Report presenting the results of an experimental investigation of the downwash and wake characteristics behind two highly swept wings in a supersonic stream. Results regarding the rate of change of downwash with angle of attack at zero lift, variation of downwash angle with angle of attack, and wake are provided.

From Introduction: "This paper, which should be of interest to those concerned with transonic wind tunnels, covers the design and operating characteristics of the nozzle."

Report presenting a semiempirical method of estimating the forces on airfoil at near sonic speeds and in the presence of detached shock waves. The calculated values were found to be in good agreement with wind-tunnel testing of the forces on sharp-nose airfoils and two-dimensional wings.

Report presenting an investigation in the two-dimensional low-turbulence tunnel of the NACA 65,3-418 airfoil section with a 25-percent-airfoil-chord plain flap and a suction slot on the flap. The primary purpose of the investigation is to determine the effect of the type of boundary-layer control on the section lift-drag ratio.

Report presenting the pressure-recovery characteristics at the vertical center line of an NACA submerged inlet of aspect ratio 5 measured in the Mach number range of 0.60 to 1.08 by the wing-flow method. Variation of ram-recovery ratio determined from measurements at the center line of the inlet with test station Mach number is presented for mass-flow ratios of 0.30 to 0.60. Results regarding the pressure-recovery characteristics and application of the data to fuselage installations are provided.

Report presenting a comparison of the lift, drag, and pitching-moment characteristics of several wings with 35 degrees of sweepback and various amounts of camber in wind-tunnel testing. Six semispan model wings were tested, three with an aspect ratio of 10 and three with an aspect ratio of 5. Results regarding model distortion under aerodynamic loads, effects of Reynolds number, effects of Mach number, and effects of camber are provided.

Report presenting an investigation to determine the stability and control characteristics of a vertically rising airplane model. Results of preliminary hovering flight tests are made in still air, away from the interference effects of the ground and side walls, and with normal airplane-type controls operating in the slipstream.

"A preliminary low-speed investigation has been made of an air scoop submerged one-half the inlet height in a depression on the surface of a simulated fuselage. Boundary-layer suction was used on the steep approach ramp to improve the internal flow. A 6-degree-included-angle diffuser with an area ratio of 1.9:1 was located behind the inlet in the model. Most of the tests were conducted with an initial turbulent boundary layer believed to approximate that which would occur on the forward part of a fuselage" (p. 1).

From Summary: "An investigation was conducted in the Langley 19-foot pressure tunnel on a 0.3-scale model of the Republic RF-84F airplane to determine modifications which would eliminate the pitch-up that occurred near maximum lift during flight tests of the airplane. The effects of high-lift and stall-control devices, horizontal tail locations, external stores, and various inlets on the longitudinal characteristics of the model were investigated. For the most part, these tests were conducted at a Reynolds number of 9.0 x 10(exp 6) and a Mach number of 0.19. The results indicated that from the standpoint of stability the inlets should possess blunted side bodies. The horizontal tail located at either the highest or lowest position investigated improved the stability of the model."

Report presenting an investigation of an inlet mounted on the side of a fuselage and utilizing a horizontally oriented 14 degree ramp located at the top of the inlet at a variety of Mach numbers. The characteristics of this inlet were compared to a conventional ramp-type side inlet. Results regarding the pressure recovery and model drag coefficients, spillage drag coefficients, and thrust minus drag comparison are provided.

Report presenting an examination of the most promising air-cooled turbine blades for conventional turbojet engines, which are convection-cooled corrugated-insert and strut-supported blades. Successful analytical methods of predicting blade temperatures have been found for both blades. Results regarding turbine-engine performance, turboprop-engine performance, performance variations with compressor-discharge air bleed, and some cooling methods are provided.

Report presenting an investigation of a total of 31 flame-holder elements that can be classified into 7 distinct types under simulated afterburner operating conditions to determine their merit and feasibility for use in a high-velocity gas stream. The results indicated that a screen-type flame holder could far exceed the velocity limits of the same size conventional V-gutter at fuel-air ratios below about 0.045.

Report presenting the effect of small variations in the axial position of the liner with respect to the nozzle on limiting rates of change of fuel flow and steady-state combustion efficiencies in a single tubular combustor. Data were obtained with two liner configurations at three combustor-inlet conditions. Results regarding transient combustion performance and steady-state combustion performance are provided.

Report presenting one-tenth-scale models of two inlet configurations of fighter-type aircraft have been tested in the 4- by 4-foot supersonic pressure tunnel. The pressure-recovery and force characteristics of the inlets were determined as a function of mass-flow ratio, angle of inlet compression, angle of attack, and Mach number.

Report presenting measurements of boiling burn-out heat flux for water flowing upward through an electrically heated tube for ranges of velocity, pressure, length-diameter ratios, and subcooling.

From Introduction: "Data on the extent of decomposition of a sample of aluminum borohy-dride during long-term storage are presented."

From Summary: "An investigation was made to evaluate several design variations of hollow turbine blades intended for missile-engine use. In one general type, the airfoils were formed from sheet metal; in a second type, the blades were cast. The blades were operated in J47 engine at 7950 rpm turbine speed and 1260 degrees Fahrenheit tail-pipe temperature until a failure occurred or a service life of 30 hours had been attained."

Report presenting free-oscillation tests to determine the dynamic hinge-moment characteristics of a trailing-edge flap-type control surface on a 4-percent-thick unswept wing with low aspect ratio. Tests were made over a range of Mach numbers, reduced frequencies, and low test speeds. Results regarding the effects of wing motion, damping moment and flutter characteristics, spring moments, and theoretical results are provided.