Flight tests were conducted to determine the effect of length of a conical windshield on the drag of a bluff body moving at supersonic speeds. A comparison is made between results obtained and results of previous drag tests of body-windshield combinations.The effect of increasing the length of the windshield is discussed.

Report presenting an investigation to determine the effects of plan-form taper on the aerodynamic characteristics of a series of symmetrical, unswept wings with thicknesses of 8-percent chord. The wings were tested with four different bodies of revolution over a range of Mach numbers. Results regarding the lift, drag, pitching-moment, lift-curve slope, lift-drag ratio, and pitching-moment curve are provided.

Report presenting testing on the first of a series of flutter rockets, designated the NACA FR-1-A, which was tested with two identical swept wings. Results regarding the launching, flight, and wing failure are provided.

Report presenting a study of the altitude-starting limits of a production turbojet engine with an axial-flow compressor and a multiple through-flow combustor. The ignition limits, flame-propagation limits, and acceleration limits of the engine were improved to increase the starting limits to relatively high altitude.

"An investigation has been conducted in the Langley 20-foot free-spinning tunnel to determine the spin and recovery characteristics of a 0.057-scale model of the modified Chance Vought XF7U-1 airplane. The primary change in the design from that previously tested was a revision of the twin vertical tails. Tests were also made to determine the effect of installation of external wing tanks" (p. 1).

Report presenting drag and longitudinal trim characteristics at low lift of a low-tail version of the North American YF-100A airplane as obtained from the flight test of a 0.11-scale rocket model at a range of Mach numbers. Longitudinal stability data and some qualitative damping-in-pitch data are also provided.

Report presenting longitudinal trim and drag at low lift of the North American YF-100A airplane at a range of Mach numbers as obtained with rocket-propelled models for an airplane, with the horizontal tail removed, and with wing removed conditions. Results regarding drag, longitudinal trim, longitudinal stability, and flutter and buffet are provided.

From Introduction: "As a part of the comprehensive investigation of the XJ34-WE-32 engine conducted in the NACA Lewis altitude wind tunnel, the over-all-performance was determined over a range of altitudes and flight Mach numbers. Other phases of the investigation are reported in reference 1. The results are given in tables and also in graphical form to show the trends of engine performance associated with changes of altitude, flight Mach number, and exhaust-nozzle area."

Memorandum presenting a theory for evaluating the mutual interference between a wing and tip tank as extended to apply to store-pylon configurations. By using the theory and the flow-field formulas of a previous report, theoretical store-pylon side-force estimates have been made for a number of store-pylon configurations. Results regarding the theory for store-pylon side force, scope of test configurations, contribution of store and pylon to combined load, effect of store spanwise location on the store-pylon side-force coefficient, effect of pylon sweep and store chordwise location, effect of sideslip on the store-pylon side-force coefficient, effect of fins on store side-force coefficient, and interference effects between inboard and outboard stores 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 discussing a flight test on a rocket-boosted canard aircraft with 60 degree delta lifting surfaces, twin normal-shock-type side inlets, and twin vertical tails. The drag, longitudinal stability, and duct performance data were obtained for a range of Mach and Reynolds numbers.

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.

Report presenting an investigation for stationary turbine blades with 10 tubes and 13 fins forming the internal heat-transfer surfaces in order to accurately predict local turbine blade temperatures. Results regarding the comparison of calculated and measured midchord blade temperatures, comparison of calculated and measured temperatures near blade trailing edge, comparison of calculated and measured temperatures near the blade leading edge, the influence of errors in calculated temperatures on design considerations, and an application of the analysis to other blade configurations are provided.

Memorandum presenting a study of two jet-noise-suppression devices consisting of teeth projecting into the jet stream was conducted on a current axial-flow turbojet engine. The sound fields obtained with the toothed devices showed a slight reduction in maximum sound pressure level, compared with the sound field from a standard nozzle.

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 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 testing of two NACA two-blade propellers at a range of blade angles and Mach numbers. The effect of compressibility and design section camber are presented for each propeller. The results indicated that if the outboard sections of a propeller are the thinnest, the design of the propellers should incorporate loading distribution that is concentrated in the tip sections.

Report presenting an investigation of the effect of inlet-air temperature on the combustion efficiency of a 16-inch ram-jet engine in a connected-pipe installation. The engine was operated over a range of fuel-air ratios with several different combustor configurations and two fuel types. Configurations tested included a sloping baffle and a can-type combustor in three configurations.

Report presenting a connected-pipe investigation to evaluate a can-type combustor configuration and to develop the configuration to give a wide operable fuel-air ratio range of high combustion efficiency. Results regarding the wind-tunnel tests and connected-pipe tests are provided.

Report presenting the achievement of supersonic inlet stabilization for Mach numbers up to approximately 2.0 by careful consideration of the possible buzz-triggering conditions. Results regarding the inlet flow-stabilization techniques, variable-geometry techniques for stable flow regulation, and effect of turbojet engine on inlet stability are provided.

"This paper presents the results of flight tests to determine the lateral and directional stability and control characteristics of the Grumman F8F-1 airplane with three vertical-tail configurations. The data presented herein have no bearing on the performance characteristics of the airplane, which were not measured but which were considered to be exceptionally good. The conclusions reached regarding the lateral and directional stability and control characteristics are summarized in this report" (p. 1).

An investigation is being conducted to determine the feasibility of studying aileron buzz by means of the wing-flow method. Two semispan models which had an aspect ratio of 6 and a taper ratio of 2 with quarter-chord half-span mass-balanced ailerons have been used. One had an NACA 23012 airfoil section and the second, an NACA 65-212 airfoil section. The ailerons on both models were subject to buzz over a small range of Mach number near 0.9. Data obtained by wing-flow testing agreed reasonably well with full-scale flight results.

Report presenting an investigation at Mach number 1.61 of the effects of chordwise fences and attached tabs on the hinge-moment characteristics of a half-delta tip control mounted on a 60 degree delta wing. Testing occurred over a range of angles of attack and control deflection. Results indicated that, in general, the effect of fences was to improve the linearity of hinge-moment curves and increase the negative values of slope parameters of hinge moment against control deflection and angle of attack.

"The results of an experimental investigation made for the purpose of developing suitable jet-engine nacelle designs for a high-speed medium bomber are presented. Two types of nacelles were investigated, the first enclosing two 4000-pounds-thrust jet engines and a 65-inch-diameter landing wheel and the second enclosing a single 4000-pounds-thrust jet engine. Both types of nacelles were tested in positions underslung beneath the wing and centrally located on the wing" (p. 1).