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National Advisory Committee for Aeronautics Collection
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National Advisory Committee for Aeronautics Collection
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Correlation of Vibratory Root Failures and Stress Distribution in J65 Compressor Blades
Initial Experiments on the Aerodynamic Cooling Associated With Large-Scale Vortical Motions in Supersonic Flow
Transonic wind-tunnel investigation of the effects of external stores and store position on the aerodynamic characteristics of a 1/16-scale model of the Douglas D-558-II research airplane
Interaction of a Jet and Flat Plate Located in an Airstream
Performance of a high-solidity high-pressure-ratio transonic rotor
Flight Investigation at Supersonic Mach Numbers of an Automatic Acceleration Control Missile in Which Rate Damping Is Obtained From a Linear Accelerometer Placed Ahead of the Missile Center of Gravity
The effect of leading-edge droop upon the pressure distribution and aerodynamic loading characteristics of a 45 degree sweptback wing at transonic speeds
Investigation of the NACA 4-(5)(05)-037 six- and eight-blade, dual-rotation propellers at positive and negative thrust at Mach numbers up to 0.90, including some aerodynamic characteristics of the NACA 4-(5)(05)-041 two- and four-blade, single-rotat
On boattail bodies of revolution having minimum wave drag
Experimental Investigation of a Five-Stage Axial-Flow Research Compressor with Transonic Rotors in All Stages 1: Compressor Design
Theory of wing-body drag at supersonic speeds
Performance Characteristics of Several Divergent-Shroud Aircraft Ejectors
The Origin and Distribution of Supersonic Store Interference From Measurement of Individual Forces on Several Wing-Fuselagestore Configurations 6. - Swept-Wing Heavy-Bomber Configuration With Stores of Different Sizes and Shapes
The origin and distribution of supersonic interference from measurement of individual forces on several wing-fuselage-store configurations 6: swept-wing heavy-bomber configuration with stores of different sizes and shapes
A simulation study of a wingless missile
Longitudinal Stability Investigation for a Mach Number Range of 0.8 to 1.7 of an Airplane Configuration With a 45 Degree Swept Wing and a Low Horizontal Tail
Preliminary Free-Flight Study of the Drag and Stability of a Series of Short-Span Missiles at Mach Numbers From 0.9 to 1.3
Results of the Flight Test of a 0.13-Scale Rocket-Boosted Model of the McDonnell F4H-1 Airplane Between Mach Numbers of 0.20 and 1.90
Wind Tunnel Investigation at High Subsonic Speeds of Drag at 0 Degrees Angle of Attack of Swept-Wing Fuselage Models With Pylon Mounted and Semisubmerged Missiles
Synthesis and Hydrolysis-Rate Studies of Decaborane Derivatives
Wind-Tunnel Investigation of the Drag and Lateral-Stability Characteristics of a 1/22-Scale Model of a Bomber Airplane Employing a Low-Aspect-Ratio Triangular Wing
Investigation of an All-Movable Control Surface at a Mach Number of 6.86 for Possible Flutter
Preliminary Investigation of Dynamic Lateral Stability Characteristics of a Configuration of the North American X-15 Research Airplane
Tabulated Pressure Data for a Series of Controls on a 40 Degree Sweptback Wing at Mach Numbers of 1.61 and 2.01
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