From Summary: "Solutions of mainstream flow patterns for three-dimensional, laminar, incompressible thin-boundary-layer flows (over flat or slightly curved surfaces) having similarity with respect to stationary polar coordinates in the plane of the surface are derived. The solutions are summarized in a table."

Note presenting laminar burning velocity measured at pressures of 1 atmosphere and below and critical boundary velocity gradient for flashback at pressures below 1 atmosphere over a range of compositions for hydrogen-air burner flames. Pressure exponents of 0.23 for burning velocity and 1.35 for flashback velocity gradient was found. Results regarding blowoff and general stability loop, burning velocity, relations among various combustion properties, and reaction order from pressure exponents are provided.

Note presenting an investigation to determine the effects of wing position on the low-speed static longitudinal and static lateral stability of airplane models with fuselages of square and rectangular cross sections and unswept and 45 degree sweptback surfaces. The results of the investigation indicated that at low angles of attack, the complete unswept models with the wing in the high position were more stable or least longitudinally unstable. The results also showed that wing-fuselage interference causes an increase in effective dihedral angle when the wing is moved to the high position.

Report discussing a flight investigation of rocket-powered models of a tailless triangular-wing airplane configuration was made through the transonic and low supersonic speed range at the Langley Pilotless Aircraft Research Station at Wallops Island, Va. An analysis of the aerodynamic coefficients, stability derivatives, and flying qualities based on the results obtained from the successful flight tests of three models is presented.

A thermal quenching equation and the Semenov burning velocity equation were combined to give expressions for the product and quotient of burning velocity and quenching distance. Experimental results for hydrocarbon-oxygen-inert gas, hydrocarbon-nitrous oxide, hydrogen-air, hydrogen-bromine, and the ethylene oxide decomposition flames were fairly well correlated by the product equation.

"Data from full-scale experimental airplane crashes were studied to determine how impact injuries occur and how the chance of such injuries may be reduced. The following hazards were considered: (1) being crushed, (2) being struck by missiles, (3) striking objects by tearing loose or flailing about, and (4) being injured by the crash decelerations. Transport, cargo, fighter, and light airplane crashes were studied" (p. 1).

From Introduction: "The object of the present paper is to present an approximate method for calculating accurately the thermal stresses in a thin plate with both chordwise and spanwise variations in temperature and chordwise but restricted spanwise variations in thickness."

The theoretical lift of a cylindrical afterbody at zero angle of attack due to incidence of the wing is calculated by means of slender-body theory. It is assumed that the vortex sheet becomes fully rolled up ahead of the tail, and the vortex paths in the presence of the body are determined analytically. The total lift of a variety of slender wing-body-tail combinations due to wing incidence is also calculated.

This report presents tabulated values of certain definite integral that are involved in the calculation of near-field propeller noise when the chordwise forces are assumed to be either uniform or of a Dirac delta type. The tabulations are over a wide range of operating conditions and are useful for estimating propeller noise when either the concept of an effective radius or radial distributions of forces are considered. Use of the tabulations is illustrated by several examples of calculated results for some specific propellers.

Report presenting a study in the 19-foot pressure tunnel to determine the effects of fuselage afterbody shape, split flaps, and variations in the span of the leading-edge flaps on the stability contributed by the horizontal tail to an airplane with the wing swept back 42 degrees.

Report presenting the linearized equations of motion have been derived for a rolling missile with slight aerodynamic asymmetries. Time histories of rolling-missile motions referred to a body-axis system have been prepared to show the types of missile motions that can be encountered.

The drag of a body alone, six triangular wings of various aspect ratios, and the combinations were measured at Mach numbers of 1.50 and 2.02 at a Reynolds number of 5.5 million (based on the body length). The experimental drag-interference results were in accordance with calculations based on NACA RM A9E19, 1949, with skin-friction effects taken into account, the interference effect being principally the result of fixing transition on the body by adding a wing.

Report presenting an investigation of the two-dimensional flow along flat plates with rounded leading edges, which provide additional information on shock-induced separation. The results indicate that laminar boundary layers can sustain the theoretical pressure rise for normal shocks without separating provided that the local Mach numbers are less than about 1.4.

From Introduction: "Results obtained in the experimental investigations of secondary flows in turbomachines (refs. 1 to 3) indicate that information concerning three-dimensional laminar boundary-layer behavior can be of practical value in interpreting and correlating measurements of losses in the turbo-machines for design purposes. Reference 4 gives a theoretical analysis of the overturning (more than mainstream turning) of the three-dimensional laminar boundary layer developed on flat or nearly flat surfaces, under mainstream flows which consist of streamline translates (i.e., the entire streamline pattern can be obtained by translating any particular streamline pattern can be obtained by translating any particular streamline parallel to the leading edge, fig. 1) with constant axial velocity component."

The experimental deflections and stresses of six plastic multicell-wing models of unswept, delta, and swept plan form are presented and compared with previously published theoretical results obtained by the electrical analog method. The comparisons indicate that the theory is reliable except for the evaluation of stresses in the vicinity of the leading edge of delta wings and the leading and trailing edges of swept wings. The stresses in these regions are questionable, apparently because of simplifications employed in idealizing the actual structure for theoretical purposes and because of local effects of concentrated loads.

Report presenting a systematic investigation of the low-speed cascade performance of particular high-speed NACA compressor blade sections. Porous test-section side walls and porous flexible end walls were employed to establish a close simulation of the two-dimensional flow. Results regarding the low-speed pressure distribution, selection of design angle of attack, correlation of design angle of attack and design turning angle, relationship between turning angle and angle of attack, operating range, pressure rise, effect of roughness, Reynolds number, and turbulence on blade performance are provided.

Report presenting an investigation in the high-speed 7- by 10-foot tunnel to determine the horizontal- and vertical-tail contributions to the static lateral stability of a complete-model swept-wing configuration at high subsonic speeds. Results regarding the methods of analysis and vertical-tail contributions are provided.

Report presenting testing of model ring-cascade thrust reversers in quiescent air to determine the effect of geometric design variables on performance and reversed-flow fields. The configurations consisted of a cascade of turning rings plus a mechanical deflector positioned aft of a 4-inch exhaust nozzle with a 7 degree external fairing. Results regarding the effect of nozzle pressure ratio on performance, effect of deflector geometry on performance, effect of cascade geometry on performance, reversed-flow boundaries, and thrust-modulation characteristics are provided.

Report presenting compressive stress-strain test results for 2024-T3 aluminum-alloy sheet for temperatures ranging from room temperature to 700 degrees Fahrenheit and for exposure times from 0.1 to 100 hours. Results regarding experimental test data, prediction of time-temperature combinations that produce maximum yield stress, and master compressive-yield-stress curve are provided.

Report presenting compressive stress-strain testing for 7075-T6 aluminum alloy sheets at temperatures ranging from room temperature to 700 degrees Fahrenheit and exposure times from 0.1 to 100 hours. Results regarding the test results and master compressive-yield-stress curve are provided.

The basic ideas of the slender-body approximation have been applied to the nonlinear transonic-flow equation for the velocity potential in order to obtain some of the essential features of slender-body theory at transonic speeds. The results of the investigation are presented from a unified point of view which demonstrates the similarity of slender-body solutions in the various Mach number ranges. The transonic area rule and some conditions concerning its validity follow from the analysis.

Note presenting an analysis of the method of measuring moment of inertia of an airplane by oscillating it on knife edges and a spring for application to flexible airplanes. The application and results of the above method in ground oscillation tests are described.

Report presenting an investigation of an airplane model conducted to determine the effect of area-suction trailing-edge flaps and several leading-edge modifications on the aerodynamic characteristics of a 45 degree sweptback wing. Results regarding the effect of trailing-edge flaps on the aerodynamic characteristics of the model with horizontal tail off, effect of wing modifications on the high-lift characteristics of the model with the horizontal tail off, aerodynamic characteristics of the model with the horizontal tail installed, and area-suction requirements are provided.

Report presenting an investigation in the stability tunnel to determine the combined effect of wing and wing-body interference on the contribution of an x-tail configuration to the low-speed rolling-stability derivatives of an airplane model with an unswept midwing and to indicate the change due to roll in the local flow angularity at a number of stations across the tail surfaces for one-half of the x-tail. Results regarding the static longitudinal characteristics, steady-roll characteristics, and angularity measurements are provided.