The possibility of overshooting the anticipated normal acceleration as a result of the artificial-feel characteristics of the F-89C airplane at a condition of minimum static stability was investigated analytically by means of an electronic simulator. Several methods of improving the stick-force characteristics were studied. It is shown that, due to the lag in build-up of the portion of the stick force introduced by the bobweight, it would be possible for excessive overshoots of normal acceleration to occur in abrupt maneuvers with reasonable assumed control movements. The addition of a transient stick force proportional to pitching acceleration (which leads the normal acceleration) to prevent this occurring would not be practical due to the introduction of an oscillatory mode to the stick-position response. A device to introduce a viscous damping force would Improve the stick-force characteristics so that normal acceleration overshoots would not be likely, and the variation of the maximum stick force in rapid pulse-type maneuvers with duration of the maneuver then would have a favorable trend.

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,.

Report presenting an experimental investigation of the pressure distributions on a hemispherical nose 3.98 inches in diameter, mounted on a cylindrical support, at several Mach and Reynolds numbers. The Reynolds number was based on body diameter and free-stream conditions. Pressure-drag coefficients were calculated and good agreement was obtained with other testing.

Report presenting supersonic-tunnel tests of two models of similar supersonic airplane configurations at Mach numbers of 1.55, 1.90, and 2.32 to determine values of the drag, lift, pitching moment, yawing moment, and side force. The models were similar except for the vertical wing location relative to the body axis and horizontal tail; one had a high wing and one had a low wing. Results regarding the precision of data, Reynolds numbers of tests, results at the different Mach numbers, and Schileren photographs are provided.

"An investigation to determine the performance and operational characteristics of the TG-1OOA gas turbine-propeller engine was conducted in the Cleveland altitude wind tunnel. As part of this investigation, the combustion-chamber performance was determined at pressure altitudes from 5000 to 35,000 feet, compressor-inlet rm-pressure ratios of 1.00 and 1.09, and engine speeds from 8000 to 13,000 rpm. Combustion-chamber performance is presented as a function of corrected engine speed and corrected horsepower" (p. 1).

Memorandum presenting high-speed wind-tunnel tests of four thin NACA 63-series airfoil sections with a design lift coefficient of 0.2 with the uniform-load type of mean camber line to determine the effectiveness of forward movement of the minimum-pressure position in improving the high-speed lift characteristics of low-drag airfoils. Results regarding the tunnel-wall effects, lift coefficient, drag coefficient, and moment coefficient are provided.

"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).

Memorandum presenting the use of the modified slender-body method to predict the lift and moment interference of triangular wing-body combinations adapted to combinations with other than triangular wings. The methods are applied to the prediction of the lit-curve slopes of nearly 100 triangular, rectangular, and trapezoidal wing-body configurations.

Report presenting the use of the modified slender-body method to predict the lift and moment interference of triangular wing-body combinations to evaluate combinations with non-triangular wings. The method is applied to the prediction of lift-curve slopes of nearly 100 triangular, rectangular, and trapezoidal wing-body configurations.

Report presenting the tumbling characteristics of dynamic models of 14 airplane designs in the free-spinning tunnel for various loadings and configurations. Conventional airplanes were not found to tumble, but tailless and tail-first airplanes might depending on the amount of static longitudinal stability. Results regarding the effect of dimensional and mass characteristics, effect of controls, use of parachutes as a tumble-recovery device, accelerations, and possibility of pilot escape are provided.

Report presenting the transonic drag characteristics of a series of wing-body combinations and their component parts using the free-fall method. The configurations examined had wings of various sweeps and thickness ratios mounted on identical bodies of fineness ratio 12.