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NACA Research Memorandums
33
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NACA Research Memorandums
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1953
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Rocket-Model Measurements of Zero-Lift Damping in Roll of the Bell MX-776 Missile at Mach Numbers from 0.6 to 1.56
Calibration of the Friez Aerovane, Wind Measuring Set AN/GMQ-11
The Results of Wind-Tunnel Tests at Low Speeds of a Four-Engine Propeller-Driven Airplane Configuration Having a Wing With 40 Degrees of Sweepback and an Aspect Ratio of 10
Effects of additives on pressure limits of flame propagation of propane-air mixtures
Experimental Investigation of Laminar-Boundary-Layer Control on an Airfoil Section Equipped With Suction Slots Located at Discontinuities in the Surface Pressure Distribution
Experimental investigation of laminar-boundary-layer control on an airfoil section equipped with suction slots located at discontinuities in the surface pressure distribution
Effect of Large Deflection of a Canard Control and Deflections of a Wing-Tip Control on the Static-Stability and Induced-Roll Characteristics of a Cruciform Canard Missile at a Mach Number of 2.01
Experimental investigation of an axial-flow supersonic compressor having rounded leading-edge blades with an 8-percent mean thickness-chord ratio
Flow Coefficients for Orifices in Base of Transpiration-Cooled Turbine Rotor Blade
Investigation at transonic speeds of aerodynamic characteristics of a semielliptical air inlet in the root of a 45 degree sweptback wing
An Investigation of Continuous Boundary-Layer Removal in an Axial Flow Compressor With Porous Walls
Calculated Lateral Frequency Response and Lateral Oscillatory Characteristics for Several High-Speed Airplanes in Various Flight Conditions
Effects of External Store Mounting on the Buffet, Trim, and Drag Characteristics of Rocket-Powered Fuselage and Store Combinations Between Mach Numbers of 0.7 and 1.4
An experimental investigation of the transonic-flow-generation and shock-wave-reflection characteristics of a two-dimensional wind tunnel with 24-percent-open, deep, multislotted walls
The Influence of the Control-Surface-Servo Natural Frequency Upon the Transient Characteristics of a Flight-Path-Angle Control System Incorporating a Supersonic Missile
The Use of a Leading-Edge Area-Suction Flap to Delay Separation of Air Flow From the Leading Edge of a 35 Degrees Sweptback Wing
Method of Estimating the Incompressible-Flow Pressure Distribution of Compressor Blade Sections at Design Angle of Attack
Method of Estimating the Incompressible-Flow Pressure Distribution of Compressor Blade Sections at Design Angle of Attack
Preliminary Investigation of the Total-Pressure-Recovery Characteristics of a Symmetric and Asymmetric Nose Inlet Over a Wide Range of Angle of Attack at Supersonic Mach Numbers
A Preliminary Investigation at Mach Number 1.91 of a Diffuser Employing a Pivoted Cone to Improve Operation at Angle of Attack
A Preliminary Study by Means of Electrical Frequency-Analysis Techniques of the Response of an Airplane Structure During Buffeting
Wind-tunnel investigation at transonic speeds of a spoiler-slot-deflector combination on an unswept NACA 65A006 wing
Experimental Investigation of a 0.4 Hub-Tip Diameter Ratio Axial-Flow Compressor Inlet Stage at Transonic Inlet Relative Mach Numbers 1: Rotor Design and Over-All Performance at Tip Speeds From 60 to 100 Percent of Design
Investigation of a Related Series of Turbine-Blade Profiles in Cascade
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