Report presenting testing of models of rocket-motor fins of the ASROC missile for flutter and divergence in the supersonic flutter tunnel for a range of Mach numbers. Results indicate that both divergence of the overhung leading edge and flutter occur within the sea-level operating conditions of the missile at Mach numbers above 1.0. Results regarding the flutter boundary, type of flutter encountered, possible solutions to flutter problems, and possible effects of nondestructive type of flutter are provided.

Report presenting testing of scale models of rocket-motor fins of the ASROC missile for flutter and divergence in the supersonic flutter tunnel over a range of Mach numbers. Results regarding the flutter boundary, type of flutter encountered, and effects of flutter are provided.

The performance of NACA 65-series compressor blade section in cascade has been investigated systematically in a low-speed cascade tunnel. Porous test-section side walls and for high-pressure-rise conditions, porous flexible end walls were employed to establish conditions closely simulating two-dimensional flow. Blade sections of design lift coefficients from 0 to 2.7 were tested over the usable angle-of-attack range for various combinations of inlet-flow angle. A sufficient number of combinations were tested to permit interpolation and extrapolation of the data to all conditions within the usual range of application. The results of this investigation indicate a continuous variation of blade-section performance as the major cascade parameters, blade camber, inlet angle, and solidity were varied over the test range. Summary curves of the results have been prepared to enable compressor designers to select the proper blade camber and angle of attack when the compressor velocity diagram and desired solidity have been determined.

Report presenting results of flutter testing on three cantilever delta-wing plan forms at a range of Mach numbers. The time and location of flutter and results of the flutter calculations are provided for each of the wings.

Memorandum presenting forces and moments measured at Mach number 1.6 in the 4- by 4-foot supersonic pressure tunnel on bombs of fineness ratios 7.0 and 10.5 in the presence of a swept-wing fighter-bomber airplane configuration for a large number of positions under the fuselage. The results can be used to calculate bomb-drop paths.

Report presenting an investigation of the heat-transfer coefficients (Stanton number and boundary-layer transition) obtained from a free-flight test of a 10 degree total-angle cone with a 1/16-inch tip radius. Testing occurred over a range of Mach numbers from 1.8 to 3.5 and a range of wall-to-local-stream temperature ratios. Results regarding skin temperatures, heat-transfer coefficient, and boundary-layer transition are presented.

Report presenting an investigation of the combined effects of wing taper ratio and low horizontal-tail position on the static longitudinal stability of a 45 degree sweptback wing-body combination with an aspect ratio of 4 at a range of Mach numbers. Results regarding tail-off pitch characteristics, tail-on pitch characteristics, and effective flow characteristics over horizontal tail are provided.

Memorandum presenting an investigation to determine the effects of increase in angle of dead rise on the overall hydrodynamic characteristics of a seaplane having a length-beam ratio of 15 and a wing loading of 120 pounds per square foot. In general, increasing the angle of dead rise from 20 to 40 degrees and 60 degrees improved the trim limits of stability and the range of center-of-gravity positions for satisfactory take-off characteristics.

Report presenting the total-pressure recovery characteristics of three circular internal-compression inlets with translating centerbodies at a range of free-stream Mach numbers. The inlets differed only in the shape of the internal compression contours. Results regarding the maximum pressure recoveries and pressure-recovery characteristics are provided.

Report presenting an investigation at high subsonic speeds to determine the static stability characteristics of a cambered-delta-wing model with wing dihedral angles of 20 degrees and 50 degrees. Results regarding the longitudinal characteristics and lateral characteristics are provided.

Report presenting an investigation to obtain information about the basic aerodynamic characteristics of two vertical-take-off-and-landing jet bomber airplanes, one with a high wing and one with a low wing. Results regarding pitch and sideslip are provided. The high-tail configurations were found to have higher lift-drag ratios for both high- and low-wing models.

Memorandum presenting the Bell X-5 variable-sweep research airplane tested primarily at 58.7 degrees sweepback to determine the characteristics at transonic speeds of a fighter-type airplane with extreme sweepback. Some of the dynamic and static lateral stability characteristics have been discussed previously. Results regarding the lateral control, roll coupling, lateral problems at high lift, wing dropping, rudder oscillation at supersonic Mach numbers, and some pilots' impressions are also provided.

Report presenting the heat transfer and pressures on the lifting surfaces of a 60 degree delta wing with NACA 65A005 profile at angles of attack up to 9 degrees. Results obtained are compared to values obtained from flat-plate theory.

Report presenting an investigation conducted by means of preflight and flight tests to determine the performance of a 50-percent-magnesium 50-percent JP-4 slurry fuel in a twin-engine ramjet test vehicle. Data were obtained over a range of Mach numbers. Although a successful flight test was carried out, the performance obtained from preflight testing was below theoretical values.

Report summarizing research on the strength and creep of aircraft structural elements and components at elevated temperatures. Experimental data for aluminum alloy columns, plates, stiffened panels, and multiweb box beams are presented for temperatures up to 600 degrees Fahrenheit and compared with results predicted from materials data.

The problem of improving operational reliability of turbojet engines is studied in a series of papers. Failure statistics for this engine are presented, the theory and experimental evidence on how engine failures occur are described, and the methods available for avoiding failure in operation are discussed. The individual papers of the series are Objectives, Failure Statistics, Foreign-Object Damage, Compressor Blades, Combustor Assembly, Nozzle Diaphrams, Turbine Buckets, Turbine Disks, Rolling Contact Bearings, Engine Fuel Controls, and Summary Discussion.

"The National Advisory Committee for Aeronautics has conducted a flight test of a model approximating the McDonnell F3H-1N airplane configuration to determine its pitch-up and buffet boundaries, as well as the usual longitudinal stability derivatives obtainable from the pulsed- tail technique. The test was conducted by the freely flying rocket-boosted model technique developed at the Langley Laboratory; results were obtained at Mach numbers from 0.40 to 1.27 at corresponding Reynolds numbers of 2.6 x 10(exp 6) and 9.0 x 10(exp 6). The phenomena of pitch-up, buffet, and maximum lift were encountered at Mach numbers between 0.42 and 0.85" (p. 1).

For a body consisting of a fineness-ratio-3 ogival nose tangent to a cylindrical afterbody 7.3 diameters long, pitot-pressure distributions in the flow field, pressure distributions over the body, and downwash distributions along a line through the vortex centers have been measured for angles of attack to 20 degrees. The Reynolds numbers, based on body diameter, were 0.15 x 10 to the 6th power and 0.44 x 10 to the 6th power. Comparisons of computed and measured vortex paths and downwash distributions are made. (author).

"An investigation was conducted in the Langley 20-foot free-spinning tunnel on a 1/23-scale model of the McDonnell F3H-1N airplane. The effects of control settings and movements upon the erect and inverted spin and recovery characteristics of the model were determined for the clean condition. Spin-recovery parachute tests were also performed. The results indicated that erect spins obtained on the airplane for the take-off or combat loadings should be satisfactorily terminated if full rudder reversal is accompanied by moving the ailerons to full with the spin (stick full right in a right spin)" (p. 1).

Report presenting an investigation to determine the longitudinal stability and afterbody pressure characteristics of the TX-14 and TX-16 special weapons at transonic and supersonic speeds. Results regarding dynamic testing and pressure testing are provided.

The zero-lift damping in roll of the Bell MX-776 missile has been measured by a sting-mounted rocket-model technique at Mach numbers from 0.6 to 1.56. The damping-in-roll data, in general, show no unusual variation with Mach number. Aileron rolling-moment effectiveness derived from these data and previously obtained rolling-effectiveness data appear reasonable,.

Memorandum presenting the use of the hypersonic similarity rule to correlate pressure distributions and wave drags for minimum-drag nose shapes derived by Von Karman and Newton. The computed results have been confirmed by comparison with available experimental data. Wave-drag results for both the Karman and Newtonian shapes are compared with each other and with results for ocnes and circular-arc tangent ogives.

Report presenting a series of fence installations tested on a swept-wing jet airplane to determine their effects on the longitudinal instability, or "pitch-up", encountered in high-maneuvering flight. Longitudinal-stability measurements were made at a variety of Mach numbers with nine fence configurations that varied in chordwise extent and spanwise position. Results regarding longitudinal stability, flow phenomena, buffeting and wing dropping, drag, and low-speed stalls are provided.

Report presenting an investigation to determine the aerodynamic characteristics of two three-blade propellers over a range of blade angles and Mach numbers. The thick-blade propeller was more adversely affected by compressibility than the thin-blade propeller, and the maximum efficiency of the thin-blade propeller was higher than the thick-blade propeller.