From introduction: This report details the conceptual design of a 100 kw gas cooled reactor power plant of the type that would satisfy the electrical and space heating load of the Air Force distant early warning stations and might find application at other remote bases.

The purpose of this report is to present a conceptual design study on a low power electrical and heat generating plant powered by nuclear energy. The nuclear reactor used in this study is the homogeneous circulating fuel type.

For a body consisting of a fineness-ratio-3 ogival nose tangent to a cylindrical afterbody 7.3 diameters long, pitot-pressure distributions in the flow field, pressure distributions over the body, and downwash distributions along a line through the vortex centers have been measured for angles of attack to 20 degrees. The Reynolds numbers, based on body diameter, were 0.15 x 10 to the 6th power and 0.44 x 10 to the 6th power. Comparisons of computed and measured vortex paths and downwash distributions are made. (author).

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.

An investigation has been conducted at the Langley 4- by 4-foot supersonic pressure tunnel at a Mach nmber of 2.01 to determine the aerodynamic characteristics of several configurations of a model of a 45 deg swept-wing airplane. The basic configuratin had a wing with 45 deg sweepback at the quarter-chord line, aspect ration 3.2, taper ration 0.468, NACA 65A005.5 sections just outboard of the inlet and NACA 65A003.7 sections at the tip. The wing was mounted slightly above the body center line and an all-movable horizantal tail was located slightly below the extended chord line of the wing. Tre design incorporated twin wing-root supersonic inlets ducted to a single exit at the base of the fuselage. The configurations investigated included an extended nose length, a bumped-fuselage afterbody, an inlet droop, an lncreased wing aspect ratio, and a revised canopy shape. Configurations employing the wing of increased aspect ratio of 3.7, which constituted the bulk of the tests, produced about a 10-percent increase in lift and in longitudinal stability as compared with the basic wing of aspect ratio 3.2. There was a slight but masurable increase in minimum drag and maximum lift-drag ratio.

Memorandum presenting rolling stability derivatives for a complete model with a low-aspect-ratio wing and tail surfaces for a Mach number range of 0.70 to 0.94 and for an angle-of-attack range from 0 to 13 degrees for the lower Mach numbers. The model test results indicated regions of neutral or unstable damping in roll at Mach numbers of 0.85 and 0.90 in the higher angle-of-attack range for the basic model. Results regarding damping in roll, yawing moment and lateral force due to rolling, and aileron characteristics are provided.

Memorandum presenting the Bell X-5 research airplane tested at 58.7 degrees sweepback during the program to determine the characteristics of a variable-sweep fighter airplane at transonic speeds. This paper includes the stability and control characteristics in the stable lift range up to Mach numbers near 1.0 at an altitude of 40,000 feet and to slightly lower Mach numbers at altitudes of 25,000 feet and 15,000 feet. Results regarding general comments, static stability and control characteristics, and longitudinal dynamic stability are provided.

The conversion of UNH to UF4 and UF6, utilizing moving-bed techniques, is being studied; sufficient progress has been made that an evaluation of the process is warranted. The procedures under study, the Fluorox Process, have three major advantages: (1) substitution of HF for high-cost fluorine, (2) considerable reduction in HF requirements, and (3) marked reduction in plant-size and mechanical complexity.

Report presenting the lateral stability and control characteristics were investigated on the Convair XF-92A delta-wing airplane during the flights of the NACA research program. The investigation included sideslips, aileron rolls, and rudder pulses at a range of altitudes and indicated speeds. The lateral handling characteristics appear satisfactory when viewed in terms of gradually increasing sideslips, lateral control effectiveness, and period, and damping.

Report presenting an investigation in the 4- by 4-foot supersonic pressure tunnel at a Mach number of 1.41 to determine the static stability and control and drag characteristics of a model of a 35 degree swept-wing airplane. The effects of alternate fuselage shapes, wing camber, wing fences, and fuselage dive brakes on aerodynamic characteristics were also investigated.

Report presenting a wind-tunnel investigation to determine the effect of lowering the wing from the top of the fuselage to the bottom of the fuselage on the longitudinal characteristics of a wing-fuselage and a wing-fuselage-tail combination with the horizontal tail at various heights above the plane of the wing. The effects of wing height on the longitudinal characteristics of the model were small.

Report presenting an investigation to determine the effect of lowering the wing from the top of the fuselage to the bottom of the fuselage on the longitudinal characteristics of a wing-fuselage and wing-fuselage-tail combination with the horizontal tail at various heights above the plane of the wing. Testing occurred at a range of Mach and Reynolds numbers.

Report presenting an investigation of the low-speed static lateral stability characteristics of a complete model with a series of M- and W-wings. They were modified from a basic 45 degree swept wing and were designed to cover a range of spanwise locations of the sweep discontinuity.

Report presenting an investigation at low speed in the 300 mph tunnel to determine the static aerodynamic forces and moments on a missile model during simulated launching from 25-percent-semispan and wing-tip locations of a wing-fuselage combination. Results regarding the differences in location and effects induced by the fuselage are provided.

Report presenting a flight investigation at a range of altitudes to determine the wing loads on the Convair XF-92A airplane over the lift range of the airplane at subsonic and transonic speeds. Theoretical lift-curve slope for a delta wing was calculated and compared with the flight data at a Mach number of 0.75.

Memorandum presenting a low-speed wind-tunnel investigation conducted to study the effects of pylon-mounted wing tanks and speed brakes on the static stability characteristics of a model with sweptback wing and tail surfaces. The wing of the model was of aspect ratio 3.45 and was swept 40 degrees at the quarter-chord line. Results for the basic configuration and modifications to the basic configuration are provided.