Report presenting an investigation of the rolling effectiveness of spoiler and aileron aerodynamic controls on a fighter-type airplane from Mach numbers 0.6 to 1.5. No effects of mutual interference between the spoiler and aileron were detectable. Results regarding drag and the effect of gap upon spoiler performance are also provided.

From Summary: "The transonic similarity rules have been applied to the correlation of experimental data for a series of 22 rectangular wings having symmetrical NACA 63A-series sections, aspect ratios from 1/2 to 6, and thicknesses from 2 to 10 percent. The data were obtained by use of the transonic bump technique over a Mach number range from 0.40 to 1.10, corresponding to a Reynolds number range from 1.25 to 2.05 million. The results show that it is possible to correlate experimental data throughout the subsonic, transonic, and moderate supersonic regimes by using the transonic similarity parameters in forms which are consistent with the Prandtl-Glauert rule of linearized theory."

Memorandum presenting a systematic study to determine the effect of molecular structure on the flammability limits of pure hydrocarbon-air mixtures at reduced pressures and room temperature. This report presents results obtained for 17 pure normal paraffins, branched paraffins, and mono-olefins. Results regarding experimental variables and experimental observations are provided.

Memorandum presenting an investigation to evaluate the effect of Reynolds number and Mach number on the aerodynamic characteristics of a horizontal tail of aspect ratio 3 equipped with a plain, sealed, full-span elevator. The line joining the quarter-chord points of the airfoil sections was swept back 45 degrees and the sections perpendicular to this line were the NACA 64A010. Results regarding the effect of Reynolds number and effects of leading-edge roughness and elevator-nose seal are provided.

Report presenting a theoretical analysis of a supersonic canard missile configuration to show the means that might be used to improve its dynamic performance characteristics. The analysis was conducted by using the best available estimates of aerodynamic and airframe parameters. Results regarding missile longitudinal performance, selection of rate factor, angle of attack and normal acceleration, frequency response, pole plots, and tip control are provided.

Memorandum presenting the pressure recovery, mass flow, and axial force of four bodies with nose inlets measured at Mach numbers between 1.4 and 2.0 and angles of attack of 0, 3, 6, and 9 degrees. The drag coefficients of axially symmetric diffusers operating at the maximum mass-flow rates were calculated from schileren photographs of the head shock waves and frictional drag considerations. Results regarding open-nose diffusers and conical-shock diffusers are provided.

Report presenting the effect on drag of varying the vertical position of a nacelle at 40 percent semispan of a 45 degree sweptback wing and body combination as determined by transonic flight tests at zero lift. Three nacelle positions were investigated: a pylon mounted nacelle, an underslung nacelle, and a symmetrically mounted nacelle. Results regarding total drag coefficient and maximum wing-tip helix angle are provided.

An analysis has been made of the drag losses in airplane flight of cross-flow plate and tubular intercoolers to determine the cooling-air weight flow and pressure drop that give a minimum drag loss for any given cooling effectiveness and, thus, a maximum power-plant net gain due to charge-air cooling. The drag losses considered in this analysis are those due to (1) the extra drag imposed on the airplane by the weight of the intercooler, its duct, and its supports and (2) the drag sustained by the cooling air in flowing through the intercooler and its duct. The investigation covers a range of conditions of altitude, airspeed, lift-drag ratio, supercharger-pressure ratio, and supercharger adiabatic efficiency. The optimum values of cooling air pressure drop and weight flow ratio are tabulated. Curves are presented to illustrate the results of the analysis.

Report presenting data from an investigation of the effects of slot location and slot geometry on the flow in a square tunnel for a Mach number range up to 1.4. Calculated static-pressure and angle-of-flow distributions along the slotted boundary are presented for several slot configurations in a tunnel with two opposite walls slotted.

From Summary: "Approximate shapes of nonlifting bodies having minimum pressure foredrag at high supersonic airspeeds are calculated.With the aid of Newton's law of resistance, the investigation is carried out for various combinations of the conditions of given body length, base diameter, surface area, and volume. In general it is found that when body length is fixed, the body has a blunt nose; whereas, when the length is not fixed, the body has a sharp nose."

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."

"An attempt is made to describe the phenomenological differences between stall flutter and buffeting. Some experimental results are presented concerning both the boundaries at which these phenomena occur and the stresses involved" (p. 1).

Memorandum presenting tests in the 9-inch supersonic tunnel of three bomb or store shapes without fins and with two sets of cruciform fins. Measurements of normal force, chord force, and pitching moment were made; analyses of the effects of angle of attack and Reynolds number on these qualities and also upon center-of-pressure position and fin effectiveness are presented.

Report presenting the effects of inclining the plane of the inlet on the performance of several converging-diverging diffusers at zero angle of attack for a range of Mach numbers. Results regarding Schileren photographs, static-pressure recovery, total-pressure loss, and total-pressure distributions are provided.

Report presenting an investigation of the flow field behind triangular wings alone and in combination with a pointed cylindrical body at Mach numbers of 1.5 and 2.0 through an angle-of-attack range of 0 to 24 degrees. Results regarding the geometric characteristics of the vortex system and downwash characteristics are provided.

The weight breakdowns in bar chart form in the present report have been prepared to give an indication of 'how we spend our weight.' They are expected to focus attention on the design functions that warrant weight reduction activity on future models.

From Introduction: "This paper presents the aerodynamic characteristics of low-aspect-ratio sweptback wing having a full-span flap type of control employing an overhanging balance of 50 percent of the flap chord.The main purpose of this investigation was to determine if overhang balances are an effective means of reducing the hinge moments of flap type of controls at transonic speeds."

Report presenting an investigation to determine the ditching characteristics of three typical multiengine airplanes equipped with different arrangements of hydro-ski ditching gear. The behavior was determined from visual observations, acceleration records, and motion pictures of the landings. Results regarding ski size, shape, and location are provided.

An analytical investigation of the effects of fuel density and heating value on the cruising range of a ram-jet airplane was made. Results indicate that with present-day knowledge of chemical fuels, neither very high nor very low fuel densities have any advantages for long-range flight. Of the fuels investigated, the borohydrides and metallic boron have the greatest range potential. Aluminum and aluminum hydrocarbon slurries were inferior to pure hydrocarbon fuel and boron-hydrocarbon slurries were superior on a range basis. It was concluded that the practical difficulties associated with the use of liquid hydrogen fuel cannot be justified on a range basis.

Report presenting measurements of average heat-transfer and friction coefficients obtained with air flowing through electrically heated ducts with square, rectangular, and triangular cross sections for a range of surface temperatures and Reynolds numbers. Results regarding heat balances, correlation of heat-transfer coefficients, correlation of friction coefficients, and correlation of peripheral temperature variations are provided.

"A variable-area auxiliary air scoop in combination with a fixed-area nose intake was tested at Mach numbers from 0 to 1.3. The purpose of the investigation was to evaluate the effectiveness of such an auxiliary intake in improving the net thrust of an intake-engine combination over a range of speeds. The results indicated that the internal flow was always stable and that improvements in net thrust would be realized at Mach numbers up to about 1.1 for an intake design Mach number of 1.3" (p. 1).

Report presenting an investigation to determine the low-speed, large-scale characteristics of an airplane configuration with an aspect ratio 2 triangular wing of variable incidence. The model consisted of the variable-incidence wing in combination with a fuselage of fineness ratio 13, a triangular vertical tail, and a thin, unswept, all-movable horizontal tail. Results regarding the lift characteristics of the model with the tail off, longitudinal stability with the horizontal tail on, trim lift and drag characteristics, and directional instability are provided.

Report discussing an investigation of external-store characteristics using a 245-gallon external fuel tank mounted under a wing of a North American F-86A airplane. The store normal force was found to increase abruptly on penetration of the buffet boundary. Information about the normal- and side-load distribution and integrated force and moment coefficients is provided.

Report presenting an investigation of spoilers at a Mach number of 1.93 to determine the effects of height and chordwise location on the section pressure distributions and section aerodynamic characteristics of a two-dimensional, 6-percent-thick, symmetrical wing. Spoilers of 3-, 5-, and 7-percent-chord height were tested at three chordwise locations. Results regarding pressure distributions, aerodynamic characteristics, and shock boundary-layer interactions are provided.