Memorandum presenting the results of an investigation directed at determining the effectiveness of various amounts and spanwise extents of conical camber on the aerodynamic characteristics of a wing-body-tail combination employing a triangular wing of aspect ratio 2.2. Five cambered wings were tested, all of which were designed for a Mach number of 1.0. Results regarding drag characteristics and lift and moment characteristics are provided.

Memorandum presenting an investigation at high subsonic speeds of a model of a twin-engine swept-wing fighter-type airplane. The model was tested with several different tail configurations and with several wing and engine inlet modifications. Results regarding pitching-moment characteristics, lift and drag characteristics, and lateral derivatives are provided.

Report presenting flight testing of a rocket-powered model of a cruciform canard missile configuration with a low-aspect-ratio wing and blunt nose. Results regarding the lift coefficient, dynamic stability, static stability, control effectiveness, and drag are provided.

Report presenting an investigation using a small-scale ramjet combustor to determine the conditions for spontaneous ignition of pentaborane, amyl nitrate, propylene oxide, and JP-4 fuel. For the range of conditions investigated, the threshold of spontaneous ignition of pentaborane is primarily governed by temperature and is also influenced by burner length and configuration. Combustion efficiency was found to increase in burner length and blocked area of the flame holder.

Report presenting testing of a full-scale rocket-powered model of a cruciform canard missile configuration with a low-aspect-ratio wing and blunt nose. Static and dynamic longitudinal stability and control derivatives were determined at low angles of attack and for a range of Mach numbers.

"An experimental radial-survey investigation of the J71-97 three-stage turbine equipped with a first stator having a throat area 87 percent of the design value was conducted at one turbine operating point. The first-, second-, and third-stage mass-averaged efficiencies were 0.897, 0.843, and 0.755, respectively. The corresponding over-all turbine efficiency was 0.856" (p. 1).

Report presenting a blade-element analysis of a compressor rotor with blade sections with NACA A(sub 2)I(Sub 8b) mean lines and 65-series thickness distributions in Freon-12 gas. Results regarding blade loss, angle of attack associated with minimum loss, peak efficiencies, and comparison with other transonic rotors are provided.

Internal performance of an XJ79-GE-1 variable ejector was experimentally determined with the primary nozzle in two representative after-burning positions. Jet-thrust and air-handling data were obtained in quiescent air for 4 selected ejector configurations over a wide range of secondary to primary airflow ratios and primary-nozzle pressure ratios. The experimental ejector data are presented in both graphical and tabulated form.

From Introduction: "In this report two-stage-turbine efficiency characteristics are analyzed as a function of work and speed requirements in terms of the effect of changing the required mean-section velocity diagram. The fundamental assumptions and limits used in reference 2 and 3 are also used herein."

Report presenting flight testing and analog-computer studies using flight-test results of a swept-wing jet fighter in the landing condition to determine the factors that influence a pilot to select the minimum approach speed for carrier-type landings. Many factors that influenced the pilot occurred in approximately the same speed range, and the quantitative determination of the influence of each factor was not possible. Results regarding measurement of airplane and engine characteristics, field-carrier landings, and analog simulation of airplane and hypothetical autopilot in high-dip maneuver at constant thrust are provided.

"Rocket-boosted free-flight tests of two models of an airplane configuration having a 45 degree swept wing and a low horizontal-tail position have provided lateral stability derivatives and control effectiveness data for a Mach number range from 0.8 to 1.7. The experimental lateral stability derivatives presented are corrected to rigid conditions and compared with theoretically calculated rigid derivatives. The results are presented without detailed analysis" (p. 1).

Report presenting the results of a free-flight investigation to determine the effect of wing warp on the lift, drag, and static longitudinal stability characteristics of a low-drag aircraft with an arrow wing of aspect ratio 1.86. Results regarding the trim, drag, lift-drag ratios, and normal force and pitching moment are provided.

Report presenting an investigation to determine the effects of initial subsonic diffusion rate, variable geometry, and throat boundary-layer control on the performance of an axisymmetric double-cone inlet. Major gains in performance at higher Mach numbers were obtained with boundary-layer control in the form of a ram scoop at the throat. Results regarding the effect of internal-area distribution, effect of spike translation, and effect of throat boundary-layer control are provided.

"The linearized theory of Tulin and Burkart for two-dimensional supercavitating hydrofoils operating at zero cavitation number is applied to the derivation of two new low-drag configurations. These sections were derived by assuming additional terms in the vorticity distribution of the equivalent airfoil; in particular, three and five terms were considered. A simplified calculation of the location of the cavity boundary streamline for arbitrary configurations is also presented" (p. 1).

Report presenting a low-speed wind-tunnel investigation of a high-wing airplane with an aspect ratio of 6.75 and 36 degrees of sweepback on the quarter-chord line in order to determine the lift increments obtainable with area-suction flaps. Comparisons were made to the slotted flaps normally used. Results regarding the flap lift, maximum lift and stability, and boundary-layer control requirements are provided.

Report presenting flight tests over a range of Mach numbers to study the effects of a simulated afterburning turbojet engine on the gross longitudinal flight characteristics of two geometrically identical models of a swept-wing fighter-type configuration. Results regarding the trim characteristics, lift, pitching moment, dynamic stability, and drag are provided.