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.

For constant-mechanical-speed operation, the two-spool thrust values are as great as or greater than the one-spool thrust values over the entire flight range considered, while the specific fuel consumption for the two engines agrees within 1 percent. The maximum difference in thrust occurs at Mach 2.8 in the stratosphere, where the two-spool thrust advantage is about 9 percent for operation with the after burning.

Report presenting a rotating total-pressure survey rake to obtain wake measurements of a compressor rotor. Results indicated that there was a considerable radial flow of the inboard-blade boundary layer and little radial flow of the inner casing boundary layer. Results regarding the variation in total-pressure-loss distribution with Mach number, variation in total-pressure-loss distribution with angle of attack, contour plots, spanwise variation in total-pressure-loss coefficient, variation of low-speed momentum loss coefficient withe angle of attack, and variation of momentum-loss coefficient with Mach number are provided.

Report presenting the longitudinal and lateral stability characteristics of a 40 degree swept-wing fighter model with and without horizontal tails of 0 degrees and 22.5 degrees negative dihedral for a range of Mach numbers, angles of attack, and sideslip.

Report presenting testing on two three-blade supersonic propellers in order to determine the effects of trailing-edge bluntness on the performance of a supersonic propeller. Results regarding propeller thrust, power, effects of Mach number and advance ratio on maximum efficiency, and a comparison to a previous test are provided.

Report presenting the stall characteristics of the J71-A2(X-29) turbojet engine as determined in an altitude test chamber. When the normal high-speed configuration of bleeds closed, inlet guide vanes open was operated in the low-speed range, the stall-limit line intersected the operating line at 4067 and 4630 rpm. Results regarding compressor performance at steady state and stall and fuel flow at steady state and stall are provided.

Report presenting a brief experimental investigation of a method for designing fuselage side air inlets with high internal total-pressure recovery and zero spillage drag at a specified design inlet mass-flow ratio. With a scoop designed according to the concept, near-zero spillage drag can be attained at the design inlet mass-flow ratio through a range of Mach numbers. Results regarding pressure recovery and drag due to the scoop are provided.

The internal drag of an axial-flow turbojet engine with the rotor locked in place to prevent windmilling and with the engine windmilling was obtained over a range of simulated Mach numbers. The corrected internal drag of the engine with the locked rotor was 210 pounds or only 46 percent of the windmilling drag at a flight Mach number of 0.8.

Memorandum presenting an investigation of the variations with Mach number and angle of attack of the dynamic rolling-moment characteristics of a slender body of revolution in combination with a cruciform tail in the 6- by 6-foot supersonic wind tunnel. Oscillograph records of the instantaneous rolling moment of the model were obtained for Mach numbers of 0.90, 1.20, 1.40, 1.53, 1.60, and 1.70 at a constant free-stream Reynolds number. Results regarding dynamic rolling moments and visual flow studies are provided.

Report presenting an investigation in the high-speed tunnel for a range of Mach numbers to determine the effects of spoiler projection on the aerodynamic characteristics of a wing-fuselage a sweptback quarter-chord line. Lift, drag, rolling, pitching, and yawing moments of the model with a wing panel equipped with 50-percent-semispan inboard spoilers located at the 70-percent-chord line.

Report presenting flight measurements using the Douglas D-558-II airplane in order to determine the longitudinal stability and control characteristics in steady and accelerated flight. Results are given for various flap positions, especially in regards to degrees of instability present.

Report presenting aerodynamic parameters and operation techniques for a fin-actuated jet-vane system for the stabilization of a rocket-powered model by means of static and flight tests. Static testing was used to obtain lift, hinge moment, and center-of-pressure location of the jet vane, while the longitudinal stability characteristics of a simplified model were determined from the results of a flight test.

Report presenting an investigation of the effect of wing-tip mounted tanks on the rolling characteristics of a wing, aspect ratio 3 with the quarter-chord line swept back 35 degrees, through a range of Mach numbers and angles of attack using the free-roll method.

Report presenting a method for predicting the stability of automatically controlled aircraft by comparing the calculated frequency-response curves for the aircraft and experimentally determined frequency-response curves for the automatic pilot. The method is applicable only to stabilization in roll. It can be used to establish the specifications of performance required for the automatic control device for pilotless aircraft designed as missiles.

From Summary: "At the request of the Air Material Command, Arm Air Forces, an investigation was conducted at the NACA Cleveland laboratory to determine the performance characteristics of the XJ-41-V turbojet-engine compressor. The complete compressor was mounted on a collecting chamber having an annular air-flow passage simulating the burner annulus of the engine and was driven by an electric motor. The compressor was extensively instrumented to determine the overall performance of the compressor, the characteristic performance of each of the compressor components, the state of the air stream in the simulated burner annulus, and the operation of the compressor bearings."