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- Elliptic Functions and Integrals with Real Modulus in Fluid Mechanics
- Extreme Speeds and Thermodynamic States in Supersonic Flight
- Evaporation, Heat Transfer, and Velocity Distribution in Two-Dimensional and Rotationally Symmetrical Laminar Boundary-Layer Flow
- Free Convection Under the Conditions of the Internal Problem
- A Correlation of Results of Flight Investigation With Results of an Analytical Study of Effects of Wing Flexibility on Wing Strains Due to Gusts
- Effect of Target-Type Thrust Reverser on Transonic Aerodynamic Characteristics of a Single-Engine Fighter Model
- Effects of Boattail Area Contouring and Simulated Turbojet Exhaust on the Loading and Fuselage-Tail Component Drag of a Twin-Engine Fighter-Type Airplane Model
- Aerodynamic Research on Fuselages with Rectangular Cross Section
- Measurements of the Buffeting Loads on the Wing and Horizontal Tail of a 1/4-Scale Model of the X-1E Airplane
- NACA Conference on High-Speed Aerodynamics
- Longitudinal and Lateral Stability and Control Characteristics and Vertical-Tail-Load Measurements for a 0.03-Scale Model of the Avro CF-105 Airplane at Mach Numbers of 1.60, 1.80, and 2.00
- NACA Research on Slurry Fuels
- An Investigation of the Free-Spinning and Recovery Characteristics of a 1/24-Scale Model of the Grumman F11F-1 Airplane With Alternate Nose Configurations With and Without Wing Fuel Tanks, TED No. NACA AD 395
- Stability of Cylindrical and Conical Shells of Circular Cross Section, with Simultaneous Action of Axial Compression and External Normal Pressure
- The Turbulent Boundary Layer on a Rough Curvilinear Surface
- Statistical Study of Turbulence: Spectral Functions and Correlation Coefficients
- Longitudinal and lateral aerodynamic characteristics at combined angles of attack and sideslip of a generalized missile model having a rectangular wing at a Mach number of 4.08
- Preliminary Analysis of a Nuclear-Powered Supersonic Airplane Using Ramjet Engines
- Off-Design Performance of Divergent Ejectors
- Performance at Mach Numbers 3.07, 1.89, and 0 of Inlets Designed for Inlet-Engine Matching Up to Mach 3
- Preliminary Study of Airplane Configurations Having Tail Surfaces Outboard of the Wing Tips
- Experimental Thermal Conductivities of the N2D4 Is in Equilibrium to 2NO2 System
- An Exploratory Investigation at Mach Numbers of 2.50 and 2.87 of a Canard Bomber-Type Configuration Designed for Supersonic Cruise Flight
- Feasibility of Nose-Cone Cooling by the Upstream Ejection of Solid Coolants at the Stagnation Point
- Experimental Investigation of a 7-Inch-Tip-Diameter Transonic Turbine
- Experimental Investigation of Turbojet-Engine Multiple-Loop Controls for Non-Afterburning and Afterburning Modes of Engine Operation
- An Experimental Investigation of Two Internal-Compression Air-Inlet Designs Which Use Fluid Boundaries as a Means of Supersonic Compression
- Temperature and Thermal-Stress Distributions in Some Structural Elements Heated at a Constant Rate
- Section Thrust Coefficients for a Full-Scale, Three-Blade, Supersonic-Type Propeller Operating at Low and Negative Blade Angles
- Slip-Flow Heat Transfer From Cylinders in Subsonic Airstreams
- Some Effects of Fin Leading-Edge Shape on Aerodynamic Heating at Mach Number 2.0 at a Stagnation Temperature of About 2,600 Degrees R
- Some Effects of Reynolds Number on the Stability of a Series of Flared-Body and Blunted-Cone Models at Mach Numbers Form 1.62 to 6.86
- Some Effects of Mass Ratio on the Transonic Flutter Characteristics of Untapered 45 Degree Sweptback Wings of Aspect Ratios 2 and 3.5
- Some Measurements of Aerodynamic Forces and Moments at Subsonic Speeds on a Rectangular Wing of Aspect Ratio 2 Oscillating About the Midchord
- Rocket-Model Investigation to Determine the Lift and Pitching Effectiveness of Small Pulse Rockets Exhausted From the Fuselage Over the Surface of an Adjacent Wing at Mach Numbers From 0.9 to 1.8
- Shape of Initial Portion of Boundary of Supersonic Axisymmetric Free Jets at Large Jet Pressure Ratios
- Preliminary Survey of Propulsion Using Chemical Energy Stored in the Upper Atmosphere
- Theoretical Investigation of Subsonic Oscillatory Blade-Row Aerodynamics
- Behavior of Some Materials and Shapes in Supersonic Free Jets at Stagnation Temperatures Up to 4,210 Degrees F, and Descriptions of the Jets
- Effects of Propeller Position and Overlap on the Slipstream Deflection Characteristics of a Wing-Propeller Configuration Equipped With a Sliding and Fowler Flap
- Transient Temperature Distribution in a Two-Component Semi-Infinite Composite Slab of Arbitrary Materials Subjected to Aerodynamic Heating With a Discontinuous Change in Equilibrium Temperature or Heat-Transfer Coefficient
- Transonic Characteristics of Outboard Ailerons on a 4-Percent-Thick 30 Degree Sweptback Wing, Including Some Effects of Aileron Trailing-Edge Thickness and Aerodynamic Balance
- Transonic Flutter Investigation of Models of the All-Movable Horizontal Tail of a Fighter Airplane
- Transonic Flutter Investigation of Models of the Sweptback Wing of a Fighter Airplane
- Qualitative Measurements of the Effective Heats of Ablation of Several Materials in Supersonic Air Jets at Stagnation Temperatures Up to 11,000 Degrees F
- Subsonic Flight Investigation of Methods to Improve the Damping of Lateral Oscillations by Means of a Viscous Damper in the Rudder System in Conjunction With Adjusted Hinge-Moment Parameters
- Summary of Flutter Experiences as a Guide to the Preliminary Design of Lifting Surfaces on Missiles
- Some Effects of Roughness on Stagnation-Point Heat Transfer at a Mach Number of 2, a Stagnation Temperature of 3,530 F, and a Reynolds Number of 2.5 X 10(Exp 6) Per Foot
- Use of Shock-Trap Bleed to Improve Pressure Recovery of Fixed-and Variable-Capture-Area Internal-Contraction Inlets; Mach Number 2.0 to 3.0
- Use of Highly Reactive Chemical Additives to Improve Afterburner Performance at Altitude