Report presenting the use of the slender-wing-type analysis to obtain general expressions for the surface pressure, lift, and rolling moment for cambered wings with swept trailing edges. The results are specialized to give the additional loading due to the deflection of trailing-edge control surfaces and the loading due to a particular type of wing twist. A numerical example for aileron control is included.

Ram-jet cycles that use the chemical energy of dissociated oxygen for propulsion in the ionosphere are presented. After a review of the properties and compositions of the upper atmosphere, the external drag, recombination kinetics, and aerodynamic-heating problems of an orbiting ram jet are analyzed. The study indicates that the recombination ram jet might be useful for sustaining a satellite at an altitude of about 60 miles. Atmospheric composition and recombination-rate coefficients were too uncertain for more definite conclusions. The ram jet is a marginal device even in the optimistic view.

Report presenting a comparison of several methods for handling excess inlet flow for the Mach number range from 1.5 to 4.0. The following techniques were examined and evaluated: normal- and oblique-shock spillage, bypassing through an auxiliary exit, bypassing to an ejector exhaust nozzle, and bypassing the excess flow through an auxiliary ramjet engine. Charts are presented for the thrust penalties at a variety of Mach numbers.

A Nusselt-Reynolds number relation for cylindrical thermocouple wires in crossflow was obtained from the experimental determination of time constants. Tests were conducted in exhaust gas over a temperature range of 2000 to 3400 R, a Mach number range of 0.3 to 0.8, and a static-pressure range from 2/3 to 1-1/3 atmospheres, yielding a Reynolds number range of 450 to 3000. The correlation obtained is Nu=(0.428 plus or minus 0.003) times the square root of Re* with average deviations of a single observation of 8.5 percent. This relation is the same as one previously reported for room-temperature conditions.

Report presenting pressure distributions and force characteristics for a body of revolution consisting of a fineness ratio of 5.75, circular-arc, ogival nose tangent to a cylindrical afterbody for a range of angles of attack. Comparison of the theoretical and experimental pressure distributions shows that for zero lift, both slender-body theory and higher-order theories yield results that are in good agreement with theory.

Effects of Reynolds number and angle of attack on the pressure distribution and normal-force characteristics of a body of revolution consisting of a fineness ratio 3 ogival nose tangent to a cylindrical afterbody 7 diameters long have been determined. The test Mach number was 1.98 and the angle-of-attack range from 0 degree to 20 degrees. The Reynolds numbers, based on body diameter, were 0.15 x 10(6) and 0.45 x 10(6). The experimental results are compared with theory.

Report presenting an investigation to determine the transition Reynolds numbers on a 10 degree cone in the 4- by 4-foot supersonic pressure tunnel at three Mach numbers and a range of Reynolds numbers. Results regarding a smooth cone and a cone with roughness are provided.

Note presenting a determination of the boundary layer behind a shock or thin expansion wave advancing into a stationary fluid. The assumption of a thin expansion wave was found to be valid for weak expansions but becomes progressively less accurate for strong expansion waves. The turbulent-boundary-layer solutions in this report represent an extension of empirical, semi-infinite flat-plate, boundary-layer data to the case where the wall is moving.

Report presenting a description of a temperature-measuring system using two sonic-flow orifices in series, which is used to measure the exhaust gas temperature of an afterburning jet engine mounted in a swinging pitot-static probe. It was found to improve the reliability and reduce the computational time required of the previously used system.

An investigation of the effectiveness of a wing equipped with a sliding flap and a leading-edge slat in deflecting a propeller slipstream downward for vertical take-off was conducted in a static-thrust facility. Results regarding the characteristics with leading-edge slat and with extended flap chord are provided.

A study to evaluate a method for predicting the downwash in a transverse plane behind a wing-body combination throughout a range of angles of attack. The wing-body combination had a ratio of maximum body diameter to wing span of 0.259, a triangular wing with an aspect ratio of 2.0, and a body of revolution with a fineness ratio of 12.5. Results regarding span loading, downwash, and vortex cores are provided.

Report presenting an investigation to determine the effects of the various components and combinations of components on the static longitudinal and lateral stability characteristics of unswept-midwing models having wings with a variety of aspect ratios for a range of angles of attack. Results regarding static longitudinal stability characteristics and static lateral stability characteristics are provided.

Report presenting an investigation of a leading-edge slat as a possible longitudinal control device for vertically rising airplanes that utilize the redirected-slipstream principle at zero forward speed in a static-thrust facility. A semispan wing model equipped with large-chord slotted flaps and two large-diameter overlapping propellers was used. Results regarding the effect of slat position, effect of propeller position, characteristics of the modified model, and a comparison of characteristics with one or two propellers are provided.

Report presenting a derivation of the lateral motions of an airplane flying through continuous random isotropic turbulence in terms of three different functions and sets of forces. Three airplanes of different size are used to demonstrate the method, illustrate characteristic trends, and exhibit some simplifications possible in the calculations.

A method is presented for the approximate solution of the nonlinear equations transonic flow theory. Solutions are found for two-dimensional flows at a Mach number of 1 and for purely subsonic and purely supersonic flows. Results are obtained in closed analytic form for a large and significant class of nonlifting airfoils. At a Mach number of 1 general expressions are given for the pressure distribution on an airfoil of specified geometry and for the shape of an airfoil having a prescribed pressure distribution. Extensive comparisons are made with available data, particularly for a Mach number of 1, and with existing solutions.

From Summary: "This paper briefly summaries the more important statistical data obtained by the NACA on the subject of ground loads. The information presented relates primarily to landing-impact and taxiing loads; however, some limited data are also presented on one phase of ground-handling loads, namely, braking friction. A number of experimental and theoretical papers dealing with various aspects of the subject are listed in the bibliography."

Note presenting tests of a hydraulic-power-controlled helicopter to determine the effect of friction in the servovalves and the effect of stick friction when the valve friction is present. The tests showed that, when the valve friction is equivalent to about 1 3/4 pounds of force at the stick, precision flying is difficult and more work is required of the pilot.

"Low-aspect-ratio wings having pointed plan forms are treated on the assumption that the flow potentials in planes at right angles to the long axis of the airfoils are similar to the corresponding two-dimensional potentials. For the limiting case of small angles of attack and low aspect ratios the theory brings out the following significant properties: (1) The lift of a slender, pointed airfoil moving in the direction of its long axis depends on the increase in width of the sections in a downstream direction. Sections behind the section of maximum width develop no lift. (2) The spanwise loading of such an airfoil is independent of the plan form and approaches the distribution giving a minimum induced drag. (3) The lift distribution of a pointed airfoil travelling point-foremost is relatively unaffected by the compressibility of the air below or above the speed of sound. A best of a triangular airfoil at a Mach number of 1.75 verified the theoretical values of lift and center of pressure" (p. 1).

Two-dimensional tests were made of an NACA 0006 airfoil with area suction applied to a porous region on a 0.3-chord trailing-edge flap deflected 50 degrees. The lift with suction approached the value computed from thin-airfoil theory. The lift gains and suction quantity requirements were unaffected by the perforation patterns of the surface over a wide range of hole sizes and spacings.

From Summary: "An investigation was made in the NACA 7 by 10 foot wind tunnel to find the increase in maximum lift coefficient which could be obtained by providing a model wing with both a Fowler trailing-edge extension flap and a Handley Page type leading-edge slot. A conventional Handley page slot proportioned to operate on the plain wing without a flap gave but a slight increase with the flap; so a special form of slot was developed to work more effectively with the flap. With the best combined arrangement the maximum lift coefficient based on the original area was increased from 3.17, for the Fowler wing, to 3.62."

Report presenting a theoretical investigation to study the effects of systematic changes in configuration of a representative airframe on the center-of-pressure travel due to changes in angle of attack and Mach number. The airframe was an unbanked canard missile configuration with low-aspect-ratio coplanar wing and tail surfaces of triangular plan form.

"A theoretical analysis is given for the stresses and deflections of a square plate with clamped edges under normal pressure producing large deflections. Values of the bending stress and membrane stress at the center of the plate and at the midpoint of the edge are given for center deflections up to 1.9 times the plate thickness. The shape of the deflected surface is given for low pressures and for the highest pressure considered" (p. 1).

Note presenting an experimental investigation conducted to determine the characteristics of a 40 degree cone for use in the measurement of Mach number, total pressure, and flow angles. The cone had a total-pressure orifice at the apex and four equally spaced static-pressure orifices on the surface and pressure measurements were taken at a range of angles of pitch, Mach numbers, and Reynolds numbers. Results regarding cone pressure distribution, determination of Mach number, determination of total pressure, and determination of flow angles are provided.

Report presenting the method and advantages of matrix algebra in setting up the geometric aspects of problems of airplane motion. The paper is divided into two parts. The first is about the aspects of matrix algebra required for use in orthogonal transformations and the other shows how to use orthogonal transformations in matrix form by applying them in several examples.