Report presenting some work done to meet the requirements of missile control designers for more powerful controls and for lower hinge moments. Some testing regarding all-movable wings and reducing hinge moments is described.

Memorandum presenting an investigation of the possibility of correlating airfoil section data with measured pressure distributions over a 45 degree sweptback wing in the Mach number range from 0.50 to 0.95 at a free-stream Reynolds number of approximately 2 million. The wing had an aspect ratio of 5.5, a taper ratio of 0.53, NACA 64A010 sections normal to the quarter-chord line, and was mounted on a slender body of revolution. Results regarding correlation of chordwise pressure distributions, correlation of magnitudes of section loads, and wing-body characteristics are provided.

Report presenting longitudinal and lateral-directional frequency responses determined from transient flight data excited by control pulses for a large flexible swept-wing airplane over a wide range of flight conditions. The effects of structural modes on the frequency response at various locations on the airplane are shown. Results regarding the low-frequency response, longitudinal transfer-function coefficients, lateral response, lateral-directional transfer-function coefficients, experimental technique, and high-frequency responses are provided.

Report presenting an investigation of the effects of streamwise gaps between wing and body on the lift and pitching moments of a moderately slender wing-body combination at Mach number 1.4 and compared with available theoretical results. The investigation included tests in which the angle of attack is varied with the all-movable wing at zero deflection and also tests at which the angle of wing deflection is varied with the body at zero angle of attack.

Report presenting an investigation at Mach number 1.62 of a series of triangular wing and body combinations to determine the interference lift, drag, and pitching moment. Testing was conducted on seven flat-plate triangular wings of varying scale, four with a half-apex angle of 30 degrees and three with a half-apex angle of 45 degrees. Results regarding wing alone, wing in the presence of the body, basic quantities for interference evaluation, interference quantities, and contributions of both types of quantities are provided.

"Some aileron load characteristics for three thin wings varying in sweep have been presented for Mach numbers from 0.80 to 1.05. For the transonic Mach number range, shock effects exert a large influence on the loading, but the exact location of each shock for a specific wing design cannot be cataloged at the present time. It is shown, however, that the aileron loading, although greater in magnitude than at subsonic speeds, nevertheless varies in as uniform a fashion as at subsonic speeds" (p. 1).

Report presenting an investigation to determine the possibility of using simplified procedures for the estimation of control loads at supersonic speeds. The results indicated that relatively simple procedures are possible for the estimation of loadings on flap-type controls at supersonic speeds for cases when no flow separation occurs ahead of the hinge line.

A transistorized binary counter circuit is described that operates over a temperature range of -65 degree F to +165 degree F. the supply voltage is 28 + 4 volts and the maximum trigger repetition rate is 5 kilocycles. the binary circuit is pre-settable and resettable by means of a switching arrangement that can be mechanized. Texas Instrument type 904 silicon transistors whose large signal current gain is 2.8 or greater at a -65 degree F can be used in this circuit.

Report presenting a wind-tunnel investigation at subsonic Mach numbers up to 0.9 to measure the root-mean-square variation of the normal forces on 27 NACA airfoil sections. The effects of thickness-chord ratio, camber, location of minimum pressure, and leading-edge radius were investigated.