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- Comparative Tensile Strengths at 1200 Degrees F of Various Root Designs for Cermet Turbine Blades
- Compressible-Flow Solutions for the Actuator Disk
- A Comparison of Several Systems of Boundary-Layer Removal Ahead of a Typical Conical External-Compression Side Inlet at Mach Numbers of 1.88 and 2.93
- Calculation of Aerodynamic Forces on an Inclined Dual-Rotating Propeller
- The Calculated and Experimental Incremental Loads and Moments Produced by Split Flaps of Various Spans and Spanwise Locations on a 45 Degrees Sweptback Wing of Aspect Ratio 8
- Analysis of Off-Design Performance of a 16-Stage Axial-Flow Compressor With Various Blade Modifications
- Longitudinal Stability, Control Effectiveness, and Drag Characteristics at Transonic Speeds of a Rocket-Propelled Model of an Airplane Configuration Having an Unswept Tapered Wing of Aspect Ratio 3.0 and NACA 65A004.5 Airfoil Sections
- Low-Lift Buffet Characteristics Obtained From Flight Tests of Unswept Thin Intersecting Surfaces and of Thick 35 Degree Sweptback Surfaces
- Low-Speed Aileron Effectiveness as Determined by Force Tests and Visual-Flow Observations on a 52 Degree Sweptback Wing With and Without Chord-Extensions
- Maximum Altitude and Maximum Mach Number Obtained With the Modified Douglas D-558-II Research Airplane During Demonstration Flights
- Longitudinal Stability and Wake-Flow Characteristics of a Twisted and Cambered Wing-Fuselage Combination of 45 Degree Sweepback and Aspect Ratio 8 With a Horizontal Tail and Stall-Control Devices at a Reynolds Number of 4.0 X 10 (Exp 6)
- Low-Speed Investigation of the Aerodynamic, Control, and Hinge-Moment Characteristics of Two Types of Controls on a Delta-Wing-Fuselage Model With and Without Nacelles
- Measurements of Heat-Transfer and Friction Coefficients for Air Flowing in a Tube of Length-Diameter Ratio of 15 at High Surface Temperatures
- Investigation of the Effect of Spanwise Positioning of a Vertically Symmetric Ogive-Cylinder Nacelle on the High-Speed Aerodynamic Characteristics of a 45 Degree Sweptback Tapered-in-Thickness Wing of Aspect Ratio 6 With and Without a Fuselage
- Investigation of the Effects of Leading-Edge Flaps on the Aerodynamic Characteristics in Pitch at Mach Numbers From 0.40 to 0.93 of a Wing-Fuselage Configuration With a 45 Degree Sweptback Wing of Aspect Ratio 4
- An Investigation of Continuous Boundary-Layer Removal in an Axial Flow Compressor With Porous Walls
- Investigation of Effects of Grain Size Upon Engine Life of Cast AMS 5385 Gas Turbine Blades
- Investigation of Blade Failures in a J34, Eleven-Stage Axial-Flow Compressor
- Investigation of Reynolds Number Effects for a Series of Cone-Cylinder Bodies at Mach Numbers of 1.62, 1.93, and 2.41
- Investigation of an Axial-Flow Compressor Rotor Having Naca High-Speed Blade Sections (A(Sub 2)I(Sub 8B) Series) at Mean Radius Relative Inlet Mach Numbers Up to 1.13
- Method of Estimating the Incompressible-Flow Pressure Distribution of Compressor Blade Sections at Design Angle of Attack
- Flight Measurement of Aerodynamic Loads and Moments on an External Store Mounted Under the Wing of a Swept-Wing Fighter-Type Airplane
- Gust-Tunnel Investigation to Determine Effects of Center-of-Gravity Position on the Gust Loads of a Delta-Wing Model With Leading Edge Swept Back 60 Degrees
- Gust-Tunnel Investigation of the Effect of Leading Edge Separation on the Normal Accelerations Experienced by a 45 Degree Sweptback-Wing Model in Gusts
- Investigation of the NACA 1.167-(0)(03)-058 and NACA 1.167-(0)(05)-058 Three-Blade Propellers at Forward Mach Numbers to 0.92 Including Effects of Thrust-Axis Inclination
- Measurements of Aerodynamic Characteristics at Transonic Speeds of an Unswept and Untapered NACA 65-009 Airfoil Model of Aspect Ratio 3 With 1/4-Chord Plain Flap by the NACA Wing-Flow Method
- Investigation of the Effects of Wing and Tail Modifications on the Low-Speed Stability Characteristics of a Model Having a Thin 40 Degree Swept Wing of Aspect Ratio 3.5
- Investigation of the Effect of Chordwise Positioning and Shape of an Underwing Nacelle on the High-Speed Aerodynamic Characteristics of a 45 Degree Sweptback Tapered-in-Thickness-Ratio Wing of Aspect Ratio 6
- Investigation of Spoilers at a Mach Number of 1.93 to Determine the Effects of Height and Chordwise Location on the Section Aerodynamic Characteristics of a Two-Dimensional Wing
- Investigation of Turbines for Driving Supersonic Compressors 5: Design and Performance of Third Configuration With Nontwisted Rotor Blades
- Investigation of Turbines for Driving Supersonic Compressors 3: First Configuration With Four Nozzle Settings and One Nozzle Modification
- Investigation of Turbines for Driving Supersonic Compressors 4: Design and Performance of Second Configuration Including Study of Three-Dimensional Flow Effects
- Analysis of Heat Transfer and Fluid Friction for Fully Developed Turbulent Flow of Supercritical Water With Variable Fluid Properties in a Smooth Tube
- The Influence of a Change in Body Shape on the Effects of Twist and Camber as Determined by a Transonic Wind-Tunnel Investigation of a 45 Degree Sweptback Wing-Fuselage Configuration
- Free-Spinning-Tunnel Investigation to Determine the Effect on Spins and Recoveries of Wing Leading-Edge Chord-Extensions and Drooped Leading-Edge Flaps on Scale Models of Two Sweptback-Wing Fighter Airplanes
- Free-Fall Measurements of the Effects of Wing-Body Interference on the Transonic Drag Characteristics of Swept-Wing-Slender-Body Configurations
- A Free-Flight Investigation at Zero Lift in the Mach Number Range Between 0.7 and 1.4 to Determine the Effectiveness of an Inset Tab as a Means of Aerodynamically Relieving Aileron Hinge Moments
- The Influence of the Control-Surface-Servo Natural Frequency Upon the Transient Characteristics of a Flight-Path-Angle Control System Incorporating a Supersonic Missile
- Horizontal-Tail Load Measurements at Transonic Speeds of the Bell X-1 Research Airplane
- Fuselage Pressures Measured on the Bell X-1 Research Airplane in Transonic Flight
- Flight Measurements of Pressures on Base and Rear Part of Fuselage of the Bell X-1 Research Airplane at Transonic Speeds, Including Power Effects
- Flight Measurements of Lift and Drag for the Bell X-1 Research Airplane Having a 10-Percent-Thick Wing
- Formulas for the Elastic Constants of Plates With Integral Waffle-Like Stiffening
- Flow Diffusion in a Constant-Diameter Duct Downstream of an Abruptly Terminated Center Body
- An Investigation at Mach Number 2.40 of Flap-Type Controls Equipped With Overhang Nose Balances
- An Investigation at Transonic Speeds of the Effects of Fences, Drooped Nose, and Vortex Generators on the Aerodynamic Characteristics of a Wing-Fuselage Combination Having a 6-Percent-Thick, 45 Degree Sweptback Wing
- Investigation at Low Speed of the Flow Field Behind the Lifting Surfaces of a Model Equipped With a 60 Degree Triangular Wing and a 60 Degree Triangular Canard Tail
- Investigation at Mach Numbers of 1.62, 1.93, and 2.41 of the Effect of Oscillation Amplitude on the Damping in Pitch of Delta-Wing-Body Combinations
- Investigation of a Ram-Jet-Powered Helicopter Rotor on the Langley Helicopter Test Tower
- Investigation at Transonic Speeds of a Forward-Located Underslung Air Inlet on a Body of Revolution