates of descent up to 15 or 20 feet per second (full scale), can be performed satisfactorily" (p. 1).

Memorandum presenting pulse techniques applied to strain gages for increasing the output level and extending the usable range. Bonded and unbonded strain gages which normally operate with exciting potentials between 3.5 and 14 volts operated satisfactorily with 200-volt pulses of 1-microsecond duration and a repetition rate of 350 per second. Results regarding maximum allowable voltages, effective pulse duration, sensitivity, minimum readable signal, effects of cable capacitance and inductance, sensitivity to external noise, and linearity are provided.

From Introduction: "The purpose of this report is to present the results of the analytical investigation of the turbine of reference 1 to indicate the extent to which the various turbine losses affect the turbine efficiency over the range of performance."

Report presenting an investigation of the proper means of coordinating the lift-acceleration commands and the roll-attitude commands to the autopilot in order to minimize transient racking errors encountered during bomber evasion. Results regarding the pull-up maneuver, horizontal turning maneuvers, the split S vertical plane maneuver, diving turn maneuver, other considerations involved in rolling maneuvers, and maximum rates of roll, control motion, and tracking-line motion are provided.

A survey of experimental data at supersonic speed indicated that shock-induced separation of a turbulent boundary layer will result for Mach numbers of approximately 1.33 or greater when a theoretical stream static-pressure-rise ratio of approximately 1.89 occurs across a shock interacting with the boundary layer. The significance of this tentative criterion for turbulent boundary-layer separation is discussed with respect to the design of supersonic diffusers.

"Slurry fuels containing extremely small particles of magnesium were prepared by concentrating the dilute slurry product resulting from the shock-cooling of magnesium metal vapors with a liquid hydrocarbon spray. A complete description of the equipment and procedure used in preparing the fuel is given. Ninety-five percent by weight of the solid particles formed by this process passed through a 100-mesh screen. The particle-size distribution of the screened fraction of one run, as determined by sedimentation analysis, indicated that 73 percent by weight of the metal particles were finer than 2 microns in equivalent spherical diameter" (p. 1).

Report presenting an experimental investigation to determine the effect of thickness and of thickness distribution on the fluctuations of normal-force and pitching-moment coefficients of airfoils. Seven symmetrical airfoils were tested. Two types of pressure pulsations were noted in the study: pulsations from an intermittent build-up and dropping of the pressure peak near the leading edge and pulsations attributable to shock-wave motion and unsteady air flow following the shock wave.

Report presenting preliminary drag data obtained for the XF-92A delta wing airplane during demonstration tests after it had been modified to use the J33-A-29 turbojet engine. Drag data, lift coefficients, and lift-curve slopes are provided.

From Introduction: "Because of the lack of data on compressor characteristics at 130 or 145 percent of design equivalent rotational speed, several simplifying assumptions were made regarding the compressor characteristics during operation at equivalent rotational speeds above the design value (hereinafter called "compressor overspeeding"). In addition to results based on these assumptions, the effect of deviation from these assumptions is discussed."

Report presenting flight tests to determine the total-pressure recovery of a split-wing ram-jet inlet with a fixed area exit 20 percent larger than the inlet throat over a range of Mach numbers. Total-pressure-recovery measurements at the diffuser exit station indicated abrupt pressure changes in the total-pressure profile throughout the Mach number range.

Report presenting a scale model of the Convair XF2Y-1 airplane with a solid-fuel rocket motor designed to simulate full-scale turbojet engine characteristics with full afterburning at a Mach number 1.2 and an altitude of 35,000 feet in free flight at a maximum Mach number of 1.45. Results regarding stability characteristics, trim characteristics, and the effect of rocket exhaust over the beaches are provided.

Report presenting the ignition delays of propane-oxygen-nitrogen mixtures as a function of temperature and composition in a flow system. Results regarding the effect of apparatus parameters, effect of propane concentration, effect of oxygen concentration, effect of temperature, and interpretation in terms of slow reaction kinetics are provided.

Memorandum presenting an investigation of the effect of the addition of approximately 6 percent nickel, cobalt, or platinum on some properties of molybdenum disilicide. These additions resulted in appreciably lowering the modulus-of-rupture strength from that of unalloyed molybdenum disilicide. Results regarding density and particle-size analysis, chemical analysis of bars, metallographic and x-ray analysis, density and resistivity, modulus-of-rupture strengths, thermal shock tests, and oxidation resistance are provided.

Report presenting free-falling recoverable-model tests at transonic speeds on a model with a low-aspect-ratio thin unswept wing and a 45 degree swept tail in the chord plane of the wing. Static- and dynamic-stability data and load-distribution data were obtained at a range of angles of attack. Results regarding lift, drag, static longitudinal stability, dynamic longitudinal stability, horizontal-tail effectiveness, loading distribution over the fuselage, and buffet boundary are provided.

Report presenting a flight investigation of the 35 degree swept-wing D-558-II rocket-powered research airplane in the transonic and supersonic speed ranges. Lift and drag values obtained in exploratory flights of the basic configuration are presented.

Report presenting an investigation in the 300 mph 7- by 10-foot tunnel to determine the effect of wing-root leading-edge- and scoop-type jet-engine air-inlet configurations on the static lateral stability characteristics of a scale model of the MX-1764 airplane. The inlet configurations generally had only small effects on the lateral stability.

Report presenting an investigation of a silicone-diester blend (SD-17) in various bench studies and in a turbopropeller engine to determine its suitability as a lubricant for aircraft engines. The performance of the fluid was satisfactory during more than 17 hours of operation in a T-38 engine with power levels from 1745 to 2400 horsepower. Results regarding bench studies and turbopropeller engine study are provided.

From Summary: "Free-flight tests have been conducted with small equivalent bodies of revolution representing different versions of the Douglas XF4D-1 airplane to determine the reduction in drag that would result from various modifications to the airplane. Results indicated that, at Mach numbers greater than 1, considerable reduction in drag would result from a thinner wing and tail, a reduction in wing-fillet thickness, and modified forward and rearward fuselage lines."

Report presenting an investigation of the effect of body indentation on the aerodynamic characteristics of an M-plan-form-wing-body combination for a variety of angles of attack and Mach numbers. The wing was tested on a plain body and a body with an indentation that was 65 percent of that required for a Mach number of 1.0. Results regarding drag characteristics, lift characteristics, pitching-moment characteristics, and estimated results are provided.

"A theoretical method is presented for calculating the flow field about wing-body combinations employing bodies deviating only slightly in shape from a circular cylinder. The method is applied to the calculation of the pressure field acting between a circular cylindrical body and a rectangular wing. The case of zero body angle of attack and variable wing incidence is considered as well as the case of zero wing incidence and variable body angle of attack" (p. 1299).

Experimental data of various investigators of liquid-metal heat-transfer characteristics were reevaluated using as consistent assumptions and methods as possible and then compared with each other and with theoretical results. The reevaluated data for both local fully developed and average Nusselt numbers in the turbulent flow region were found still to have considerable spread, with the bulk of the data being lower than predicted by existing analysis. An equation based on empirical grounds which represents most of the fully developed heat-transfer data is nu = 0.625 pe(0.4) where nu represents the Nusselt number and pe the Peclet number. The theoretical prediction of the heat transfer in the entrance region was found to give lower values, in most cases, than those found in the experimental work.