Search
Search U.S. government technical reports digitized or harvested by TRAIL.
Keyword Search
7169 results returnedSearch results
- The Effect of an Operating Propeller on the Aerodynamic Characteristics of a 1/10-Scale Model of the Lockheed XFV-1 Airplane at High Subsonic Speeds (TED No. NACA DE-377)
- Concerning the Flow About Ring-Shaped Cowlings Part 9: The Influence of Oblique Oncoming Flow on the Incremental Velocities and Air Forces at the Front Part of Circular Cowls
- On Rotational Conical Flow
- Amplitude of Supersonic Diffuser Flow Pulsations
- Wind-Tunnel Investigation of the Static Longitudinal Stability Characteristics of a 0.15-Scale Model of the Hermes A-1E2 Missile at High Subsonic Mach Numbers
- An Approximate Method of Calculating the Deformations of Wings Having Swept, M or W, A, and Swept-Tip Plan Forms
- Some Experiences Regarding the Nonlinearity of Hot Wires
- Small-Scale Transonic Investigation of the Effects of Partial-Span Leading-Edge Camber on the Aerodynamic Characteristics of a 50 Degree 38' Sweptback Wing of Aspect Ratio 2.98
- Thirty-Seventh Annual Report of the National Advisory Committee for Aeronautics: Administrative Report Including Technical Report Nos. 1003 to 1058
- Time-History Data of Maneuvers Performed by an F-86A Airplane During Squadron Operational Training
- A method of calibrating airspeed installations on airplanes at transonic and supersonic speeds by the use of accelerometer and attitude-angle measurements
- Analysis of V-g records from the Grumman F8F-2 airplane
- Performance Characteristics at Mach Numbers to 2.0 of Various Types of Side Inlets Mounted on Fuselage of Proposed Supersonic Airplane 2: Inlets Utilizing Half of a Conical Spike
- Preliminary Investigation of the Low-Amplitude Damping in Pitch of Tailless Delta- and Swept-Wing Configurations at Mach Numbers From 0.7 to 1.35
- Preliminary Results of Horizontal-Tail Load Measurements of the Bell X-5 Research Airplane
- Preliminary Tank Tests of Some Hydro-Ski-Wheel Combinations in the Planing Condition
- An Experimental Investigation of the Base Pressure Characteristics of Nonlifting Bodies of Revolution at Mach Numbers From 2.73 to 4.98
- Experimental Investigation of the Effects of Vortex Generators on the Maximum Lift of a 6-Percent-Thick Symmetrical Circular-Arc Airfoil Section
- Experimental Investigation of Internal Flow Characteristics of Forward Underslung Fuselage Scoops With Unswept Entrances at Mach Numbers of 1.41 to 1.96
- Some Low-Speed Studies of the Effects of Wing Location on Wing-Deformation-Body-Freedom Flutter
- Rocket-Model Investigation to Determine the Force and Hinge-Moment Characteristics of a Half-Delta Tip Control on a 59 Degree Sweptback Delta Wing Between Mach Numbers of 0.55 and 1.43
- Rocket-Model Investigation of the Rolling Effectiveness of a Fighter-Type Wing-Control Configuration at Mach Numbers From 0.6 to 1.5
- Preliminary Investigation of the Effects of Inlet Asymmetry on the Performance of Converging-Diverging Diffusers at Transonic Speeds
- A Preliminary Low-Speed Wind-Tunnel Investigation of a Thin Delta Wing Equipped With a Double and a Single Slotted Flap
- A Preliminary Investigation of the Static and Dynamic Longitudinal Stability of a Grunberg Hydrofoil System
- Time-History Data of Maneuvers Performed by McDonnell F2H-2 Airplane During Squadron Operational Training
- Total-Pressure and Schlieren Studies of the Wakes of Various Canard Control Surfaces Mounted on a Missile Body at a Mach Number of 1.93
- Total-Pressure Recovery of a Circular Underslung Inlet With Three Different Nose Shapes at a Mach Number of 1.42
- Transonic Drag Characteristics and Pressure Distribution on the Body of a Wing-Body Combination Consisting of a Body of Revolution of Fineness Ratio 12 and a Wing Having Sweepback of 45 Degrees, Aspect Ratio 4, Taper Ratio 0.6, and NACA 65A006 Airfoil Sections
- Transonic Flight Tests to Compare the Zero-Lift Drags of 45 Degree Sweptback Wings of Aspect Ratio 3.55 and 6.0 With and Without Nacelles at the Wing Tips
- Transonic Flight Tests to Determine Zero-Lift Drag and Pressure Recovery of Nacelles Located at the Wing Tips on a 45 Degree Sweptback Wing and Body Combination
- Use of an Aerodynamically Pulsed All-Movable Horizontal Tail to Obtain Longitudinal Characteristics of Rocket-Powered Models in Free Flight and Some Initial Results From an Arrow-Wing-Body-Tail Configuration
- A Transonic Wind-Tunnel Investigation of the Aerodynamic Characteristics of Three 4-Percent-Thick Wings of Sweepback Angles 10.8 Degrees, 35 Degrees, and 47 Degrees, Aspect Ratio 3.5, and Taper Ratio 0.2 in Combination With a Body
- Pressure Distributions on Bodies of Revolution at Subsonic and Transonic Speeds
- Pressure Distributions at Mach Numbers From 0.6 to 1.9 Measured in Free Flight on a Parabolic Body of Revolution With Sharply Convergent Afterbody
- Pressure Distribution and Aerodynamic Coefficients Associated With Heat Addition to Supersonic Air Stream Adjacent to Two-Dimensional Supersonic Wing
- Pressure Measurements on an Ogive-Cylinder Body at Mach Number 4.04
- Propeller Induced Angles of Attack and Section Angles of Attack for the NACA 10-(3)(066)-03, 10-(3)(049)-03, 10-(3)(090)-03, 10-(5)(066)-03, and 10-(0)(066)-03 Propellers
- Propeller Lift and Thrust Distribution From Wake Surveys of Stagnation Conditions
- Some Effects of Aeroelasticity at Mach Numbers From 0.7 to 1.6 on the Rolling Effectiveness of Thin Flat-Plate Delta Wings Having 45 Degree Swept Leading Edges and Full-Span Constant-Chord Ailerons
- Some Effects of Spoiler Height, Wing Flexibility, and Wing Thickness on Rolling Effectiveness and Drag of Unswept Wings at Mach Numbers Between 0.4 and 1.7
- Theoretical Calculation of the Effect of the Fuselage on the Spanwise Lift Distribution on a Wing
- Theoretical Damping in Roll and Rolling Moment Due to Differential Wing Incidence for Slender Cruciform Wings and Wing-Body Combinations
- Time Histories of Maneuvers Performed With an F-86A Airplane During Squadron Operations
- The Use of the Rolled-Up Vortex Concept for Predicting Wing-Tail Interference and Comparison With Experiment at Mach Number of 1.62 for a Series of Missile Configurations Having Tandem Cruciform Lifting 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: Effects of Controlling the Chordwise Distribution of Suction Air Velocities
- Wind-Tunnel Investigation of a Shielded Total-Pressure Tube at Transonic Speeds
- Wind-Tunnel Investigation at High and Low Subsonic Mach Numbers of a Thin Sweptback Wing Having an Airfoil Section Designed for High Maximum Lift
- Wind-Tunnel Investigation at High Subsonic Speeds of Spoilers of Large Projection on an NACA 65A006 Wing With Quarter-Chord Line Swept Back 32.6 Degrees
- A Wind-Tunnel Investigation at Low Speeds of the Aerodynamic Characteristics of Various Spoiler Configurations on a Thin 60 Degrees Delta Wing