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National Advisory Committee for Aeronautics Collection
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National Advisory Committee for Aeronautics Collection
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Ice protection of turbojet engines by inertia separation of water 3: annular submerged inlets
Internal-Film Cooling of Rocket Nozzles
Investigation at large scale of the pressure distribution and flow phenomena over a wing with the leading edge swept back 47.5 degrees having circular-arc airfoil sections and equipped with drooped-nose and plain flaps
Analysis and Preliminary Investigation of Eddy-Current Heating for Icing Protection of Axial-Flow-Compressor Blades
An Investigation of the Characteristics of an Unswept Wing of Aspect Ratio 4.01 in the Langley 8-Foot High-Speed Tunnel
Damping-in-Roll Characteristics of a 42.7 Degree Sweptback Wing as Determined From a Wind-Tunnel Investigation of a Twisted Semispan Wing
Aerodynamic study of a wing-fuselage combination employing a wing swept back 63 degrees : effectiveness of an elevon as a longitudinal control and the effects of camber and twist on the maximum lift-drag ratio at supersonic speeds
Aerodynamics of slender bodies at Mach number of 3.12 and Reynolds numbers from 2 x 10(exp 6) to 15 x 10(exp 6) 2: aerodynamic load distributions of series of five bodies having conical noses and cylindrical afterbodies
Development of Metal-Bonding Adhesive FPL-710 With Improved Heat-Resistant Properties
Forces and moments on pointed blunt-nosed bodies of revolution at Mach numbers from 2.75 to 5.00
Flight and Test-Stand Investigation of High-Performance Fuels in Pratt & Whitney R-1830-94 Engines 4: Comparison of Cooling Characteristics of Flight and Test-Stand Engines
Effects of internal configuration on afterburner shell temperatures
Damping in Roll of Rocket-Powered Test Vehicles Having Swept, Tapered Wings of Low Aspect Ratio
An analytical method for evaluating factors affecting application of transpiration cooling to gas turbine blades
Estimated deceleration of airplane nose section jettisoned at various altitudes and airspeeds
Longitudinal-control effectiveness and downwash characteristics at a Mach number of 1.24 of a 1/30-scale semispan model of the Bell X-5 airplane as determined by the NACA wing-flow method
Characteristics of perforated diffusers at free-stream Mach number 1.90
Propeller Section Aerodynamic Characteristics as Determined by Measuring the Section Surface Pressures on an NACA 10-(3)(08)-03 Propeller Under Operating Conditions
Free-Spinning Tunnel Tests of a 1/20-Scale Model of the McDonnell XF3H-1 Airplane : TED No. NACA DE 343
Longitudinal Stability and Control Characteristics of a Canard Missile Configuration for Mach Numbers From 1.1 to 1.93 as Determined From Free-Flight and Wind-Tunnel Investigation
The transonic characteristics of 38 cambered rectangular wings of varying aspect ratio and thickness as determined by the transonic-bump technique
Lateral-control investigation at transonic speeds of retractable spoiler and plug-type spoiler-slot ailerons on a tapered 60 degree sweptback wing of aspect ratio 2 : transonic-bump method
Transonic Drag Characteristics and Pressure Distribution on the Body of a Wing-Body Combination Consisting of a Body of Revolution of Fineness Ratio 12 and a Wing Having Sweepback of 45 Degrees, Aspect Ratio 4, Taper Ratio 0.6, and NACA 65A006 Airfoil Sections
An experimental cascade study of the effects of a solidity reduction on the two-dimensional aerodynamic characteristics of a turbine-rotor blade suitable for air cooling
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