From Introduction: "The effect of flame-holder and fuel-system design on the burner performance and the effect of altitude and flight Mach number on over-all performance with a fixed-area exhaust nozzle are reported in reference 1 to 4. Altitude performance characteristics of a tail-pipe burner having a converging conical burner section are presented in this report. Tail-pipe burner performance at several flight conditions is given in both tabular and graphical forms and compared with performance of the standard engine and of the tail-pipe burner reported in reference 2."
Memorandum presenting wind-tunnel testing of a jet-engine nacelle on a semispan wing with the leading edge swept back 37.25 degrees made to determine the effects of the nacelle on the aerodynamic characteristics of the wing. In comparison with the force characteristics of the wing alone, the addition of the nacelle to the wing in each position resulted in favorable interference on the maximum-lift and pitching-moment characteristics and in a small increase in drag.
Report presenting an investigation of various external-store configurations on a model of a tailless airplane with a sweptback wing over a range of Mach numbers. The investigation was performed out of a desire to reduce the drag interference caused by external stores as much as possible. Results regarding the aerodynamic characteristics in pitch, lift-drag ratios, effect of Mach number, variation of control effectiveness, aerodynamic characteristics in yaw, and variation of stability parameters are provided.
Report presenting flight measurements in sideslips of the static lateral and directional stability characteristics of the Douglas D-558-II airplane. It is part of an investigation to determine the stability and control characteristics and aerodynamic loads acting on the wing and horizontal tail of an airplane from stalling speed up to a maximum Mach number of 0.90. Results regarding variations of rudder, total aileron, elevator control positions and control forces, aileron position, and aerodynamic hinge moments are provided.
Memorandum presenting an investigation made at a Mach number of 1.93 to determine lift, drag, pitching-moment, and average downwash characteristics of several missile configurations. Five configurations with rectangular wings and tails of various spans were tested; each of the configurations had two locations of the wing relative to the tail.
Report presenting force testing on an NACA 3-(3)(05)-05 eight-blade dual-rotating propeller at a range of blade angles. Results indicated that good efficiencies can be obtained at high subsonic forward Mach numbers by operation at high blade angle. Results regarding the propeller characteristics, individual power coefficients, effect of forward Mach number on the maximum efficiency of the dual propeller, and effect of small changes in the rear-propeller blade angle on the dual-propeller characteristics are also provided.
"Pressure-distribution measurements were made during a lateral-control investigation of a semispan wing with the NACA 0012-64 section and a 20-percent-chord plain aileron. The results are presented as tables of pressure coefficients for Mach numbers from 0.60 to 0.85. No analysis of the results is included" (p. 1).
"A theoretical investigation has been made to determine the effect of nonlinear stability derivatives on the lateral stability of an airplane. Motions were calculated on the assumption that the directional-stability and the damping-in-yawing derivatives are functions of the angle of sideslip. The application of the Laplace transform to the calculation of an airplane motion when certain types of nonlinear derivatives are present is described in detail" (p. 1009).
"The proportional-plus-flicker automatic pilot operates by a nonlinear principle whereby a fast-acting flicker servomotor response is combined with a low-speed proportional servomotor response for the purpose of obtaining supersonic stability and control. Essentially, the autopilot maintains a zero reference about which the output is proportional to the input. However, a flicker response overrides this proportional response at a fixed angle of gimbal displacement on either side of the zero gyroscope reference" (p. 1).
Report presenting the aerodynamic properties of a model of a jettisonable nose section with a circular cross section as determined at low speed from an investigation in the 20-foot free-spinning tunnel. The results indicated that the aerodynamic characteristics of the nose were greatly affected by proximity to the fuselage. Even for a stabilized nose, it may be necessary to eject the nose forward forcibly in order to prevent high accelerations along the backbone of the pilot.
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