Report presenting an analytical investigation of the performance of a turbojet engine with air bled off at the compressor outlet. A wide range of engine and flight conditions are covered and air bleeds of 0 to 15 percent of the air mass flow are considered. Results are provided in the form of generalized performance charts that are applicable to a wide range of operating conditions.

Report presenting the wing-aileron coefficients of oscillating air forces for two-dimensional supersonic flow for a variety of Mach numbers. Various ratios of control-surface chord to airfoil chord are employed in the calculation and for each combination of chord ratio and Mach number, approximate 35 values of reduced frequency are utilized.

"The method of computing velocity and pressure distributions along wing profiles under the assumption of the simplified density-speed relation, outlined in NACA Technical Note 1006, is extended to the case of a nonsymmetrical profile and a flow with circulation. The shape of the profile, the speed of the undisturbed flow, and a parameter determining the angle of attack may be prescribed. The problem is reduced to a nonlinear integral equation which can be solved numerically by an iteration method" (p. 1).

From Summary: "An extremely simple computational method is established for obtaining circulatory flows around given bodies to a high degree of accuracy for flows satisfying the linear pressure and specific-volume equation of state. The method depends not on an integral equation but on the transformation from the holograph to the physical plane involving the determination of an arbitrary analytic function. The determination of the arbitrary analytic function by elementary means results in a close approximation of the given body."

Report presenting a wind-tunnel investigation of a partial model of a conventional fighter airplane to determine the effects of rate of change of angle of attack on its maximum lift. The results indicated that the maximum lift coefficient increased linearly with pitching velocity up to a limit value of the lift coefficient which depended on the Mach number.

Note presenting an analysis for interpreting results of dynamic tests of a model investigated at full-scale Mach number in terms of the corresponding full-scale body. The analysis indicates that dynamic similarity for such a condition can be closely approximated although the effect of gravity is not to scale.

Note presenting the lift and damping in roll for families of thin sweptback tapered wings with raked-in and cross-stream wing tips. Equations were derived for wings that are contained within a boundary formed by the Mach lines, which means that the wing has subsonic leading edges, supersonic trailing edges, and supersonic wing tips.

From Introduction: "Experimental investigations of air-induction systems in which the air flows of two intakes join in a common duct have inducted that many of these systems are subject to air-flow instability at low inlet-velocity ratios. Therefore, an analysis has been made to determine a proper basis for an explanation and to provide a more quantitative explanation of the flow instability and the flow reversal. This report presents the results of this analysis."

Report presenting an investigation to determine the properties of a boron carbide-iron ceramal. The properties were compared to the properties of hot-pressed boron carbide. The properties evaluated were room- and elevated-temperature modulus of rupture, resistance to fracture by thermal shock, density, and oxidation characteristics.

Report presenting an investigation in the 20-foot free-spinning tunnel to determine whether the effectiveness of a spin-recovery parachute would be influenced by a reduction, through the use of a shock absorber, or the opening shock load. The results indicated that a given spin-recovery parachute was effective with or without a rubber shock absorber installed in the parachute towline. Results regarding the effect of the shock absorber on spin-recovery characteristics and effect of porosity and towline length on shock load are provided.

Note presenting an investigation conducted to determine the effects of an aging treatment on the life of a small cast Vitallium gas-turbine blades operated at a blade temperature of approximately 1500 degrees Fahrenheit and a stress of 20,000 pounds per square inch at the blade-failure plane. Twenty blades that were aged for 48 hours at 1500 degrees Fahrenheit were compared with 33 unaged blades. Results regarding turbine evaluation and metallurgical examination are provided.

Report presenting a method for calculating the pressure drop of a high-speed compressible fluid in a constant-area duct under the simultaneous action of friction and heat transfer. The temperature distribution assumed in the development of the working chart can be made to closely approximate, in on one or two steps, the temperature distributions found in the cooling passages of ramjet and tail-pipe-burner combustion chambers.

Report presenting an experimental investigation on the thermal and hydrodynamical behavior of air flowing along a steam-heated plate to which were attached cylindrical fins. The data indicate that the principal criterion for the application of the equations for heat transfer along unfinned flat plates is the initiation of a thermal boundary layer.

Note presenting a method of calibrating airspeed installations on airplanes at transonic and supersonic speeds by use of instrumentation in the airplane only. A description of the method and some suggestions for increasing the accuracy of the method are provided.

Note presenting a method for calculating the pressure distribution and damping in steady roll at supersonic Mach numbers of thin, flat, sweptback wings with all edges straight and subsonic. It can be adapted to wings with negative rake at the tips, but the method is developed only for wings with streamwise tips.

The third report in a series of five that present unanalyzed pressure data obtained in tests of five full-scale propellers with NACA 16-series blade sections. Pressure distributions on the blade sections were measured under operating conditions to determine the aerodynamic characteristics of each blade section. This particular report presents information for nine radial stations of the NACA 10-(3)(090)-03 propeller.

Report presenting exploratory testing obtained with leading-edge wing chord-extensions on two 52 degree sweptback wings. The wings had the same aspect ratio but different airfoil sections. Results regarding force characteristics and flow characteristics are provided.

"A complete stage of an axial-flow compressor was designed and built to investigate the possibility of obtaining a high pressure ratio with an acceptable efficiency through the use of the optimum combination of high blade loading and high relative inlet Mach number. Over-all stage performance was investigated over a range of flows at equivalent tip speeds of 418 to 836 feet per second. At design speed (836 ft/sec), a peak total-pressure ration of 1.445 was obtained with an adiabatic efficiency of 0.89. For design angle of attack at the mean radius, a total-pressure ratio of 1.392 was obtained" (p. 1).

Report presenting a wind-tunnel investigation to explore the possibility of employing boundary-layer suction slots as a means for delaying laminar separation at the leading edge and turbulent separation over the rear portions of the airfoil section at high lift coefficients. Results regarding lift and drag are explored.

Memorandum presenting an investigation of 4811C ceramic blades and the problems involved in the adaption of ceramic materials to stressed turbine components. Results regarding spin tests and rotating heat-shock runs are provided.

Report presenting an investigation of a submerged air scoop consisting of a conventional scoop located in a dimple in the fuselage surface at low speeds. Results regarding a study of the basic inlet without suction, a comparison of arrangements using boundary-layer control, the performances of the most desirable configurations with a certain boundary layer, and variation of boundary-layer thickness are provided.

Report presenting an investigation by the transonic-bump method through a range of Mach numbers in the high-speed 7- by 10-foot tunnel to determine the lateral-control characteristics of 30-percent-chord flap-type controls of various spans and locations. The wing of the semispan fuselage-wing combination had 60 degrees of sweepback of the quarter-chord line, a taper ratio of 0.6, an aspect ratio of 4.0, and an NACA 65A006 airfoil section parallel to the free air stream.

From Introduction: "This paper presents the results of an investigation of force and moment characteristics for a wing with an unswept quarter-chord line, aspect ratio 2, taper ratio 0.78, and an NACA 65A004 airfoil section parallel to the free stream."

Report presenting testing of a semispan model of a wing with the leading edge swept back 37.25 degrees, an aspect ratio of 6.04, and a taper ratio of 0.5 in order to ascertain the compressibility effects on the forces, moments, and surface pressures. Lift, drag, and pitching-moment data along with chordwise distribution of static pressure at five spanwise stations are presented for a range of Mach numbers and a constant Reynolds number. Results regarding force and moment characteristics, critical flow and drag increase at high subsonic Mach numbers, and pressure changes with increasing Mach number are provided.