Report presenting an investigation at two Mach numbers to examine the flow, force, and moment characteristics associated with spoilers mounted on a flat plate at a range of sweep angles. Pressure measurements were obtained over the plate and spoiler faces. The pressures were integrated to determine the spoiler lift, pitching-moment, drag, and hinge-moment characteristics.

Memorandum presenting the methods and instruments used at a particular lab to illustrate the magnitudes of errors associated with Mach number measurements at supersonic speeds and at high altitudes. Data is presented for two modified methods of the basic radar phototheodolite method of position-error calibration.

Report presenting an investigation at two Mach numbers to determine the pressure distributions, chordwise loadings, and spanwise loadings for a series of 25.4-percent-chord trailing-edge controls on a trapezoidal wing with a 23 degree sweptback leading edge, aspect ratio of 3.1, and taper ratio of 0.4.

Report presenting an investigation at low speed of a complete-model configuration with a wing of aspect ratio 4, taper ratio 0.3, and 45 degrees sweepback and had inboard and outboard ailerons. The model was tested over a range of sideslip and angles of attack to determine variations of the aerodynamic coefficients, especially pitching-moment coefficient, with sideslip angle. The results indicate that with ailerons deflected, an appreciable variation of pitching moment with sideslip angle can exist.

Report presenting an investigation of three phases: an experimental investigation of a thin airfoil with blowing over a trailing-edge flap, a comparison of the results of the experimental investigation with the results of other similar investigations, and a theoretical study of the relationships among the air-flow and power parameters for the general blowing case. The investigation utilized a two-dimensional model of the NACA 0006 airfoil equipped with a nose flap and six alternate trailing-edge flaps.

Report presenting an investigation of the lateral stability and control effectiveness of a model of a fighter-type airplane model with a low-aspect-ratio and 3.4-percent-thick wing with negative dihedral at a range of Mach numbers, sideslip angles, and angles of attack. Results regarding the lateral characteristics at zero angle of attack, lifting conditions, and lateral and directional controls are provided.

Report presenting the longitudinal stability characteristics of a simple infrared homing missile determined in flight with a rocket-powered model. Static and dynamic longitudinal stability derivatives of the cruciform, interdigitated, canard-wing missile configuration were determined using the pulse-rocket technique for a range of Mach numbers.

Paper presenting a preliminary account of some research conducted on the general problem of flow separation. The research is fundamental in nature, partly theoretical, and partly experimental. Measurements are made of subsonic and supersonic speeds for a variety of two dimensional model shapes involving separation.

Tests have been made in the Langley 4- by 4-foot supersonic pressure tunnel at a Mach number of 2.01 to determine the effects of the addition of four small fuselage-mounted cruciform fins on the directional characteristics of a 45 deg swept-wing airplane model at angles of attack up to 15.3 deg and angles of sideslip up to about 16 deg. The results showed that the addition of the four cruciform fins to the model increased the directional stability substantially at the highest angle of attack and, at the same time, caused relatively small changes in drag.

Memorandum presenting oscillatory hinge-moment characteristics obtained from free-flight tests of two rocket-powered models equipped with a 60 degree sweptback clipped delta wing featuring an unbalanced, constant-chord, full-span trailing-edge control. One aircraft had a control with a sharp trailing edge, and the other had a trailing-edge thickness equal to 1/2 the thickness at the hinge line. Results regarding control pulsing systems, control damping, and control restoring moments are provided.

Memorandum presenting a review of the subsonic-diffuser data available in the literature, which is then reduced to certain appropriate performance coefficients and presented as functions of the significant geometric and flow variables. Results regarding total-pressure-loss factor, diffuser effectiveness, recovery of diffuser effectiveness in the tailpipe, inlet speed effects, exit flow distributions, boundary-layer control, and effects of distorted inlet velocity distribution are provided.

Report presenting a review of subsonic-diffuser data, which was reduced to certain appropriate performance coefficients and presented as functions of the significant geometric and flow variables. The report is divided into the following sections: performance at low speeds, the effect of increasing the inlet speed up to choking Mach numbers, illustrations of the effectiveness of boundary-layer controls, and illustrations of the effects of distorted inlet velocity distributions at subsonic speeds.

Thermodynamic properties of hydrogen and its products of combustion with air are tabulated in a form convenient for use in cycle analysis and design of turbojet engines. Only low pressures are considered, and the effects of dissociation are ignored. Several thermodynamic processes are analyzed, and their analysis is illustrated by numerical example.