Browse TRAIL Inventories

A Finite Step Method for the Calculation of Span Loadings of Unusual Plan Forms

Flight Determination of Drag and Pressure Recovery of a Nose Inlet of Parabolic Profile at Mach Numbers From 0.8 to 1.7

An Experimental Investigation at Subsonic Speeds of a Scoop-Type Air-Induction System for a Supersonic Airplane

Flight Determination of the Effects of Wing Vortex Generators of the Aerodynamic Characteristics of the Douglas D-558-I Airplane

Some Effects of Fuselage Interference, Wing Interference, and Sweepback on the Damping in Roll of Untapered Wings as Determined by Techniques Employing Rocket-Propelled Vehicles

Some Experiments on the Flutter of Sweptback Cantilever Wing Models at Mach Number 1.3

Tabulated Pressure Coefficients and Aerodynamic Characteristics Measured in Flight on the Wing of the D-558-I Research Airplane Through a Mach Number Range of 0.80 to 0.89 and Throughout the Normal-Force-Coefficient Range at Mach Numbers of 0.61, 0.70, 0.855, and 0.88

Experimental Investigation of Flow in the Rotating Passages of a 48-Inch Impeller at Low Tip Speeds

Altitude Operation of Gas-Turbine Engine With Variable-Area Fuel-Nozzle System

Dynamic Longitudinal Stability and Control of Tandem Coupled Bomber-Fighter Airplane Models With Rigid and Pitch-Free Couplings

Time Histories of the Aerodynamic Loads on the Vertical and Horizontal Tail Surfaces of a Jet-Powered Bomber Airplane During Sideslip Maneuvers at Approximately 20,000 Feet

Results of Flight Tests to Determine Drag of Parabolic and Cone-Cylinder Bodies of Very Large Fineness Ratios at Supersonic Speeds

Summary of Spin and Recovery Characteristics of 12 Models of Flying-Wing and Unconventional-Type Airplanes

Theoretical Investigation of an Automatic Control System With Primary Sensitivity to Normal Accelerations as Used to Control a Supersonic Canard Missile Configuration

The Use of Suction to Prevent Shock-Induced Separation in a Nozzle

Water Landing Investigation of a Hydro-Ski Model at Beam Loadings of 18.9 and 4.4

Wind-Tunnel Investigation at Mach Numbers From 0.50 to 1.29 of an Unswept, Tapered Wing of Aspect Ratio 2.67 With Leading- and Trailing-Edge Flaps - Flaps Deflected in Combination

Wind-Tunnel Investigation at Subsonic and Low Transonic Speeds of the Effects of Aileron Span and Spanwise Location on the Rolling Characteristics of a Test Vehicle With Three Untapered 45 Degree Sweptback Wings

Altitude-Test-Chamber Investigation of Performance of a 28-Inch Ram-Jet Engine 4: Effect of Inlet-Air Temperature, Combustion-Chamber-Inlet Mach Number, and Fuel Volatility on Combustion Performance

Force and Pressure Characteristics for a Series of Nose Inlets at Mach Numbers From 1.59 to 1.99 4: Conical-Spike External-Internal Compression Inlet Utilizing Perforated Cowl

Wing-Flow Study of Pressure-Drag Reduction at Transonic Speed by Projecting a Jet of Air From the Nose of a Prolate Spheroid of Fineness Ratio 6

Application of Response Function to Calculation of Flutter Characteristics of a Wing Carrying Concentrated Masses

Critical Combinations of Bending, Shear, and Transverse Compressive Stresses for Buckling of Infinitely Long Flat Plates

The Effect on Zero-Lift Drag of an Indented Fuselage or a Thickened Wing-Root Modification to a 45 Degree Sweptback Wing-Body Configuration as Determined by Flight Tests at Transonic Speeds

Effects of Spoiler on Airfoil Pressure Distribution and Effects of Size and Location of Spoilers on the Aerodynamic Characteristics of a Tapered Unswept Wing of Aspect Ratio 2.5 at a Mach Number of 1.90

The Effects of Increasing the Leading-Edge Radius and Adding Forward Camber on the Aerodynamic Characteristics of a Wing With 35 Degrees of Sweepback

The Effect of End Plates, End Struts, and Depth of Submergence on the Characteristics of a Hydrofoil

A Comparison of Predicted and Experimentally Determined Longitudinal Dynamic Responses of a Stabilized Airplane

Comparison of Transonic Characteristics of Lifting Wings From Experiments in a Small Slotted Tunnel and the Langley High-Speed 7- by 10-Foot Tunnel

A Comparison of Two Techniques Utilizing Rocket-Propelled Vehicles for the Determination of the Damping-in-Roll Derivative

Comparison of Zero-Lift Drag Determined by Flight Tests at Transonic Speeds of Pylon, Underslung, and Symmetrically Mounted Nacelles at 40 Percent Semispan of a 45 Degrees Sweptback Wing and Body Combination

Comparison of Zero-Lift Drags Determined by Flight Tests at Transonic Speeds of Symmetrically Mounted Nacelles in Various Spanwise Positions on a 45 Degrees Sweptback Wing and Body Combination

Comparison of Zero-Lift Drags Determined by Flight Tests at Transonic Speeds of Symmetrically Mounted Nacelles in Various Chordwise Positions at the Wing Tip of a 45 Degrees Sweptback Wing and Body Combination

Comparisons of the Effectiveness and Hinge Moments of All-Movable Delta and Flap-Type Controls on Various Wings

Description and Investigation of a Dynamic Model of the XH-17 Two-Blade Jet Driven Helicopter

Considerations on a Large Hydraulic Jet Catapult

Correlation of Supersonic Convective Heat-Transfer Coefficients From Measurements of the Skin Temperature of a Parabolic Body of Revolution (NACA RM-10)

Buffeting-Load Measurements on a Jet-Powered Bomber Airplane With Reflexed Flaps

Aerodynamic Characteristics of Tapered Wings Having Aspect Ratios of 4, 6, and 8, Quarter-Chord Lines Swept Back 45 Degrees, and NACA 63(Sub 1)a012 Airfoil Sections: Transonic-Bump Method

Aerodynamic Characteristics of Four Wings of Sweepback Angles 0 Degrees, 35 Degrees, 45 Degrees, and 60 Degrees, NACA 65A006 Airfoil Section, Aspect Ratio 4, and Taper Ratio 0.6 in Combination With a Fuselage at High Subsonic Mach Numbers and at a Mach Number of 1.2

Aerodynamic Characteristics of Four Bodies of Revolution Showing Some Effects of Afterbody Shape and Fineness Ratio at Free-Stream Mach Numbers From 1.50 to 1.99

Average Skin-Friction Coefficients From Boundary-Layer Measurements in Flight on a Parabolic Body of Revolution (NACA RM-10) at Supersonic Speeds and at Large Reynolds Numbers

Interferometer With Large Working Field Utilizing Schlieren Optics

Low-Speed Investigation of Several Types of Split Flap on a 47.7 Degree Sweptback-Wing - Fuselage Combination of Aspect Ratio 5.1 at a Reynolds Number of 6.0 X 10(Exp 6)

Low-Speed Investigation of the Effects of Single Slotted and Double Slotted Flaps on a 47.7 Degree Sweptback-Wing: Fuselage Combination at a Reynolds Number of 6.0 X 10(Exp 6)

Investigation of the Effects of Twist and Camber on the Aerodynamic Characteristics of a 50 Degrees 38 Minutes Sweptback Wing of Aspect Ratio 2.98: Transonic-Bump Method

Investigation of Low-Speed Lateral Control and Hinge-Moment Characteristics of a 20-Percent-Chord Plain Aileron on a 47.7 Degrees Sweptback Wing of Aspect Ratio 5.1 at a Reynolds Number of 6.0 X 10(Exp 6)

Flight Investigation of the Effect of Sideslip on the Pressure at the Static Orifices of the Boeing B-29 Airplane

Flight Investigation of the Drag of Round-Nosed Bodies of Revolution at Mach Numbers From 0.6 to 1.5 Using Rocket-Propelled Test Vehicles

Instrumentation for Recording Transient Performance of Gas-Turbine Engines and Control Systems


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