Memorandum presenting an analysis of probable heat-exchanger weights for stationary and rotary regenerator heat exchangers for use in a hydrogen-expansion turbine engine. This is because rotary regenerators offer possibilities for a considerably lighter heat-exchanger core, possibly one-fourth that of the stationary regenerators.

Report presenting free-flight measurements of the rolling effectiveness and drag of trailing-edge spoilers on low-aspect-ratio wings with both laminar and turbulent boundary layers at two different Mach numbers. The effect of a spoiler deflected from the surface of a wing is to cause boundary-layer separation upstream.

Report presenting measurements of recovery temperatures on a slender cone-cylinder with a 12 degree vertex angle and a 1.25-inch-diameter cylinder for a range of Mach numbers. Results regarding the visual evidence, temperature distributions, pressure distributions, summary figures, correlation of temperature patterns with boundary-layer transition and separation, and recovery factors are provided.

Memorandum presenting a theoretical mixed-jet one-spool turbofan engine analyzed over a range of flight Mach numbers up to 2.95. The engine was characterized by an eight-stage fan-compressor unit. Results regarding performance maps, rotating stall, turbofan inlet axial velocity, and weight-flow variations are provided.

Memorandum presenting an experimental and analytical study made at transonic speeds up to Mach number 1.43 to determine the ability of present calculation procedures to predict transonic drag-rise changes which result from physical model changes. Both wing-body and wing-body-tail configurations were investigated.

Experimental study to determine the vibrational modes of several hollow turbine blades and a solid turbine blade of similar aerodynamic design. Results regarding the significance of nodal patterns, vibrational modes of six blade types, and the probability of excitation in some of the blades are provided.

Report presenting a review of the present status of research and development on high-energy fuels for ramjet propulsion. It also presents experimental investigations on the use of high-energy fuels in ram jets that include the materials aluminum, boron, boron hydrides, carbon, coal and coal-light metal compositions, liquid hydrogen, and magnesium. A comparison of the fuels in terms of heating values, combustion temperatures and specific impulse, and availability of fuels are provided.

From Introduction: "Good experimental correlation of the analytical results was obtained for the compressor even though isentropic flow and axial symmetry were assumed (reference 1). In order to determine the flow through the turbine being investigated, however, it was necessary to extend the method of reference 1 to include the flow downstream of the rooter since the large blade taper and hub-shroud curvature caused downstream conditions which affected the flow inside the rotor."

Report discussing testing of a model of a cruciform 60 degree delta-wing missile configuration with half-delta tip controls at a range of Mach numbers. Longitudinal stability derivatives, control effectiveness, and drag characteristics were obtained using a square-wave pulsed-control technique.

Report presenting an investigation at transonic speeds in the high-speed 7- by 10-foot tunnel to determine the effect of wing sweep on the maximum-lift characteristics of a series of wings with aspect ratio 4, taper ratio 0.6, and NACA 65A006 airfoil sections. Testing occurred over a range of Mach and Reynolds numbers. Maximum lift coefficients were found to increase with increased sweep at lower Mach numbers but decreased with increase sweep at higher Mach numbers.

Report presenting testing of a body with a 22.5 degree conical nose, a 4-diameter-long cylindrical midsection, and a 20 degree cone-frustum tail flare. The tests were made over a variety of angles of attack and Mach numbers. Results regarding spark shadowgraph pictures and predictions versus the actual values were provided.

Report presenting a correlation of the available data on various flap-type high-lift devices in two-dimensional form for flap-chord ratios ranging from 20 to 40 percent. Data for plain, single-slotted, and double-slotted flaps, and for suction and blowing flaps, are provided. Analysis regarding the effect of wing thickness and slot width is also provided for the various types of flaps.

Memorandum presenting a summary of ignition-lag data obtained from 1949 to 1956 in terms of dependence on temperature, pressure, reactor geometry, mixing method, and propellant composition. Analysis of the results and comparisons with data from other sources indicate agreement with a chemical kinetics model provided that mixing is reasonably energetic.

From Summary: "Presented herein are the results of a study of some of the problems associated with the cross-roll filter, command computer, and g-limiter of an automatic interceptor system."

Report presenting an experimental and analytical study at transonic speeds up to Mach number 1.43 to determine the ability of present calculation procedures to predict transonic drag-rise changes resulting from physical model changes. Results regarding wing-body configurations, wing-body-tail configurations, and drag-rise change are provided. With the exception of the model with the bluff forebody and afterbody, the currently available calculative procedures provided estimates of transonic drag within 15 percent of measured values.

Report presenting an analysis of probable heat-exchanger weights for stationary and rotary regenerator heat exchangers for use in a hydrogen-expansion turbine engine. Rotary regenerators may be used for a considerably lighter heat-exchanger core, possibly one-fourth that of the stationary regenerators.

"A spin investigation has been conducted in the Langley 20-foot free-spinning tunnel on a 1/20-scale model of the Chance Vought XF6U-1 airplane. The effects of control settings and movements upon the erect and inverted spin and recovery characteristics of the model were determined for the normal-fighter condition. The investigation also included tests for the take-off fighter condition (wing-tip tanks plus fuel added) spin-recovery parachutes, and simulated pilot escape" (p. 1).