Search
Search U.S. government technical reports digitized or harvested by TRAIL.
Keyword Search
4176 results returnedSearch results
- The Effect of Wind Bending Deflection on the Rolling Moment Due to Sideslip
- A Device for Measuring Sonic Velocity and Compressor Mach Number
- Method for Calculation of Pressure Distributions on Thin Conical Bodies of Arbitrary Cross Section in Supersonic Stream
- De-Icing Effectiveness of External Electric Heaters for Propeller Blades
- Characteristics of Low-Aspect Ratio Wings at Supercritical Mach Numbers
- Buckling Tests of Flat Rectangular Plates Under Combined Shear and Longitudinal Compression
- Tensile and Compressive Properties of Laminated Plastics at High and Low Temperatures
- Effect of Partial Wing Lift in Seaplane Landing Impact
- Shear Flows in Multicell Sandwich Sections
- Fracture Strength of 75S-T Aluminum Alloy Under Combined Stress
- Analytical Method of Determining Transmission of Particles and Radiation Through Great Thickness of Matter
- An Improved Photoelastic Method for Determining Plane Stresses
- An Investigation of the Low-Speed Static Stability Characteristics of Complete Models Having Sweptback and Sweptforward Wings
- Cyclic Engine Test of Cast Vitallium Turbine Buckets 2
- Effect of Aerodynamic Hysteresis on Critical Flutter Speed at Stall
- Effect of Centrifugal Force on Critical Flutter Speed on a Uniform Cantilever Beam
- Efficiency of Radial-Flow Turbine of Turbo Engineering Corporation TTT13-18 Turbosupercharger
- Results Obtained During Extension of U.S. Air Force Transonic-Flight Tests of XS-1 Airplane
- Indirect Methods for Obtaining Ram-Jet Exhaust-Gas Temperature Applied to Fuel-Metering Control
- Wind-Tunnel Investigation of Horizontal Tails 1: Unswept and 35 Degrees Swept-Back Plan Forms of Aspect Ratio 3
- High-Speed Aerodynamic Characteristics of a Model Tail Plane with Modified NACA 65-010 Sections and 0 Degree and 45 Degrees Sweepback
- High-Speed Aerodynamic Characteristics of a Lateral-Control Model 1: NACA 0012-64 Section with 20-Percent-Chord Plain Aileron and 0 Degree and 45 Degrees Sweepback
- The High-Speed Aerodynamic Effects of Modifications to the Wing and Wing-Fuselage Intersection of an Airplane Model with the Wing Swept Back 35 Degrees
- High-Speed Stability and Control Characteristics of a Fighter Airplane Model with a Swept-Back Wing and Tail
- Relation of Nozzle-Blade and Turbine-Bucket Temperatures to Gas Temperatures in a Turbojet Engine
- Theoretical and Experimental Analysis of Low-Drag Supersonic Inlets Having a Circular Cross Section and a Central Body at Mach Numbers of 3.30, 2.75, and 2.45
- On the Theory of Oscillating Airfoils of Finite Span in Subsonic Compressible Flow
- Comparison of Theoretical and Experimental Heat-Transfer Characteristics of Bodies of Revolution at Supersonic Speeds
- Prediction of the Effects of Propeller Operation on the Static Longitudinal Stability of Single-Engine Tractor Monoplanes with Flaps Retracted
- Method of Estimating the Minimum Size of a Tail or Wing-Tip Parachute for Emergency Spin Recovery of an Airplane
- Theoretical Stability Derivatives of Thin Sweptback Wings Tapered to a Point with Sweptback or Sweptforward Trailing Edges for a Limited Range of Supersonic Speeds
- Wind-Tunnel Investigation of High-Lift and Stall-Control Devices on a 37 Degree Sweptback Wing of Aspect Ratio 6 at High Reynolds Numbers
- Ditching Tests of a 1/18-Scale Model of the Lockheed Constellation Airplane
- Ditching Tests of Two Models of the Army B-36 Airplane
- Ditching Tests of a 1/24-Scale Model of the Lockheed XR60-1 Airplane, TED No. NACA 235
- A Restricted List of Aircraft Materials Research Projects
- The Method of Characteristics for the Determination of Supersonic Flow Over Bodies of Revolution at Small Angles of Attack
- Residual Stress Analysis of Overspeeded Disk With Central Hole by X-Ray Diffraction
- One-Dimensional Flows of an Imperfect Diatomic Gas
- The Effectiveness at High Speeds of a 10-Percent-Chord Plain Trailing-Edge Flap on the NACA 65-210 Airfoil Section
- Experiments on Stability of Bunsen-Burner Flames for Turbulent Flow
- The Effects of Fuel Sloshing on the Lateral Stability of a Free-Flying Airplane Model
- Pressure Recovery at Supersonic Speeds Through Annular Duct Inlets Situated in a Region of Appreciable Boundary Layer 2: Effect of an Oblique Shock Wave Immediately Ahead of the Inlet
- Performance of a Ram-Jet-Type Combustor With Flame Holders Immersed in the Combustion Zone
- Note on the Importance of Imperfect-Gas Effects and Variation of Heat Capacities on the Isentropic Flow of Gases
- Results Obtained During Accelerated Transonic Tests of the Bell XS-1 Airplane in Flights to a Mach Number of 0.92
- A Method for Calculating Flow Fields of Cowlings with Known Surface-Pressure Distributions
- Wind-Tunnel Investigation of Horizontal Tails 4: Unswept Plan Form of Aspect Ratio 2 and a Two-Dimensional Model
- Effect of High-Lift Devices on the Low-Speed Static Lateral and Yawing Stability Characteristics of an Untapered 45 Degrees Sweptback Wing
- Wind-Tunnel Investigation of Horizontal Tails 2: Unswept and 35 Degree Swept-Back Plan Forms of Aspect Ratio 4.5