Search
Search U.S. government technical reports digitized or harvested by TRAIL.
Keyword Search
7169 results returnedSearch results
- Pressure Measurements on a Sharply Converging Fuselage Afterbody With Jet on and Off at Mach Numbers From 0.8 to 1.6
- Pressure-Rise and Leakage-Loss Characteristics of a Rotating Cowling
- Spin-Tunnel Investigation of a Model of a 60 Degree Delta-Wing Airplane to Determine the Spin, Recovery, and Longitudinal Trim Characteristics Throughout an Extensive Range of Mass Loadings
- Time Histories of Horizontal-Tail Loads, Elevator Loads, and Deformations on a Jet-Powered Bomber Airplane During Wind-Up Turns at Approximately 15,000 Feet and 22,500 Feet
- Wind-Tunnel Investigation at Low Speed of a Wing Swept-Back 63 Degrees and Twisted and Cambered for a Uniform Load at a Lift Coefficient of 0.5
- Wind-Tunnel Investigation at Low Speed of a Wing Swept Back 63 Degrees and Twisted and Cambered for Uniform Load at a Lift Coefficient of 0.5 and With a Thickened Tip Section
- Wind-Tunnel Investigation of the Effects of a Jet Engine Nacelle on the Aerodynamic Characteristics of a 37.25 Degree Swept Back Wing at High Subsonic Speeds
- Wind-Tunnel Investigation of the Low-Speed Longitudinal and Lateral Control Characteristics of a Triangular-Wing Model of Aspect Ratio 2.31 Having Constant-Chord Control Surfaces
- The Use of Area Suction for the Purpose of Delaying Separation of Air Flow at the Leading Edge of a 63 Degree Swept-Back Wing
- Theoretical Investigation of the Dynamic Lateral Stability Characteristics of the Douglas X-3 Research Airplane, Study 41-B
- The Effect of Spanwise Aileron Location on the Rolling Effectiveness of Wings With 0 Degree and 45 Degree Sweep at Subsonic, Transonic, and Supersonic Speeds
- The Effect of Sweepback on the Longitudinal Characteristics at a Mach Number of 1.24 of a 1/30 Scale Semispan Model of the Bell X-5 Airplane From Tests by the NACA Wing Flow Method
- Effects of Varying the Size and Location of Trailing-Edge Flap-Type Controls on the Aerodynamic Characteristics of a Unswept Wing at a Mach Number of 1.9
- Effects of Obstructions in Compressor Inlet on Blade Vibration in 10-Stage Axial-Flow Compressor
- Effect of Compressibility and Camber as Determined From an Investigation of the NACA 4-(3)(08)-03 and 4-(5)(08)-03 Two-Blade Propellers Up to Forward Mach Numbers of 0.925
- The Effect of Changes in the Leading-Edge Radius on the Aerodynamic Characteristics of a Symmetrical, 9-Percent-Thick Airfoil at High-Subsonic Mach Numbers
- Determination by the Free-Fall Method of the Drag and Longitudinal Stability and Control Characteristics of a Canard Model at Transonic Speeds
- Determination of Longitudinal Stability of the Bell X-1 Airplane From Transient Responses at Mach Numbers Up to 1.12 at Lift Coefficients of 0.3 and 0.6
- Ditching Tests With a 1/16-Size Model of the Navy XP2V-1 Airplane at the Langley Tank No. 2 Monorail
- Ditching Tests of a 1/18-Scale Model of the Lockheed Constellation Airplane
- Drag Investigation of Some Fin Configurations for Booster Rockets at Mach Numbers Between 0.5 and 1.4
- Calculated Lift Distributions of a Consolidated Vultee B-36 and Two Boeing B-47 Airplanes Coupled at the Wing Tips
- The Calculation of the Path of a Jettisonable Nose Section
- Damping in Yaw and Static Directional Stability of a Canard Airplane Model and of Several Models Having Fuselages of Relatively Flat Cross Section
- The Damping in Roll of Rocket-Powered Test Vehicles Having Rectangular Wings With NACA 65-006 and Symmetrical Double-Wedge Airfoil Sections of Aspect Ratio 4.5
- Aerodynamic Investigation of a Parabolic Body of Revolution at Mach Number of 1.92 and Some Effects of an Annular Jet Exhausting From the Base
- Aerodynamic Characteristics at a Mach Number of 1.38 of Four Wings of Aspect Ratio 4 Having Quarter-Chord Sweep Angles of 0 Degrees, 35 Degrees, 45 Degrees, and 60 Degrees
- Aerodynamic Characteristics at a Mach Number of 1.25 of a 6-Percent-Thick Triangular Wing and 6- and 9-Percent-Thick Triangular Wings in Combination With a Fuselage: Wing Aspect Ratio 2.31, Biconvex Airfoil Sections
- Ability of Pilots to Control Simulated Short-Period Yawing Oscillations
- Aerodynamic and Lateral-Control Characteristics of a 1/28-Scale Model of the Bell X-1 Airplane Wing-Fuselage Combination: Transonic-Bump Method
- Altitude-Chamber Performance of British Rolls-Royce Nene II Engine 3 - 18.00-Inch-Diameter Jet Nozzle
- Altitude Test Chamber Investigation of Performance of a 28-Inch Ram-Jet Engine 2: Effects of Gutter Width and Blocked Area on Operating Range and Combustion Efficiency
- Altitude-Test-Chamber Investigation of Performance of a 28-Inch Ram-Jet Engine 1: Combustion and Operational Performance of Four Combustion-Chamber Configurations
- Low-Speed Aerodynamic Characteristics of a Series of Swept Wings Having NACA 65A006 Airfoil Sections (Revised)
- Maximum-Lift Investigation of a 1/40-Scale X-1 Airplane Wing at Mach Numbers From 0.60 to 1.15
- Maximum-Lift Investigation at Mach Numbers From 0.05 to 1.20 of a Wing With Leading Edge Swept Back 42 Degrees
- Longitudinal Trim and Drag Characteristics of Rocket-Propelled Models Representing Two Airplane Configurations
- The Longitudinal Stability, Control Effectiveness, and Control Hinge Moment Characteristics Obtained From a Flight Investigation of a Canard Missile Configuration at Transonic and Supersonic Speeds
- Low-Speed Investigation of the Aerodynamic Loads on the Droop-Nose Flap of a Wing With Leading Edge Swept Back 47.5 Degrees and Having Symmetrical Circular-Arc Airfoil Sections at a Reynolds Number of 4.3 X 10 (Exp 6)
- Low-Speed Investigation of the Effect of Several Flap and Spoiler Ailerons on the Lateral Characteristics of a 47.5 Degree Sweptback-Wing-Fuselage Combination at a Reynolds Number of 4.4. X 10(6)
- Low-Speed Investigation of Deflectable Wing-Tip Elevators on a Low-Aspect-Ratio Untapered 45 Degree Sweptback Semispan Wing With and Without an End Plate
- Low-Speed Pressure-Distribution Measurements at Reynolds Number of 3.5 X 10(Exp 6) on a Wing With Leading-Edge Sweepback Decreasing From 45 Degrees at the Root to 20 Degrees at the Tip
- Investigation of Blade-Row Flow Distributions in Axial-Flow-Compressor Stage Consisting of Guide Vanes and Rotor-Blade Row
- Flight Investigation of the Pressure Distributions and Loads on a Front and Rear Sliding Canopy
- Flight Investigation of the Effect of Thickening the Aileron Trailing Edge on Control Effectiveness for Sweptback Tapered Wings Having Sharp-and Round-Nose Sections
- Flight Investigation of the Aileron Characteristics of the Douglas D-558-I Airplane (BuAero No. 37972) at Mach Numbers Between 0.6 and 0.89
- Flight Investigation of Longitudinal Stability and Control Characteristics and Stalling Characteristics of a C-54D Airplane
- Full-Scale Investigation of Boundary-Layer Control by Suction Through Leading-Edge Slots on a Wing-Fuselage Configuration Having 47.5 Degree Leading-Edge Sweep With and Without Flaps
- Longitudinal Stability and Control Characteristics at High Subsonic Speeds of Two Models of a Transonic Research Airplane With Wings and Horizontal Tails of Aspect Ratios 4.2 and 2
- Measurements of Aerodynamic Characteristics of a 35 Degree Sweptback NACA 65-009 Airfoil Model With 1/4-Chord Bevelled-Trailing-Edge Flap and Trim Tab by the NACA Wing-Flow Method