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NACA Technical Notes
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NACA Technical Notes
20
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1952
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1952
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NACA Technical Notes
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A Probability Analysis of the Meteorological Factors Conducive to Aircraft Icing in the United States
A blade-element analysis for lifting rotors that is applicable for large inflow and blade angles and any reasonable blade geometry
The theoretical characteristics of triangular-tip control surfaces at supersonic speeds: Mach lines behind trailing edges
Effects of Aspect Ratio on Air Flow at High Subsonic Mach Numbers
Investigation of the influence of fuselage and tail surfaces on low-speed static stability and rolling characteristics of a swept-wing model
Numerical determination of indicial lift and moment functions for a two-dimensional sinking and pitching airfoil at Mach numbers 0.5 and 0.6
Experimental investigation of the local and average skin friction in the laminar boundary layer on a flat plate at a Mach number of 2.4
Plastic Stress-Strain Relations for Combined Tension and Compression
A probability analysis of the meteorological factors conducive to aircraft icing in the United States
Boundary-layer development and skin friction at mach number 3.05
Practical Calculation of Second-Order Supersonic Flow Past Nonlifting Bodies of Revolution
Influence of Chemical Composition on Rupture Test Properties at 1500 Degrees Fahrenheit of Forged Chromium-Cobalt-Nickel-Iron Base Alloys
Preview of Behavior of Grain Boundaries in Creep of Aluminum Bicrystals
Measurements of flying qualities of an F-47D-30 airplane to determine lateral and directional stability and control characteristics
An analysis of the normal accelerations and airspeeds of a two-engine type of transport airplane in commercial operations on routes in the central United States from 1948 to 1950
Experiments in External Noise Reduction of a Small Pusher-Type Amphibian Airplane
Choking of a Subsonic Induction Tunnel by the Flow from an Induction Nozzle
A Method of Selecting the Thickness, Hollowness, and Size of a Supersonic Wing for Least Drag and Sufficient Bending Strength at Specified Flight Conditions
Matrix and Relaxation Solutions That Determine Subsonic Through Flow in an Axial-Flow Gas Turbine
Span load distributions resulting from angle of attack, rolling, and pitching for tapered sweptback wings with streamwise tips: Supersonic leading and trailing edges
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