Browse TRAIL Inventories

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

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

An Investigation of the Hydrodynamic Characteristics of a Jet-Powered Dynamic Model of the DR 56 Flying Boat: TED No. NACA DE 328

An Investigation of Flow Characteristics at Mach Number 4.04 Over 6- and 9-Percent-Thick Symmetrical Circular-Arc Airfoils Having 30-Percent-Chord Trailing-Edge Flaps

Lateral Control Characteristics and Dihedral Effect of a Wing-Body Combination With a Variable Incidence Triangular Wing and Wing-Tip Ailerons at a Mach Number of 1.52

An Analytic Determination of the Flow Behind a Symmetrical Curved Shock in a Uniform Stream

Free-Flight Investigation of the Longitudinal Stability and Control of a Rocket-Propelled Missile Model Having Cruciform, Triangular, Interdigitated Wings and Tails

Horizontal-Tail Effectiveness and Downwash Surveys for Two 47.7 Degree Sweptback Wing-Fuselage Combinations With Aspect Ratios of 5.1 and 6.0 at a Reynolds Number of 6.0 X 10(Exp 6)

Flight Measurements With the Douglas D-558-II (BuAero No. 37974) Research Airplane: Measurements of the Distribution of the Aerodynamic Load Among the Wing, Fuselage, and Horizontal Tail at Mach Numbers Up to 0.87

Flight Measurements With the Douglas D-558-II (BuAero No. 37974) Research Airplane: Static Longitudinal Stability and Control Characteristics at Mach Numbers Up to 0.87

Flight Measurements With the Douglas D-558-II (BuAero No. 37974) Research Airplane: Dynamic Lateral Stability

Investigation at Supersonic Speeds of Some of the Factors Affecting the Flow Over a Rectangular Wing With Symmetrical Circular-Arc Section and 30-Percent-Chord Trailing-Edge Flap

An Investigation of a Supersonic Aircraft Configuration Having a Tapered Wing With Circular-Arc Sections and 40 Degree Sweepback: Force Characteristics of the Complete Configuration and Its Various Components at Mach Numbers of 1.40 and 1.59

Experimental investigation of tail-pipe-burner design variables

Investigations on Wings With and Without Sweepback at High Subsonic Speeds

On the Turbulent Friction Layer for Rising Pressure

On the recording of turbulent longitudinal and transverse fluctuations

Flight-Determination of the Low-Lift Drag and Longitudinal Stability of a 1/10-Scale Rocket-Powered Model of the Douglas XF4D-1 Airplane at Mach Numbers from 0.7

Preliminary Transient Performance Data for Afterburner Operation of Westinghouse Electronic Power Regulator on XJ34-WE-32 Turbojet Engine in Altitude Wind Tunnel

On Ionization and Luminescence in Flames

Deplacement Effect of the Laminar Boundary Layer and the Pressure Drag

Supplementary Ditching Investigation of a 1/18-Scale Model of the North American B-45 Airplane

A Thermodynamic Study of the Turbine-Propeller Engine

Yawed-Landing Investigation of a Model of the Convair Y2-2 Airplane, TED No. NACA DE 363

On Motion of Fluid in Boundary Layer Near Line of Intersection of Two Planes

Preliminary Results of a Flight Investigation of 1/6-Scale Rocket-Powered Models of the Bell MX-776 to Determine Aileron Rolling Effectiveness and Total Drag

Investigation of Turbulent Flow in a Two-Dimensional Channel

The Design of Variable Mach Number Asymmetric Super-Sonic Nozzles by Two Procedures Employing Inclined and Curved Sonic Lines

Effect of Angle of Incidence of Second-Stage Vane Assembly on Third-Stage Compressor-Blade Vibration and Engine Performance

Annual Report of the National Advisory Committee for Aeronautics (38th). Administrative Report Including Technical Report Nos. 1059 to 1110

Annual Report of the National Advisory Committee for Aeronautics (36th). Administrative Report Including Technical Report Nos. 951 to 1002

Annual Report of the National Advisory Committee for Aeronautics (34th). Administrative Report Including Technical Report Nos. 892 to 921

Annual Report of the National Advisory Committee for Aeronautics (35th). Administrative Report Including Technical Report Nos. 922 to 950

Ditching Investigation of a 1/14-Scale Model of the XC-123 Airplane

Factors Affecting the Starting Characteristics of Gas-Turbine Engines

NACA Conference on Aircraft Structures

Coolant-Flow Calibrations of Three Simulated Porous Gas-Turbine Blades


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