Browse TRAIL Inventories

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


Published Year

Subject

Author

‹‹ previous 1 2 ... 140 141 142 143 144 next ››