Report presenting the low-speed stalling and lift characteristics of the Douglas D-558-II airplane measured in a series of 1 g stalls in four different airplane configurations. Various combinations of landing gear, flaps, inlet-duct flaps, and slats were tested at a range of altitudes.

Report presenting testing using rocket-powered models to provide an experimental comparison with linearized theoretical calculations for zero-lift drag of sweptback tapered wings with thin, symmetrical, double-wedge airfoil sections. The theory compared favorably with experimental results over most of the test range. Taper was generally found to increase wing drag at low supersonic speeds but reduced drag at higher speeds.

Memorandum presenting an investigation of the low-speed static stability characteristics of a canard model with a 45 degree sweptback wing and a 60 degree triangular horizontal control surface. Results regarding longitudinal stability and control and lateral stability and control are provided.

Report presenting a wind-tunnel investigation to determine the low-speed longitudinal and lateral control characteristics of a model with a triangular wing with NACA 65(06)-006.5 airfoil sections, aspect ratio 2.31, and constant-chord control surfaces. The values of the hinge-moment parameters were found to be of somewhat greater magnitude than would be expected on unswept wings with the same aspect ratio.

Report presenting a method for calculating the path of a jettisonable nose section at any speed by means of successive approximations using static aerodynamic characteristics. Conditions for consideration, including the effect of stabilizing fins, are included in the calculations.

From Summary: "Flight tests have been conducted on rocket-propelled models of an airplane configuration incorporating a sweptback wing with inverse taper to investigate the drag, stability, and control characteristics at transonic and supersonic speeds. The models were tested with a conventional tail arrangement in the Mach number range from 0.55 to 1.2. In addition to the various aerodynamic parameters obtained, the flying qualities were computed for a full-scale airplane with the center-of-gravity location at 18 percent of the mean aerodynamic chord. Also, included in this investigation are drag measurements made on relatively simple fixed-control models tested with both conventional and V-tail arrangements."

Memorandum presenting an investigation conducted in the 20-foot free-spinning tunnel with a scale model to determine the spin and recovery characteristics of the McDonnell XF3H-1 airplane. The effects of control settings and movements on the erect and inverted spin and recovery characteristics of the model were determined. Results regarding design gross weight loading, variation of loading, spin-recovery parachutes, pilot escape, landing condition, control forces, and recommended recovery technique are provided.

Report presenting a wind-tunnel investigation of the low-speed static longitudinal characteristics of a model of the X-3 airplane with the wing flaps neutral and deflected. Results regarding those characteristics with the flaps neutral, with the flaps fully deflected, in the presence of a ground plane, with the flaps partially deflected, and effect of miscellaneous changes of the model are provided.

From Summary: "Signal Corps wind equipment AN/GMQ-1 consisting of a 3-cup anemometer and wind vane was calibrated for wind velocities from 1 to 200 miles per hour. Cup-shaft failure prevented calibration at higher wind velocities. The action of the wind vane was checked and found to have very poor directional accuracy below a velocity of 8 miles per hour. After shaft failure was reported to the Signal Corps, the cup rotors were redesigned by strengthening the shafts for better operation at high velocities. The anemometer with the redesigned cup rotors was recalibrated, but cup-shaft failure occurred again at a wind velocity of approximately 220 miles per hour."

The effect of fuel volatility on altitude starting limits of an axial-flow-compressor-type turbojet engine was investigated using fuels with Reid vapor pressures of 1.1 and 5.4 pounds per square inch. At flight Mach numbers from 0.40 to 0.85, the AN-F-58 fuel allowed consistent windmilling at altitudes 2000 to 8000 feet higher than was obtained with the 1.1-pound Reid vapor pressure fuel. At a flight Mach number of 0.25, ignition could not be established at any altitude with the lower-volatility fuel.

Report presenting results from a preliminary flight investigation on a swept-wing airplane of the lateral-control characteristics and wing-dropping tendency encountered at high Mach numbers. Measurements of aileron and rudder-control effectiveness are presented and used with estimated damping-in-roll characteristics and data from steady sideslips to approximate the variation of effective dihedral with Mach number.

Report presenting measurements of chordwise pressure distribution over the 10-percent-thick wing of the X-1 research airplane at a section near the midspan of the left wing. Results regarding the upper- and lower-surface pressure distributions at a range of Mach numbers and section loads are provided.

Report investigating the effects of interference on wing-body combinations by testing a pointed, cylindrical body at Mach numbers of 1.50 and 2.02 of six triangular wings with a range of aspect ratios and with the wing and body in combination. Theoretical characteristics of the body and wings alone and in combination were calculated from available theories and compared with experimental results.

Report presenting results obtained with quiescent fuel-air mixtures and with small diffusion flames, which indicate that combustion efficiencies close to 100 percent were obtained at pressure much lower than those found in turbojet combustors at altitudes of 60,000 feet.

To determine effect of nonuniform inlet-air velocities, a full scale, axial-flow turbojet engine was investigated in Lewis altitude wind tunnel at altitudes from 20,000 to 50,000 feet, 0.21 flight Mach number and corrected engine speeds from 77.3 percent of rated speed to rated speed. Total-pressure variations as large as 103 pounds per square foot in radial direction and 90 pounds per square foot in circumferential direction at 30,000 feet were obtained. With the distortions investigated, net thrust varied between 0.95 and 1.03 of the thrust with uniform inlet-air distribution. Similarly the ratio of specific fuel consumption varied from 1.00 to 1.04. Within the arrange of this investigation the effects of nonuniform inlet velocity were not serious for the engine investigated.

Report presenting the use of porous-walled tunnels at supersonic Mach numbers as a means of avoiding reflection of a stream disturbance extending to the walls. Results from analysis and an experiment with a 4 degree wedge at a Mach number of 1.2 are provided.

"An investigation of the nature of the flow field behind a rectangular circular-arc wing has been conducted in the Langley 9-inch supersonic tunnel. Pitot- and static-pressure surveys covering a region of flow behind the wing have been made together with detailed pitot surveys throughout the region of the wake. In addition, the flow direction has been measured using a weathercocking vane measurements. Theoretical calculations of the variation of both downwash and sidewash with angle of attack using Lagerstrom's superposition method have been made" (p. 1).

Report presenting an investigation in the high speed tunnel to determine the effects of several wing-mounted external-store configurations on the aerodynamic characteristics of a model of a swept wing-fuselage combination for a range of Mach numbers. Some of the configurations explored included inboard underwing installations and wing-tip installations. Results regarding lift-drag ratios, drag characteristics, lift-curve slope, and pitching-moment characteristics are provided.

From Summary: "A flight investigation was made of a supersonic twin-ram-jet test vehicle using short-flame-length burners. The test demonstrated a maximum acceleration of 3.6g and a maximum flight Mach number of 3.02. Data were obtained over a Mach number range from about 1.9 to 3.0, an altitude range from 1,800 to 40,900 feet, and a fuel-air-ratio range from 0.012 to 0.065."

Report discussing tests of an unshrouded axial-flow supersonic compressor rotor. Information about the pressure ratio, efficiency, and flow rate with and without inlet guide vanes is provided. The results are also compared to testing on the original shrouded rotor.

Report presenting testing of the zero-lift drag of two wings, one with 45 degree sweepforward of the inboard panel and 45 degree sweepback of the outboard panel ("M" wing) and the other with a reverse sweep ("W" wing) at a range of Mach numbers. Both wings were found to have greater drag than a sweptback wing and less drag than a rectangular wing at transonic speeds. The differences were reduced at Mach numbers above 1.25.

"Tabulated pressure coefficients and aerodynamic characteristics are presented for six spanwise stations on the left wing of the Bell X-1 research airplane. The data were obtained in level flight at Mach numbers from 0.79 to 1.00 and in a pull-up to an airplane normal-force coefficient of 0.91 at a Mach number of approximately 0.96" (p. 1).

From Introduction: "Performance data are presented in this report to show the characteristics of the turbine operating as an integral part of the engine. Typical results are graphically presented to show the effects of changes in altitude, flight Mach number, and exhaust-nozzle-outlet area on turbine performance. All turbine-performance data obtained are given in tabular form."

Report presenting an investigation of the cooling effectiveness of water films on the inner surface of a well-insulated, 4-inch-diameter duct with air flowing through the duct at a range of temperature and Reynolds numbers. Results regarding the effect of the gas temperature and mass velocity on liquid-cooled length, effect of coolant flow on liquid-cooled length, and some suggestions for further investigation are provided. Equations for correlation are created from the data.