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NACA Research Memorandums
269
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NACA Research Memorandums
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1949
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1949
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Performance of Single-Stage Turbine of Mark 25 Torpedo Power Plant with Two Special Nozzles 2 - Efficiency with 20 Degrees-Inlet-Angle Rotor Blades
Effect of an Increase in Hull Length-Beam Ratio From 15 to 20 on the Hydrodynamic Characteristics of Flying Boats
Performance of Single-Stage Turbine of Mark 25 Torpedo Power Plant with Two Special Nozzles 1 - Efficiency with 0.45-inch Rotor Blades
Wind-Tunnel Tests of a 0.16-Scale Model of the Douglas MX-656 Airplane at High Subsonic Speeds. 2 - Wing and Fuselage Pressure Distribution
Preliminary Measurements of the Dynamic Lateral Stability Characteristics of the Douglas D-588-II (BuAero No. 37974) Airplane
An NACA Vane-Type Angle-of-Attack Indicator for use at Subsonic and Supersonic Speeds
Preliminary Aerodynamic Investigation of the Effect of Camber on a 60 Degree Delta Wing with Round and Beveled Leading Edges
Aerodynamic Study of a Wing-Fuselage Combination Employing a Wing Swept Back 63 Degrees: Characteristics Throughout the Subsonic Speed Range With the Wing Cambered and Twisted for a Uniform Load at a Lift Coefficient of 0.25
Experimental performance of chlorine trifluoride-hydrazine propellant combination in 100-pound-thrust rocket engine
Preliminary Theoretical and Flight Investigation of the Lateral Oscillation of the X-1 Airplane
The Static-Pressure Error of Wing and Fuselage Airspeed Installations of the X-1 Airplanes in Transonic Flight
Supplementary Wind-Tunnel Investigation of the Stability of the Jettisonable Nose Section of the X-2 Airplane
Design Factors for 4- by 8-Inch Ram-Jet Combustor
Analysis of the dynamic lateral stability characteristics of the Bell X-2 airplane as affected by variations in mass, aerodynamic, and dimensional parameters
Ditching Tests of a 1/18-Scale Model of the Lockheed Constellation Airplane with Speedpak Attached
Effect of Sweepback on the Low-Speed Static and Rolling Stability Derivatives of Thin Tapered Wings of Aspect Ratio 4
Resistance and Spray Characteristics of a 1/13-Scale Model of the Consolidated Vultee Skate 7 Seaplane: TED No. NACA DE 338
Analysis and Preliminary Investigation of Eddy-Current Heating for Icing Protection of Axial-Flow-Compressor Blades
Damping-in-Roll Characteristics of a 42.7 Degree Sweptback Wing as Determined From a Wind-Tunnel Investigation of a Twisted Semispan Wing
Calculative method for estimating the interference pressure field at zero lift on a symmetrical swept-back wing mounted on a circular cylindrical body
Experimental investigation of hot-gas bleedback for ice protection of turbojet engines 3: nacelle with short straight air inlet
Measurements of Aileron Effectiveness of the Bell X-1 Airplane at Mach Numbers Between 0.9 and 1.06
Spark ignition of flowing gases I : energies to ignite propane-air mixtures in pressure range of 2 to 4 inches mercury absolute
Stability and Control Data Obtained from Fourth and Fifth Flights of the Northrop X-4 Airplane (A.F. No. 46-676)
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