Report presenting testing of a translating cone inlet with a variable bypass at Mach numbers 1.6, 1.8, and 2.0 with both a choked exit plug and a J34 turbojet engine. The main difference between the two options was increased inlet subcritical stability with the engine. Results regarding basic diffuser performance, inlet stability, buzz amplitude and frequency, and diffuser-exit profiles are provided.

"A J34 turbojet engine was investigated at free-stream Mach numbers of 0.12 and 1.6 to 2.0 to determine the effect of supersonic inlet operation on engine performance. With the exception of ideal jet thrust, the use of generalized engine parameters correlated the engine data satisfactorily when the exit nozzle was choked. Large total-pressure distortions did not affect compressor efficiency" (p. 1).

Memorandum presenting the static lateral-directional stability characteristics of several airplane models recently investigated which cover many of the geometric arrangements of high-speed airplane components of current interest. The results are limited to the most pertinent aerodynamic phenomena contributing to the lateral-directional characteristics of each airplane type. Results for five different models are provided.

Report presenting preliminary drag data obtained for the XF-92A delta wing airplane during demonstration tests after it had been modified to use the J33-A-29 turbojet engine. Drag data, lift coefficients, and lift-curve slopes are provided.

Report presenting the static lateral-directional stability characteristics of several airplane models that cover many of the geometric arrangements of high-speed airplane components of current interest. The results are presented for a subsonic Mach number of 0.9 and for supersonic Mach numbers ranging from 1.2 to 1.9. Five different models are described and tested.

Report presenting an investigation of a normal-shock positioning control which utilized the bypass of a supersonic inlet to set the required air flow for a J34 turbojet engines to Mach number 2.0 in the supersonic tunnel. Continuous control without oscillations was obtained by use of the pressure signal from the small static probe. Calculated response time generally agreed with measured values.

Report presenting static single shear tests of 3/16-inch-diameter 2117-T4 (A17S-T4) aluminum-alloy rivets at elevated temperatures. The maximum temperature tested was 800 degrees Fahrenheit and the time at temperature prior to testing range from 1/2 hour to 720 hours.

Report presenting an investigation of the transonic flutter characteristics of two 64 degree sweptback delta wings. Both of the wings had simulated streamwise ribs and orthogonal spanwise spars, but the wings had different stiffness and mass.

Report presenting an investigation by the transonic-bump method of the static longitudinal aerodynamic characteristics of a series of swept, highly tapered, thin wings in the high-speed 7- by 10-foot tunnel. Testing occurred over a range of Mach and Reynolds numbers and angles of attack. Results regarding lift and drag characteristics and longitudinal stability characteristics are provided.

Report presenting the propulsive and aerodynamic characteristics of a flat ramjet engine suitable for use on a helicopter rotor and compared with previous tests of an equivalent engine with a circular cross section. The results indicate that the flat engine has higher values of propulsive thrust plus power-off drag than the circular engine. The power-off and drag characteristics indicate that the flat engine has lift-drag ratios about 3 times those obtained with the circular engine.

Report presenting an investigation of an NACA 10-(1.7)(062)-057-27 two-blade swept propeller was conducted int he 16-foot high-speed tunnel over a range of blade-angle settings. Two related straight propellers were also tested over the same operating range as the swept propeller. Results regarding envelope efficiency, effect of compressibility on maximum efficiency, effect of sweep on power coefficient, constant-power propeller operation, and effect of sweep on propeller-blade loading are provided.

From Introduction: "The design and flight evaluation of an airborne target simulator for use in tracking studies of fighter-type airplanes equipped with optical gunsights have recently been reported (ref. 1). In this equipment the target airplane was represented by a movable dot of light projected on the windshield of the test airplane."