Report presenting a flight investigation using a rocket-powered model to evaluate the roll-rate stabilization of the Naval Ordnance Test Station SIDEWINDER missile, which uses aerodynamic damping by gyro-actuated rollerons. Dynamic roll instability was found to occur in flight.

Report presenting the initial development of a technique for the qualitative study of the stability and control characteristics of a free, self-propelled, dynamic submarine model. Two types of control systems were evaluated. Results regarding the qualitative analysis of the control system, dive paths, equations of motion, and comparison with experimental paths are provided.

Report discussing an investigation to determine the effects of aeroelasticity on the rolling effectiveness of a model of a McDonnell F3H-1 airplane wing. The plane was found to be subject to aeroelastic losses that varied with Mach number and altitude.

Report discussing the ignition-delay determinations of three organophosphorous fuels with nitric acid oxidants at simulated altitude conditions with a small-scale rocket engine.

Report presenting experiments to study the start of fretting and cause of damage during the early stages of fretting of steel-steel combinations at a frequency 5 cycles per minute, an amplitude of 0.006 inch, a load of 150 grams, in air with relative humidity of less than 10 percent. Pure iron, glass, and iron oxide powder compacts were used in supplementary experiments.

Note presenting an analysis of the temperature distributions in a fluid over an oscillating surface with heat transfer and associated heat-transfer parameters are compared with those for the case of conduction at a stationary surface with the same initial temperature potential. It was found that the heat transfer for the oscillating surface can be considerably different from that for conduction alone.

Report presenting a wind-tunnel investigation to determine the effects of leading-edge radius and maximum thickness-chord ratio on the variation with Mach number of the aerodynamic characteristics of several thin symmetrical NACA 4-digit-series airfoil sections. The variations with Mach number of the lift, drag, and pitching moment for a 4-percent-chord-thick airfoil section are not significantly affected by a change of leading-edge radius from 0.18 to 0.53 percent of the chord.

From Summary: "The zero-lift drag of a 60 degree delta-wing-body combination (designated AGARD model 2) has been determined by free-flight tests of two models between Mach numbers of 0.8 and 1.7. These Mach numbers correspond to Reynolds numbers, based on body length, of 4 x 10(exp 6) and 12 x 10(exp 6), respectively. An estimate of the drag of the configuration was made by summing the estimates of the drag of the various components. The agreement between measured and estimated drag is good."

Report presenting an analysis of the heat transfer between an insulated tube and the fluid moving through the tube for three inlet fluid conditions: one with constant fluid temperature, one with the temperature decreased exponentially, and one with the temperature decreasing linearly with time. Results regarding the correlation of computed and experimental temperatures, multiple-tube bundle, and single insulated tube are provided.

"The magnitude and frequency of occurrence of maneuver accelerations experienced by five types of commercial transport airplanes during routine operations have been obtained from time-history (VGH) records and are presented herein. The results are compared with available gust-acceleration data for the operations considered. It is indicated that maneuver accelerations may contribute substantially to the total load histories of transport airplanes, particularly in the case of medium-altitude operations" (p. 1).

Report presenting wind-tunnel tests of a body of revolution with a circular nose inlet conducted at low speeds to ascertain some of the effects of inlet lip bluntness and profile on diffuser performance and body drag. Testing occurred at free-stream Mach numbers up to 0.330 with inlet flows from zero to choking and a steady 0 degree angle of attack and angle of yaw. Results regarding the internal-flow studies with the strut-mounted model and drag and surface-pressure studies with the sting-supported model are provided.

Report presenting the results of some sample calculations for the bending-aileron and torsion-aileron flutter of an idealized wing-aileron system for several values of Mach number in supersonic flow and some subsonic Mach numbers. The results are preliminary but may provide some knowledge of the influence of variations in certain parameters and to indicate some of the differences in the trends at high and low speeds.

Note presenting a study of the effect of overstressing on the fatigue properties of SAE 4340 steel. The effect of microstructure on the susceptibility to reduction in fatigue life due to cycles of overstress was investigated. Results regarding the effect of microstructure on overstressing damage, influence of criterion of failure on fatigue life, and effect of overstressing on endurance-limit statistics are provided.

Note presenting a review of the present and future trends of rolling-contact bearings for aircraft gas-turbine engines, which indicates that while rolling-contact bearings are satisfactory for present production engines, new bearings for future, higher output aircraft engines require more development. These new engines have operating conditions resulting in two primary problems: cage materials and endurance of materials for raceways and rolling elements.

Report presenting an investigation of the effects of heat transfer on boundary-layer transition on a body of revolution at Mach number 1.61 and a range of Reynolds numbers based on body length. Results regarding transition on a smooth model, transition on a roughened model, and a comparison with other available data are provided.

Report presenting an investigation of the effects of heat transfer on boundary-layer transition at higher Reynolds numbers, greater amounts of heating, and a more extensive study of the effects of surface irregularities than what was published in a previous report. Report presenting tests with a smooth model and tests with surface roughness and tunnel flow disturbance are provided.

Report presenting pressure-distribution data for a wing-body combination at several Mach and Reynolds numbers to investigate the effects of wing-body interference. The model was a single-wedge, rectangular wing mounted on a cylindrical body with an ogival nose. Results regarding the general physical principles, effects of angle of attack, effect of wing-incidence angle, effect of Reynolds number, and comparison with theory from other sources are provided.

Report presenting a simple method of experimentally determining the product of inertia and the inclination of the principal longitudinal axis of inertia of an airplane. The results of the method are provided and a description of the equipment and techniques are given for a simple model and a conventional airplane. Results regarding moments of inertia about the body reference area, the product of inertia and inclination of the principal axis, and the principal moments of inertia are provided.

Note presenting linearized supersonic lifting-surface theory in conjunction with structural influence coefficients to formulate a method for analyzing the aeroelastic behavior in roll at supersonic speeds of a rectangular wing mounted on a cylindrical body. Results obtained using the method are compared with the results obtained by using simplified methods of analysis.

From Summary: "Linearized theory for compressible unsteady flow is used to derive the velocity potential and lift and moment coefficients in the form of oscillating rectangular wing moving at a constant supersonic speed. Closed expressions for the velocity potential and lift and moment coefficients associated with pitching and translation are given to seventh power of the frequency. These expressions extend the range of usefulness of NACA report 1028 in which similar expressions were derived to the third power of the frequency of oscillation. For example, at a Mach number of 10/9 the expansion of the potential to the third power is an accurate representation of the potential for values of the reduced frequency only up to about 0.08; whereas the expansion of the potential to the seventh power is an accurate representation for values of the reduced frequency up to about 0.2. The section and total lift and moment coefficients are discussed with the aid of several figures. In addition, flutter speeds obtained in the Mach number range from 10/9 to 10/6 for a rectangular wing of aspect ratio 4.53 by using section coefficients derived on the basis of three-dimensional flow are compared with flutter speeds for this wing obtained …

Note presenting an analysis of the flow of fluids with and without heat sources and subject to body forces between two plane parallel surfaces which are oriented in the direction of the generating body force under the condition that the temperature vary linearly along these surfaces. Results regarding the velocity and temperature distributions, heat transfer, and fluid flow are provided.

Note presenting an investigation made to augment data previously obtained on the compressive strengths of stiffened flat-sheet panels to include the range where ultimate strengths approach the compressive yield strengths of the materials. The sheet materials tested were alclad and nonclad 14S-T6, 24S-T3, and 75S-T6. Results regarding the typical failure, ultimate strengths, rivet failures, and buckling stresses are provided.

Report presenting an experimental investigation to determine the porosity characteristics of perforated materials in normal and parallel flow. The results indicted that the porosity of material is governed principally by its open ratio, but that density has a slight effect.

"An investigation at medium to high subsonic speeds has been conducted in the Langley low-turbulence pressure tunnel to determine the static stability and control characteristics and to measure the fin normal forces and moments for a model of a wingless fin-controlled missile. With the horizontal-fin deflection limited to a maximum of 6 degrees, longitudinally stable and trimmed flight could not be maintained beyond an angle of attack of 17 degrees for a Mach number of 0.88 and beyond 20 degrees for a Mach number of 0.50 for any center-of-gravity location without the use of some auxiliary stability or control device such as jet vanes" (p. 1).