An analysis has been made of available experimental data to show the effects of most variables that are predominant in determining base pressure at supersonic speeds. Two dimensional bases and bases of bodies of revolution, restricted to turbulent boundary layers, are covered.

Report presenting an experimental investigation to determine the effect of rotor leading-edge sweepback on the aerodynamic performance of a transonic turbine. Using an unmodified stator with the modified rotor resulted in large incidence angles at the rotor mean and tip sections.

From Summary: "A flight investigation was conducted to determine the effects of inlet modification and rocket-rack extension on the longitudinal trim and low-lift drag of the Douglas F5D-1 airplane. The investigation was conducted with a 0.125-scale rocket-boosted model between Mach Numbers of 0.81 and 1.64. This paper presents the changes in trim angle of attack, trim lift coefficient, and low-lift drag caused by the modified inlets alone over a small part of the test Mach number range and by a combination of the modified inlets and extended rocket racks throughout the remainder of the test."

Report presenting an investigation of the zero-lift-drag characteristics of nine symmetrical airfoils at a range of Mach and Reynolds numbers. Results regarding pressure and force data are also provided.

Report presenting an investigation of a wing swept back 35 degrees in combination with one basic body and three modified bodies at a range of Mach numbers from 0.60 to 1.20. Results regarding force studies and pressure studies are provided. The bodies modified according to the Kuchenmann ring-vortex method resulted in superior aerodynamic characteristics except with regard to zero-lift drag at high supersonic Mach numbers.

Report presenting an investigation at low speeds of the static-stability characteristics of a simplified model of an unusual configuration. The model had three identical triangular airfoils of low aspect ratio. Results of tests of the simplified model of the configuration are presented for a large range of angles of attack and sideslip.

Report discussing an investigation of the supersonic area rule using rocket-propelled zero-lift models of straight wing-body configurations at a range of Mach and Reynolds numbers. The body was modified with symmetrical indentations according to area-rule considerations in order to reduce wave drag. The indentations were found to have an effect at Mach numbers 1.10 and 1.41 but did not have any benefit above Mach number 1.3.

Report presenting a flight investigation using a rocket-powered model to evaluate the roll-rate stabilization of the Naval Ordnance Test Station SIDEWINDER missile, which uses aerodynamic damping by gyro-actuated rollerons. Dynamic roll instability was found to occur in flight.

Memorandum presenting an investigation in the 20-foot free-spinning tunnel on a 1/25-scale model of the McDonnell F3H-2N airplane. The effects of control settings and movements on the erect and inverted spin and recovery characteristics of the model were determined for the clean condition. Results regarding erect spins, engine gyroscopic moments, inverted spins, spin-recovery parachute, and landing condition tests are provided.

Memorandum presenting an investigation of the effect of fuel composition and boiling point on the performance of the type of I-16 jet-propulsion engine. Testing occurred with 14 fuels embodying different types of hydrocarbon and with a range of boiling points. The results indicated that fuel composition and boiling range have a negligible effect on engine thrust, rotor speed, and gas temperatures for the principal types of hydrocarbon fuel when used for short periods of time.

Report presenting an investigation of liquid-film cooling at a variety of air temperatures and Reynolds numbers. Results regarding the effect of coolant flow per circumferential length on liquid-cooled length, correlation of heat transfer from hot gas to liquid film for constant coolant flow per circumferential length, and generalized plot of film-cooling data based on heat-transfer correlation at constant coolant flow per circumferential length are provided.

Report presenting a study of the effect of fuel properties on carbon deposition in jet-propulsion engine combustors using seven fuels: kerosene, Diesel fuel oil, toluene, xylene, 62-octane gasoline, a commercial solvent, and AN-F-32 (JP-1) in an I-16 engine at static sea-level conditions and constant rotor speed. Results regarding the reproducibility of data, reduced exhaust-jet-nozzle area, and fuel comparison are provided.

The results of an investigation of the effects of leading-edge chord-extensions and extensible leading-edge flaps on the low-speed aileron characteristics of a 52 degrees sweptback wing with circular-arc airfoil sections are presented. A description and illustrations of the vortex flow as it passes over the wing are included. The investigation was conducted at Reynolds numbers of 5.5 times 10(exp 6) and 1.3 times 10(exp 6) and corresponding Mach numbers of 0.11 and 0.065 for an angle-of-attack range of 0 degrees through stall.

Report presenting the lateral-control characteristics of two spans of spoiler and flap-type ailerons on an unswept wing with an aspect ratio of 2.5 and hexagonal airfoil sections. Measurements of rolling moments, yawing moments, aileron hinge moments, normal forces, and balance-camber pressures for various configurations of the wing.

An analysis has been made of the characteristics of several cooling cycles suitable for cockpit cooling of supersonic aircraft. All the cycles considered utilize the difference between dynamic and ambient static pressure to actuate the cooling system and require no additional power source. The results of the study indicate that as flight speeds become greater, increasingly complex systems are required to reduce the altitudes above approximately 35,000 feet, a system composed of an externally loaded expansion turbine in conjunction with a supersonic diffuser would maintain tolerable ventilating air temperature, at least up to a flight Mach number of 2. The most complex system considered,composed of compressor, intercooler, and expansion turbine with the intercooler cooling air decreased in temperature by expansion through an auxiliary turbine is capable of maintaining a ventilation air temperature less than ambient temperature up to a flight Mach number of 3.7.

Report presenting a blade-vibration and rotating-stall survey on a production turbojet engine with a 13-stage axial-flow compressor with a pressure ratio of 7 and an air flow of 120 pounds per second. Results regarding stall patterns, maximum vibratory stresses, and location of the stall zones are provided.

The structural damping in the torsion mode of vibration of a series of untwisted, laminated thin beams simulating propeller blades is presented. The number of lamination were varied, as well as the bonding material and the method of joining lamination. Application of the data to the calculation of the minimum flutter speed of thin propeller blades indicates that appreciable gains in the minimum flutter speed may be obtained for laminated blades using a Cycleweld bond.

Memorandum presenting an investigation to determine the static longitudinal and lateral stability and control characteristics of an airplane configuration with a trapezoidal wing with modified hexagonal airfoil section and tail surfaces with 5 degrees semiangle wedge sections carried out in the 11-inch hypersonic tunnel.

Memorandum presenting a theoretical study of the effect of limiting the deflection and rate of deflection of the control surface on the normal acceleration and roll response to step commands for a representative, automatically controlled, supersonic, tailless interceptor. Results regarding pitch, roll, and some general comments are provided.