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National Advisory Committee for Aeronautics Collection
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National Advisory Committee for Aeronautics Collection
49
Technical Report Archive and Image Library
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NACA Research Memorandums
35
NACA Technical Memorandums
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NACA Technical Notes
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NACA Research Memorandums
35
NACA Technical Memorandums
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1949
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National Advisory Committee for Aeronautics Collection
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The effects of aerodynamic brakes upon the speed characteristics of airplanes
Investigation of flow coefficient of circular, square, and elliptical orifices at high pressure ratios
Method of determining conditions of maximum efficiency of an independent turbine-propeller combination
An analysis of the effect of lift-drag ratio and stalling speed on landing-flare characteristics
Investigation of Flow Coefficient of Circular, Square, and Elliptical Orifices at High Pressure Ratios
Hydrodynamic characteristics of a swept planing-tail hull
Preliminary Investigation of 3-Inch Slotted Transonic Wind-Tunnel Test Sections
Preliminary Wind-Tunnel Investigation at High-Subsonic Speeds of Planing-Tail, Blended, and Airfoil-Forebody Swept Hulls
Flight Investigation of the Effect of Boundary-Layer Suction on Profile-Drag Coefficient at Supercritical Mach Numbers
Wind-tunnel investigation of horizontal tails. 5: 45 degree swept-back plan form of aspect ratio 2
Aerodynamic characteristics of a wing with quarter-chord line swept back 60 degrees, aspect ratio 4, taper ratio 0.6, and NACA 65A006 airfoil section: transonic-bump method
Altitude-chamber performance of British Rolls-Royce Nene II engine 1: standard 18.75-inch-diameter jet nozzle
Flow studies in the asymmetric adjustable nozzle of the Ames 6-by 6-foot supersonic wind tunnel
Aerodynamic Characteristics of an Airfoil-Forebody Swept Flying-Boat Hull With a Wing and Tail Swept Back 51.3 Degrees at the Leading Edge
Investigation of Extensible Wing-Tip Ailerons on an Untapered Semispan Wing at 0 Degree and 45 Degrees Sweepback
Investigation of Internal Regenerative Fuel-Heating System for 20-Inch Ram Jet
Free-flight performance of 16-inch-diameter supersonic ram-jet units 1: four units designed for combustion-chamber-inlet Mach number of 0.12 at free-stream Mach number of 1.6 (units A-2, A-3, A-4, and A-5)
A comparison of the experimental subsonic pressure distributions about several bodies of revolution with pressure distributions computed by means of the linearized theory
Tests of Lifting Surfaces on Conical and Cylindrical Portions of a Body at Subsonic Mach Numbers and at a Mach Number of 1.2
Preliminary analysis of axial-flow compressors having supersonic velocity at the entrance of the stator
Analytical and Experimental Investigation of 90 Degrees Supersonic Turning Passages Suitable for Supersonic Compressors or Turbines
Reynolds number effect on axial-flow compressor performance
Method of Determining Centrifugal-Flow-Compressor Performance With Water Injection
Tests of a model horizontal tail of aspect ratio 4.5 in the Ames 12-foot pressure wind tunnel I : quarter-chord line swept back 35 degrees
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