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Performance of single-stage compressor designed on basis of constant total enthalpy with symmetrical velocity diagram at all radii and velocity ratio of 0.7 at rotor hub
A preliminary gust-tunnel investigation of leading-edge separation on swept wings
A transonic-wing investigation in the Langley 8-foot high-speed tunnel at high subsonic Mach numbers and at a Mach number of 1.2: Wing-fuselage configuration having a wing of 0 degrees sweepback, aspect ratio 4.0,taper ratio 0.6, and NACA 65A006 ai
Analysis of Limitations Imposed on One-Spool Turboprop-Engine Designs by Compressors and Turbines at Flight Mach Numbers of 0.06, and 0.8
Effect of Fuel-Air Distribution on Performance of a 16-Inch Ram-Jet Engine
Flutter Investigation in the Transonic Range of Six Airfoils Attached to Three Freely Falling Bodies
Investigation of the Kingfisher XAUM-2 Flying Torpedo in the Langley Full Scale Tunnel, TED No. NACA DE 327
Tank tests of a 1/8-size powered dynamic model of the Martin PBM-5 seaplane equipped with a single Edo hydro-ski : TED No. NACA AD3110
Experimental Evaluation of Gaseous Hydrocarbon Fuel in a 16-Inch-Diameter Ram-Jet Engine
Investigation of the NACA 4-(4)(06)-057-45a and NACA 4-(4)(06)-57-45b Two-Blade Swept Propellers at Forward Mach Numbers to 0.925
An Investigation of the Low-Speed Characteristics of Two Sharp-Edge Supersonic Inlets Designed for Essentially External Supersonic Compression
Performance of Compressor of XJ-41-V Turbojet Engine 2 - Static-Pressure Ratios and Limitation of Maximum Flow at Equivalent Compressor Speed of 8000 RPM
Altitude-Test-Chamber Investigation of a Solar Afterburner on the 24C Engine 1 - Operational Characteristics and Altitude Limits
Effect of Three Modifications on Performance of Auxiliary-Stage Supercharger for V-1710-93 Engine
Low-Speed Static Stability Characteristics of a Canard Model with a 45 Degree Sweptback Wing and a 60 Degree Triangular Horizontal Control Surface
Matching Characteristics of J35-A-23 Compressor and Two-stage Turbine
Aerodynamic characteristics at subcritical and supercritical Mach numbers of two airfoil sections having sharp leading edges and extreme rearward positions of maximum thickness
Preliminary Wind Tunnel Investigation of Two Types of Jet-Exit Configurations for Control of Aircraft
A Transonic Wind-Tunnel Investigation of an Unswept-Wing-Body Combination at Angles of Attack Up to 24 Degrees
A study of fuel-nitric acid reactivity
Investigation of a High-Flow Transonic-Compressor Inlet Stage Having a Hub-Tip Radius of 0.35
Altitude-Wind-Tunnel Investigation of a 4000-Pound-Thrust Axial-Flow Turbojet Engine. 2 - Operational Characteristics
Investigation of the Longitudinal Aerodynamic Characteristics of a Trapezoidal-Wing Airplane Model With Various Vertical Positions of Wing and Horizontal Tail at Mach Numbers of 1.41 and 2.01
Effect of spark repetition rate on the ignition limits of a single tubular combustor
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