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- A Cooled-Gas Pyrometer for Use in High-Temperature Gas Streams
- Effects of Wing Sweep, Horizontal-Tail Configuration, and a Ventral Fin on Static Stability Characteristics of a Model With a Wing of Aspect Ratio 3 at Mach Numbers From 2.29 to 4.65
- Elevated-Temperature Combined Stress-Rupture Plus Fatigue Strength of Waspaloy Having Different Aging Treatments and/or Molybdenum Contents
- Effects of Boundary-Layer Displacement and Leading-Edge Bluntness on Pressure Distribution, Skin Friction, and Heat Transfer of Bodies at Hypersonic Speeds
- Effect of Spike-Tip and Cowl-Lip Blunting on Inlet Performance of a Mach 3.0 External-Compression Inlet
- Effects of External Store-Pylon Configuration and Position on the Aerodynamic Characteristics of a 45 Degree Swept Wing-Fuselage Combination at a Mach Number of 1.61
- The Effects of an Inverse-Taper Leading-Edge Flap on the Aerodynamic Characteristics in Pitch of a Wing-Body Combination Having an Aspect Ratio of 3 to 45 Degrees of Sweepback at Mach Numbers to 0.92
- Effects of Nose Shape and Spray Control Strips on Emergence and Planing Spray of Hydro-Ski Models
- Effects of Leading-Edge Slat and Trailing-Edge Split Flap on the Aerodynamic Characteristics of a Wing-Fuselage Combination Having a Nearly Triangular Wing of Aspect Ratio 2.9 at Mach Numbers From 0.60 to 0.92
- Effect of Distributed Granular-Type Roughness on Boundary-Layer Transition at Supersonic Speeds With and Without Surface Cooling
- The Effect of Compressor-Inlet Water Injection on Engine and Afterburner Performance
- A Comparison of Flight-Measured Carrier-Approach Speeds With Values Predicted by Several Different Criteria for 41 Fighter-Type Airplane Configurations
- Cumulative Fatigue Damage at Elevated Temperature
- Calculation of Flutter Characteristics for Finite-Span Swept or Unswept Wings at Subsonic and Supersonic Speeds by a Modified Strip Analysis
- Buffet Tests of an Attack-Airplane Model With Emphasis on Analysis of Data From Wind-Tunnel Tests
- Aerodynamic Characteristics at a Mach Number of 6.8 of Two Hypersonic Missile Configurations, One With Low-Aspect-Ratio Cruciform Fins and Trailing-Edge Flaps and One With a Flared Afterbody and All-Movable Controls
- Aerodynamic Load Distribution on a 45 Degree Sweptback Wing With Leading-Edge Chord-Extensions at Transonic Speeds, Including Effects of a Spoiler-Slot-Deflector Aileron
- Aerodynamic Characteristics at Mach Numbers From 2.5 to 3.5 of a Canard Bomber Configuration Designed for Supersonic Cruise Flight
- Aerodynamic Performance and Static Stability and Control of Flat-Top Hypersonic Gliders at Mach Numbers From 0.6 to 18
- Analytical and Experimental Investigation of Aerodynamic Forces and Moments on Low-Aspect-Ratio Wings Undergoing Flapping Oscillations
- Longitudinal Stability Investigation of a Vertical-Take-Off-and-Landing Airplane Configuration With Simulated Jet Intake and Exhaust at Mach Numbers of 1.61 and 2.01
- Low-Speed Boundary-Layer-Control Investigation on a Thin Rectangular Semispan Wing With Leading-Edge and Trailing-Edge Flaps
- Measurements of Aerodynamic Heat Transfer on a 15 Degree Cone-Cylinder-Flare Configuration in Free Flight at Mach Numbers Up to 4.7
- Investigation of Lithium Hydride and Magnesium as High-Temperature Internal Coolants With Several Skin Materials
- An Investigation of the Effects of Atmospheric Corrosion on the Fatigue Life of Aluminum Alloys
- An Investigation of the Effect of Target Temperature on Projectile Penetration and Cratering
- Investigation of Control Signals for Variable Ramps of Twin-Duct Side Inlets
- Investigation of an All-Moveable Control Surface at a Mach Number of 6.86 for Possible Flutter
- A Flight Investigation of the Effects of Varied Lateral Damping on the Effectiveness of a Fighter Airplane as a Gun Platform
- Heat Transfer to 0 Degree and 75 Degree Swept Blunt Leading Edges in Free Flight at Mach Numbers From 1.90 to 3.07
- High Mach Number, Low-Cowl-Drag, External-Compression Inlet With Subsonic Dump Diffuser
- Investigation of the Static Stability Characteristics of Five Hypersonic Missile Configurations at Mach Numbers From 2.29 to 4.65
- Investigation of Vortex Movements About a Wing in Steady Subsonic Flow Undergoing a Large Angle-of-Attack Change in a Blast-Induced Gust
- Measurements of Aerodynamic Forces and Moments at Subsonic Speeds on a Simplified T-Tail Oscillating in Yaw About the Fin Midchord
- Investigation of Minimum Drag and Maximum Lift-Drag Ratios of Several Wing-Body Combinations Including a Cambered Triangular Wing at Low Reynolds Numbers and at Supersonic Speeds
- 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 Tantalum in a 3,800 Degrees Fahrenheit Supersonic Airstream
- Investigation of Flutter Characteristics of Three Low-Aspect-Ratio All-Movable Half-Span Control Surfaces at Mach Numbers From 1.49 to 2.87
- Investigation of the Longitudinal Aerodynamic Characteristics of a Trapezoidal-Wing Airplane Model With Various Vertical Positions of Wing and Horizontal Tail at Mach Numbers of 1.41 and 2.01
- Analysis of Turbulent Flow and Heat Transfer in Noncircular Passages
- Experimental Investigation of the Lateral Trim of a Wing-Propeller Combination at Angles of Attack Up to 90 Degrees With All Propellers Turning in the Same Direction
- Theoretical Calculations of Supersonic Wave Drag at Zero Lift for a Particular Store Arrangement
- Theoretical Rocket Performance of JP-4 Fuel with Several Fluorine-Oxygen Mixtures Assuming Equilibrium Composition
- Theoretical Rocket Performance of Liquid Methane with Several Fluorine-Oxygen Mixtures Assuming Frozen Composition
- Hydrodynamic Characteristics of a Model of a Proposed Six-Engine Hull-Type Seaplane Designed for Supersonic Flight
- Flight Tests of Two Smoke-Producing Devices Having Deacon Rocket Boosters
- Heat Transfer for Mach Numbers Up to 2.2 and Pressure Distributions for Mach Numbers Up to 4.7 From Flight Investigations of a Flat-Face-Cone and a Hemisphere-Cone
- Heat Transfer Measured on a Flat-Face Cylinder-Flare Configuration in Free Flight at Mach Numbers From 1.6 to 2.7
- Further Investigation of Fatigue-Crack Propagation in Aluminum-Alloy Box Beams
- Heat-Transfer and Pressure Measurements From a Flight Test of the Second 1/18-Scale Model on the Titan Intercontinental Ballistic Missile Up to a Mach Number of 3.91 and Reynolds Number Per Foot of 23.4 X 10(Exp 6) : Coord. No. AF-AM-70