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- Influence of Automatic Control of Roll Coupling and Pitch-Up on Tail Loads
- Influence of Boric Oxide Deposition on Turbojet-Engine Operation
- A Note on the Ability to Predict Transonic Drag-Rise Changes Due to Model Modifications
- NACA Conference on Aircraft Loads, Structures, and Flutter
- Comparative Study of Turbofan and Turbojet Engines
- Comparison and Evaluation of Two Model Techniques Used in Predicting Bomb-Release Motions
- Cascade Investigation of Cooling Characteristics of a Castfinned Air-Cooled Turbine Blade for Use in a Turboprop Engine
- The Design and Cascade Tests of Free-Streamline and Full-Contour 160 Degree Turning Supersonic-Turbine-Blade Sections
- Calculation of External-Store Loads and Correlation With Experiment
- Comparison of Experimental and Theoretical Zero-Lift Wave-Drag Results for Various Wing-Body-Tail Combinations at Mach Numbers Up to 1.9
- Aerodynamic Loads on Tails at High Angles of Attack and Sideslip
- Altitude Performance of a Turbojet Engine Using Pentaborane Fuel
- Analyses for Turbojet Thrust Augmentation With Fuel-Rich Afterburning of Hydrogen, Diborane, and Hydrazine
- Analytical Investigation of Fuel-Cooled Turbine Blades With Return-Flow Type of Finned Coolant Passages
- Use of Constant Diffuser Mach Number as a Control Parameter for Variable-Geometry Inlets at Mach Numbers of 1.8 to 2.0
- Wind-Tunnel Investigation at High Subsonic Speeds of the Effects on Static Stability Characteristics of Various Modifications to a Swept-Wing Fighter-Type Airplane Model
- A Wind-Tunnel Investigation of the Effects of Conical Camber for an Airplane Configuration Having a Triangular Wing of Aspect Ratio 2.2
- Wind-Tunnel Tests of the Static Longitudinal Characteristics at Low Speed of a Swept-Wing Airplane With Blowing Flaps and Leading-Edge Slats
- Aerodynamics of Oscillating Control Surfaces at Transonic Speeds
- Material Compatibility With Gaseous Fluorine
- Measurement of Static Forces on Internally Carried Bombs of Three Fineness Ratios in Flow Field of a Swept-Wing Fighter-Bomber Configuration at a Mach Number of 1.61 With Illustrative Drop Path Calculations
- Flight Investigation of Pentaborane Fuel in 9.75-inch-diameter Ram-jet Engine With Downstream Fuel Injection
- High-Altitude Performance of J71-A-11 Turbojet Engine and Its Components Using JP-4 and Gaseous-Hydrogen Fuels
- Investigation of Ejection Releases of an MB-1 Rocket From a 0.04956-Scaled Model of the Convair F-106A Airplane at Mach Number 1.59
- Investigation of Ejection Releases of an MB-1 Rocket From a 0.04956-Scaled Model of the Convair F-106A Airplane at Mach Number 1.59
- Investigation of the Low-Speed Flight Characteristics of a 1/15-Scale Model of the Convair XB-58 Airplane
- Wind-Tunnel Tests of a Series of Practice Bombs
- Transonic Flutter Investigation of an All-Movable Horizontal Tail for a Fighter Airplane
- Dynamic Stability Investigation of Two Right Circular Cylinders in Axial Free Flight at Mach Numbers From 0.4 to 1.7 Fineness-Ratio- 2.56 Cylinder and Fineness-Ratio-4.0 Cylinder With Flared Afterbody
- Experimental Performance of a 5000-Pound-Thrust Rocket Chamber Using a 20-Percent-Fluorine - 80-Percent-Oxygen Mixture With RP-1
- Experimental Investigation of the Transonic and Supersonic Flutter Characteristics of the Upper and Lower Vertical Tails of an Air-to-Ground Missile
- Effect of Hinge-Line Position on the Oscillating Hinge Moments and Flutter Characteristics of a Flap-Type Control at Transonic Speeds
- Investigation of a 0.6 Hub-Tip Radius-Ratio Transonic Turbine Designed for Secondary-Flow Study 2 - Design and Experimental Performance of Turbine With Low-Velocity-Turning Stator and Standard Rotor
- Investigation of a 0.6 Hub-Tip Radius-Ratio Transonic Turbine Designed for Secondary-Flow Study 3 - Experimental Performance With Two Stator Configurations Designed to Eliminate Blade Wakes and Secondary-Flow Effects and Conclusions From Entire Stator Investigation
- Investigation of an Afterburning Ramjet Using Gaseous Hydrogen as Fuel at Mach Number of 3.0
- Investigation of an Air-Cooled, Plug-Type, Variable-Area Exhaust Nozzle
- Investigation of an Underslung Normal-Wedge Inlet at Free-Stream Mach Numbers From 1.50 to 1.99
- Investigation of an Underslung Scoop Inlet at Mach Numbers to 1.99
- Investigation of Drag and Static Longitudinal and Lateral Stability Characteristics of a Model of a 40.4 Degree Swept-Wing Airplane at Mach Numbers of 1.56 and 2.06
- Investigation of Ejection Releases of an MB-1 Rocket From a 0.04956-Scaled Model of the Convair F-106A Airplane at Several Mach Numbers and Simulated Altitudes
- Investigation of Rotating-Stall Limits in a Supersonic Turbofan Engine
- Heat Transfer in Regions of Separated and Reattached Flows
- In-Flight Gains Realized by Modifying a Twin Side-Inlet Induction System
- Investigation of High-Angle-of-Attack Performance of a 14 Deg Ramp-Type Inlet in Various Circumferential Body Locations: Mach Number Range 1.5 to 2.0
- Investigation of Static Pressures and Boundary-Layer Characteristics on the Forward Parts of Nine Fuselages of Various Cross-Sectional Shapes at M Infinity Equal 2.01
- Analysis of Fluorine Addition to the Vanguard First Stage
- Brief Studies of Turbojet Combustor and Fuel-System Operation With Hydrogen Fuel at -400 Degrees F
- Aerodynamic Forces and Moments on a Large Ogive-Cylinder Store at Various Locations Below the Fuselage Center Line of a Swept-Wing Bomber Configuration at a Mach Number of 1.61
- Simplified Theory for Dynamic Relation of Ramjet Pressures and Fuel Flow
- Some Factors Affecting the Static Longitudinal and Directional Stability Characteristics of Supersonic Aircraft Configurations