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- A Brief Hydrodynamic Investigation of a Navy Seaplane Design Equipped With a Hydro-Ski
- Calculated Lateral Frequency Response and Lateral Oscillatory Characteristics for Several High-Speed Airplanes in Various Flight Conditions
- Data on Spoiler-Type Ailerons
- The Design of Brittle-Material Blade Roots Based on Theory and Rupture Tests of Plastic Models
- Effect of Certain Combinations of Wall Contouring and Design Exit Velocity Distribution on Prediction of Turbine-Nozzle Mass Flow
- Experimental Determination of Gas Motion Accompanying Screeching Combustion in a 6-Inch Simulated Afterburner
- Effect of Inlet-Air Temperature on Performance of a 16-Inch Ram-Jet Combustor
- Effect of Reduction in Thickness From 6 to 2 Percent and Removal of the Pointed Tips on the Subsonic Static Longitudinal Stability Characteristics of a 60-Degree Triangular Wing in Combination With a Fuselage
- Effects of Compressibility at Mach Numbers Up to 0.8 on Internal-Flow Characteristics of a Cowling-Spinner Combination Equipped With an Eight-Blade Dual-Rotation Propeller
- Effects of Fuel Temperature and Fuel Distribution on the Combustion Efficiency of a 16-Inch Ram-Jet Engine at a Simulated Mach Number of 2.9
- Effect of Fuel-Air Ratio Concentration in Combustion Zone on Combustion Performance of a 16-Inch Ram-Jet Engine
- Effect of Fuel Injector Location and Mixture Control on Performance of a 16-Inch Ram-Jet Can-Type Combustor
- Downwash Behind a Triangular Wing of Aspect Ratio 3 - Transonic Bump Method
- Drag Measurements at Low Lift of a Four-Nacelle Airplane Configuration Having a Longitudinal Distribution of Cross-Sectional Area Conducive to Low Transonic Drag Rise
- Flight Measurements of the Stability Characteristics of the Bell X-5 Research Airplane in Sideslips at 59 Degrees Sweepback
- 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