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NACA Research Memorandums
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NACA Research Memorandums
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Effects of angle of attack and airfoil profile on the two-dimensional flutter derivatives for airfoils oscillating in pitch at high subsonic speeds
Sea-level static equilibrium performance of actual two-spool turbojet engine and comparison with hypothetical engine
A Transonic Wind-Tunnel Investigation of the Longitudinal Force and Moment Characteristics of a Plane and a Cambered 3-Percent-Thick Delta Wing of Aspect Ratio 3 on a Slender Body
Analytical Study of the Effect of Center-of-Gravity Position on the Response to Longitudinal Control in Landing Approaches of a Swept-Wing Airplane of Low Aspect Ratio Having No Horizontal Tail
Effect of Ice Formations on Section Drag of Swept NACA 63A-009 Airfoil with Partial-Span Leading-Edge Slat for Various Modes of Thermal Ice Protection
Preliminary Investigation of a Technique for Stability Studies of a Self-Propelled Model of a Submerged Submarine
Zero-Lift Drag of the Chance Vought Regulus II Missile at Mach Numbers Between 0.8 and 2.2 as Determined From the Flight Tests of Two 0.12-Scale Models
Investigation of Adjustable Supersonic Inlet in Combination With J34 Engine Up to Mach 2.0
The Effect of an Operating Propeller on the Aerodynamic Characteristics at High Subsonic Speeds of a Model of a Vertical-Rising Airplane Having an Unswept Wing of Aspect Ratio 3
Effect of Ice Formations on Section Drag of Swept NACA 63A-009 Airfoil With Partical-Span Leading-Edge Slat for Various Modes of Thermal Ice Protection
Preliminary performance data for the J57-P-1 turbojet engine at altitudes up to 65,000 feet
Effect of nose shape and trailing-edge bluntness on the aerodynamic characteristics of an unswept wing of aspect ratio 3.1, taper ratio 0.4, and 3-percent thickness
Investigation of a missile airframe with control surfaces consisting of projecting quadrants of the nose cone
Altitude performance of compressor, turbine, and combustor components of 600-B9 turbojet engine
Investigation of a 10-Stage Subsonic Axial-Flow Research Compressor 5: Effect of Reducing Inlet-Guide-Vane Turning on Over-All and Inlet-Stage Performance
A Flight Investigation of the Effects of Inclination of the Principal Axis of Inertia on the Dynamic Lateral Stability of the Republic XF-91 Airplane
Experimental Determination of Boundary-Layer Transition on a Body of Revolution at M = 3.5
An Experimental Investigation of Four Triangular-Wing-Body Combinations in Sideslip at Mach Numbers 0.6, 0.9, 1.4, and 1.7
Low-Speed Cascade Tests of Two 45 Degree Swept Compressor Blades With Constant Spanwise Loading
Rocket-Powered Model Investigation of Lift, Drag, and Stability of a Body-Tail Configuration at Mach Numbers From 0.8 to 2.3 and Angles of Attack Between Plus or Minus 6.5 Degrees
Transonic Wind-Tunnel Investigation of the Effects of Taper Ratio, Body Indentation, Fixed Transition, and Afterbody Shape on the Aerodynamic Characteristics of a 45 Degree Sweptback Wing-Body Combination
Comparison of experimental with calculated results for the lifting effectiveness of a flexible 45 degree sweptback wing of aspect ratio 6.0 at Mach numbers from 0.8 to 1.3
Transonic wind-tunnel investigation of the effect of body indentation for boattail and cylindrical afterbody shapes on the aerodynamic characteristics of an unswept-wing-body combination
Tests in the Ames 40- by 80-foot wind tunnel of the effects of varying wing modifications on the longitudinal characteristics of two-triangular wing airplane models with and without horizontal tails
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