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National Advisory Committee for Aeronautics Collection
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Technical Report Archive and Image Library
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UNT Libraries Government Documents Department
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National Advisory Committee for Aeronautics Collection
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1952
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Effect of water vapor on combustion of magnesium hydrocarbon slurry fuels in small-scale afterburner
Effects of stabilizing fins and a rear-support sting on the base pressure of a body of revolution in free flight at Mach numbers from 0.7 to 1.3
Investigation of the Effects of Variations in the Reynolds Number Between 0.4 X 10(Exp 6) 3.0 X 10(Exp 6) on the Low-Speed Aerodynamic Characteristics of Three Low-Aspect-Ratio Symmetrical Wings With Rectangular Plan Forms
Aerodynamic characteristics of two 25-percent-area trailing-edge flaps on an aspect ratio 2 triangular wing at subsonic and supersonic speeds
Effects of three types of blunt trailing edges on the aerodynamic characteristics of a plane tapered wing of aspect ratio 3.1, with a 3-percent- thick biconvex section
Investigation of Turbines for Driving Supersonic Compressors 2: Performance of First Configuration With 2.2 Percent Reduction in Nozzle Flow Area
Preliminary air-flow and thrust calibrations of several conical Cooling-air ejectors with a primary to secondary temperature ratio of 1.0 I :diameter ratios of 1.21 and 1.10
Use of Choked Nozzle Technique and Exhaust Jet Diffuser for Extending Operable Range of Jet-Engine Research Facilities
Effects of Some Primary Variables of Rectangular Vortex Generators on the Static-Pressure Rise Through a Short Diffuser
Some Wind-Tunnel Results of an Investigation of the Flutter of Sweptback- and Triangular-Wing Models at Mach Number 1.3
Effect of Various Blade Modifications on Performance of a 16-Stage High-Pressure-Ratio Axial-Flow Compressor 1 - Effect on Over-All Performance Characteristics of Decreasing Twelfth Through Fifteenth State Stator-Blade Angles 3 Degrees
Method of Estimating the Stick-Fixed Longitudinal Stability of Wing-Fuselage Configurations Having Unswept or Swept Wings
Summary of some effective aerodynamic twisting-moment coefficients of various wing-control configurations at Mach numbers from 0.6 to 1.7 as determined from rocket-powered models
Wind-Tunnel Investigation of a Shielded Total-Pressure Tube at Transonic Speeds
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