Report presenting an investigation in the supersonic pressure tunnel at Mach number 2.01 to study the wake patterns in the lee of bodies at high angles of attack. The configurations tested consisted of two cylindrical body shapes, one circular and one elliptical in cross section, with a fineness-ratio-3.5 ogival nose and a fineness-ratio-6 conical nose. Results regarding vapor-screen photographs, wake characteristics, wake patterns, wake characteristics, and testing with transition strips are included.

Report presenting a determination of the landing contact conditions of the Boeing B-47 airplane using a specially built motion picture camera. A statistical analysis of the sinking speeds and horizontal speeds was carried out on the photographs.

"An investigation to determine the static longitudinal and lateral stability characteristics of a 1/62-scale model of the Bell X-1A has been conducted in the Langley 9-inch supersonic tunnel. tests were made at Mach numbers of 1.62, 1.94, 2.22, 2.40, and 2.62 on the wing-body, wing-body-vertical-tail, and complete configurations. Data are presented for both the body and stability axes. Detailed analysis of the test results is omitted" (p. 1).

Report discussing an investigation of the performance of a three-stage transonic compressor with high stage pressure ratios to investigate problems encountered when high-pressure-ratio transonic stages are grouped together to form a multistage compressor. Results are presented regarding overall performance in Freon, stage performance, and radial variation in overall stagnation pressure ratio.

Memorandum presenting a theoretical analysis of a cruciform missile configuration equipped with floating controls to determine if such controls can be utilized to improve the airframe transient response characteristics.The investigation covers either forward or aft locations of the floating controls at supersonic speeds. The results indicate that a substantial increase in airframe damping can be obtained through a proper selection of hinge-moment coefficients and through the use of a fixed-rate viscous damper attached to the floating-control surfaces.

Report presenting the aerodynamic loads acting over the vertical tail, which were determined during an investigation of the lateral stability and control characteristics of the Convair XF-92A. Results regarding the vertical-tail panel characteristics, vertical-tail load parameters, and vertical-tail bending and normal-force coefficients are provided.

Report presenting an investigation to determine the effect of wing profile on the transonic aerodynamic characteristics of rectangular and triangular wings with aspect ratios of 3. Five wings were compared over a range of Mach and Reynolds number. Results regarding the rectangular and triangular wings and use of transonic area rule are provided.

Report presenting an investigation to determine the effect of rotation on the internal flow and force characteristics of an NACA 1-series E-type cowl, designed to operate with a four-blade single-rotation propeller. Results regarding internal-flow characteristics, force characteristics, and velocity distributions are provided.

Memorandum presenting rolling-stability derivatives for three wing configurations, which were tested on the same fuselage, over a range of Mach numbers and angles of attack. The wings were assorted plan-form configurations of current interest and were not part of a geometrically related series of plan forms. Results regarding basic damping-in-roll results, estimation of rolling derivatives, and estimated effects of Reynolds number are provided.

Memorandum presenting an investigation of the Douglas D-558-II swept-wing research airplane with various modifications designed to alleviate swept-wing instability and pitch-up. In this study, the airplane was modified to include wing-chord extensions and was flight-tested.

Memorandum presenting an investigation of a low-speed leading-edge chord extension in the 19-foot pressure tunnel. Chord-extensions of various geometric designs were tested on three 45 degree sweptback wings of aspect ratio 5 and taper ratio 0.28 incorporating different airfoil sections. The data indicated that leading-edge chord-extensions could be used to produce large reductions in the longitudinal instability of all three wings tested.

Report presenting an investigation at low speed in the Langley full-scale tunnel of the downwash, sidewash, and wake behind a large-scale 60 degree triangular wing with 10-percent-thick biconvex airfoil sections. Results regarding the air-stream surveys for three different configurations and stability and trim are provided.

Report discussing an investigation into the effects of camber and leading-edge-flap deflection on the pressure pulsations on thin rigid airfoils at a range of Mach numbers. The ideal camber or flap deflection was found to be dependent on Mach number and normal-force coefficient. The results of this testing, which used a 64A006 airfoil, was compared to previous testing using a 65A006 airfoil.

Report presenting an investigation in the supersonic blowdown tunnel to determine the effects of external store location on the lift, drag, and pitching-moment characteristics of a 60 degree delta wing at Mach numbers of 1.41, 1.62, and 1.96. Brief comparative tests were also made to determine the effect of changing the sweep of the strut attaching the store to the wing and of changing the chordwise location of the swept strut.

Memorandum presenting a screening of various hydroxides for use in nuclear reactors as possible coolant moderators for operation at temperatures of about 1500 degrees Fahrenheit. The hydroxides that appear stable at a pressure of about 1 atmosphere are those of sodium, potassium, rubidium, lithium, barium, and strontium. Results regarding the core uranium investments and reflector savings are provided.

Report presenting a preliminary flight investigation to evaluate an oil-flow technique for air-flow visualization. Mixtures of silicone oil and finely powdered graphite particles were spread on a wing panel of a swept-wing jet airplane and photographs were taken of the oil patterns that formed in flight at transonic speeds and on the ground. An interpretation of the photographs is provided.

Report discussing a finless NACA RM-10 missile string-mounted on a parent body to determine the total drag, base drag, and wall temperature at peak Mach number 4.04. The total- and base-drag measurements were well-correlated with wind tunnel results and calculations made by using Love's method. The existence of considerable regions of laminar flow on the body during the flight were observed.

"In order to determine the effect of shape, compressibility, and Reynolds number on the drag and critical speed for simple forms, the drag forces on models of various simple geometric cross sections were measured in the NACA 11-inch high-speed wind tunnel. The models were circular, semitubular, elliptical, square, and triangular (isosceles) cylinders. They were tested over a speed range from 5 percent of the speed of sound to a value in excess of the critical speed, corresponding, for each model, approximately to a tenfold Reynolds number range, which extended from a minimum of 840 for the smallest model to a maximum of 310,000 for the largest model" (p. 169).

Report presents the results of flight tests comparing the relative effectiveness of conventional ailerons of the same size on wings of rectangular and tapered plan forms made with a Fairchild 22 airplane. Information is included comparing conventional and floating wing-tip ailerons on a tapered wing. The results showed that the conventional ailerons were somewhat more effective on the tapered than on the rectangular wing. The difference, however, was so small as to be imperceptible to the pilots. The floating wing-tip ailerons were only half as effective as the conventional ailerons and, for this reason, were considered unsatisfactory.

"The pressure distribution tests described in this report, covering angles of attack up to 90 degrees, were made on a rectangular monoplane wing model in the atmospheric wind tunnel of the Langley Memorial Aeronautical Laboratory. These tests indicate that a rectangular wing, by reason of its large tip loads, is uneconomical aerodynamically and structurally, has pronounced lateral instability above maximum lift, and is not adaptable to accurate calculation based on the classical wing theory" (p. 197).

"A theoretical investigation of tail-pipe burning, water injection at the compressor inlet, combination tail-pipe burning plus water injection, bleedoff, and rocket-assist methods thrust augmentation for turbojet engines was made for an engine representative of those in current use. The effect of augmented liquid ratio on augmented thrust ratio and the effects of altitude and flight Mach number on the performance of various methods were determined. The additional take-off weight involved by the use of the different thrust augmentation methods, as well as the effect of the various thrust augmentation methods on the range of a representative aircraft was also investigated" (p. 727).

"Theoretically derived charts and equations are presented by which tail-rotor design studies of directional trim and control response at low forward speed can be conveniently made. The charts can also be used to obtain the main-rotor stability derivatives of thrust with respect to collective pitch and angle of attack at low forward speeds. The use of the charts and equations for tail-rotor design studies is illustrated. Comparisons between theoretical and experimental results are presented. The charts indicate, and flight tests confirm, that the region of vortex roughness which is familiar for the main rotor is also encountered by the tail rotor and that prolonged operation at the corresponding flight conditions would be difficult" (p. 1).

From Summary: "This report presents analytical methods for computing temperature distributions in liquid-cooled turbine blades, or in simplified shapes used to approximate sections of the blade. The individual analyses are first presented in terms of their mathematical development. Nondimensional charts to simplify some temperature-distribution calculations are also given."

Paper presents a method for estimating the size of a tail or wing-tip parachute required for satisfactory emergency recovery of airplanes during spin demonstrations. The method was developed from an analysis of the results of investigations conducted in the 20-foot free-spinning tunnel with dynamically scaled models of 23 airplanes. Results regarding the conventional airplane, tailless aircraft, and estimation of shock load developed by the opening of the spin-recovery parachute.