Report presenting an analysis to determine the effect of increasing the fin-chord length while holding the span constant on the lift and longitudinal static stability of fin-body combinations. Rectangular and triangular fins with spans of 2 and 3 body diameters in combination with a fineness-ratio-14 ogive-cylinder body were tested.

Report presenting an investigation to determine the effect of a Küchemann type fuselage modification designed to reduce the interference velocities at the wing-fuselage junctures on the longitudinal characteristics of a wing-fuselage-tail combination and several wing-fuselage combinations. The tests were made through an angle-of-attack range at Mach numbers varying from 0.60 to 0.92 at a Reynolds number of 2 million. Results regarding the 64A wing-fuselage-tail combination, four-digit wing-fuselage combinations, and effects of Mach number are provided.

The compressor case of a 13-stage axial-flow compressor was modified to incorporate air-bleed systems over the fifth and tenth rotor stages. Rotating stall-exited rotor-blade vibrations were measured in the first and second stages at 60 and 68 percent of rated speed, respectively. Either the fifth- or the tenth-stage bleeds satisfactorily eliminated the peak vibratory stresses.

Report presenting an analysis of horizontal-tail loads on a flexible multi-engined jet-propelled swept-wing medium bomber to determine the tail lift-curve slope due to tail angle of attack, tail-lift curve slope due to elevator deflection, tail pitching-moment coefficient due to elevator deflection, downwash factor, and elevator effectiveness factor. The effect of the stabilizer, effects of elevator flexibility, and effects of wing stability are presented.

Performance of supersonic ramp-type side inlet with ram-scoop throat bleed and varying fuselage boundary layer removal at low supersonic speeds.

Report presenting a method for analyzing the effects of inertia and aerodynamic cross-coupling on the response of airplanes in rolling maneuvers. The method is based on the concept that variations in the calculated steady-state angle of attack and sideslip with roll rate give a measure of the onset and degree of roll coupling. An evaluation of this concept from several different perspectives is also provided.

From Introduction: "Experimental investigations of the combustion characteristics of diborane, pentaborane, and pentaborane-hydrocarbon blends in modified turbojet combustors have been conducted at this laboratory at the request of the Bureau of Aeronautics, Department of the Navy, as part of Project Zip. Results of these single-combustor tests are presented in references 2 to 5."

"Preliminary tests made by the General Electric Company indicated that aerodynamic loads might cause large enough distortions in the thin sheet-metal rings of a nuclear fuel element to result in structural failure. The magnitude of the distortions in a test fuel element was determined from strains measured with airflow conditions simulating those expected during engine operation. The measured vibratory strains were low enough to indicate the improbability of failure by fatigue. A conservative estimate of the radial deflection that accompanied peak strains in the outer ring was +0.0006 inch" (p. 1).

Memorandum presenting an investigation conducted in the 7- by 10-foot tunnel of the static longitudinal and lateral stability characteristics of a model with a 45 degree sweptback wing of aspect ratio 4 and with several different tail arrangements. The tail configurations studied had unswept, rectangular surfaces and included a T-tail and conventional fuselage-mounted horizontal and vertical tails. Results regarding wing-fuselage characteristics, effects of afterbody shape, effect of tail configuration on stability, and comparison of swept- and unswept-wing configurations are provided.

Report presenting a five-degree-of-freedom analysis of aircraft maneuvering stability, which showed that gyroscopic moments due to engine rotor momentum produced considerable rolling asymmetry for certain values of stability derivatives and flight conditions. Results regarding the altitude effects, Mach number effects, initial load factor, effective dihedral, static stability, roll velocity, and comparison with simplified longitudinal- and lateral-mode theory are provided.

Memorandum presenting a preliminary and theoretical investigation of the effect of velocity diagram on inlet total-pressure distortions through single-stage subsonic axial-flow compressors for incompressible flow. A theoretical investigation was used to determine proper velocity diagrams and then the wake of a 1/4-inch-diameter rod was measured upstream of the rotor. The tests indicated that the derived equation will estimate the downstream distortion with reasonable accuracy for inlet total-pressure distortion which extends far enough circumferentially to alter the static-pressure field in the blade passage.

Report presenting an investigation to determine the internal-flow characteristics of three top-mounted scoop inlets with rounded lips. The inlets were mounted at the leading edge, midchord, or trailing edge of a high 45 degree sweptback 6-percent-thick wing. Results regarding the total pressures at inlet, flow distortions at inlet measuring station, and boundary-layer control are presented.

"An investigation has been completed in the Langley 20-foot free-spinning tunnel on a l/18-scale model of the Ryan X-13 airplane to determine its spin, recovery, and tumbling characteristics, and to determine the minimum altitude from which a belly landing could be made in case of power failure in hovering flight. Model spin tests were conducted with and without simulated engine rotation. Tests without simulated engine rotation indicated two types of spins: one, a slightly oscillatory flat spin; and the other, a violently oscillatory spin" (p. 1).

Report presenting testing of a modified 1/10-power nose shape in free flight at Mach numbers up to 6.7. Measured heating rates were presented and compared with calculated values. Results regarding transition and comparison with previous investigations are provided.

Memorandum presenting a discussion of oscillating flap-type and all-movable controls with particular emphasis on the aerodynamic forces and moments at transonic speeds. Hinge-moment results from recent wind-tunnel and rocket-powered-model tests are summarized for trailing-edge flap-type controls to illustrate the effects of control hinge-line position and profile shape on one-degree-of-freedom flutter of this type of control.

Report presenting an investigation of a five-stage rocket model at mach number 13.9 and an altitude of 81,500 feet. Temperatures were measured at 12 stations on the flat-face copper nose. Heating rates calculated from temperature time histories are compared to theoretical predictions of the rates.

Memorandum presenting a study of the effects of automatic augmentation or controlling systems on the tail loads experienced in rolling maneuvers and in pitch-up. The results were calculated on an analog computer and the equations of five degrees of freedom were used for the rolling maneuvers and three degrees of freedom for pitch-up.

Report presenting an investigation in the 10- by 10-foot supersonic wind tunnel on a 16-inch ramjet equipped with an afterburner and using gaseous hydrogen for the primary and afterburner fuels. The primary nozzle had a contraction ratio of 0.6 and the exit nozzle had a contraction ratio of 0.9. The results indicated that at a constant diffuser-exit Mach number, afterburner operation produces more than twice the thrust available without afterburning.

Report presenting an outline of a proposed statistical program to collect data for the establishment of more realistic maneuver-loads design criteria. Some sample experimental data are also included to indicate possible methods of statistical analysis and the potential sample size needed for the program.

Report presenting an investigation in the high speed tunnel of some effects of wing height and angle of attack on the vertical-tail pressure distribution of a complete model in sideslip at high subsonic speeds. The 45 degree swept wing had an aspect ratio of 4, a taper ratio of 0.30, and NACA 65A006 airfoil sections parallel to the model plane of symmetry. Results regarding vertical-tail loads and vertical-tail center of pressure are provided.

Memorandum presenting a study to determine locations of pressure sensors for controlling the spike position of a blunt-lip, axisymmetric inlet with internal contraction. The inlet performance was determined at Mach numbers of 0.63 and 1.5 to 2.0 for airflow schedules corresponding to those of a given turbojet engine over a wide range of ambient temperatures. The use of the ratio of a throat static pressure to either a local total or the spike-tip total pressure provided a signal that could set nearly maximum pressure recoveries at Mach numbers of 1.7 to 2.0 and within 6 percent of maximum recovery at Mach 1.5.

Memorandum presenting a flight test of a pentaborane-fueled air-launched ramjet engine with convergent-divergent exhaust nozzle. The engine was boosted to a Mach number of about 2.00 by a small internally housed rocket; the ramjet then accelerated to a maximum free-stream Mach number of 3.02 at an altitude of 29,500 feet.

Report presenting two turbine stator configurations designed to investigate the effect on turbine performance of either reducing or eliminating stator-blade wakes, secondary-flow loss accumulations, and circumferential variations in total pressure at stator exits. Rotor performance with the standard stator with spacer was better than what was obtained with the standard configuration.

Memorandum presenting two turbine stator configurations designed to investigate the effect on turbine performance of either reducing or eliminating stator-blade wakes, secondary-flow loss accumulations, and circumferential variations in total pressure at the stator exits. Results regarding stator surveys, overall performance with the semivaneless stator, overall performance with the standard stator with spacer, rotor-exit surveys, and rotor-blade momentum loss are provided.