Browse TRAIL Inventories

Correlation of forced-convection heat-transfer data for air flowing in smooth platinum tube with long-approach entrance at high surface and inlet-air temperatures

Correlation of laboratory smoke test with carbon deposition in turbojet combustors

Aerodynamic characteristics of NACA RM 10 missile in 8 by 6 foot supersonic wind tunnel at Mach numbers from 1.49 to 1.98. 3: analysis of force distribution at angle of attack (stabilizing fins removed)

Aerodynamic characteristics of NACA RM-10 missile in 8- by 6-foot supersonic wind tunnel at Mach numbers from 1.49 to 1.98 1: presentation and analysis of pressure measurements (stabilizing fins removed)

Interpretation of boundary-layer pressure-rake data in flow with a detached shock

Analytical investigation of turbines with adjustable stator blades and effect of these turbines on jet-engine performance

Analytical determination of local surface heat-transfer coefficients for cooled turbine blades from measured metal temperatures

Aerodynamic characteristics of a wing with unswept quarter-chord line, aspect ratio 2, taper ratio 0.78, and NACA 65A004 airfoil section : transonic-bump method

Combustion efficiencies in hydrocarbon-air systems at reduced pressures

Analytical Investigation of Propeller Efficiency at High Subsonic Flight Speeds near Mach Number Unity

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 - trailing-edge flaps deflected

Analytical investigation of flow and heat transfer in coolant passages of free-convection liquid-cooled turbines

Antiknock evaluation of hydrocarbons and ethers as aviation fuel components

Aerodynamic characteristics of a wing with quarter-chord line swept back 60 degrees, aspect ratio 2, taper ratio 0.6, and NACA 65A006 airfoil section : transonic bump method

Aerodynamic characteristics of a wing with unswept quarter-chord line, aspect ratio 4, taper ratio 0.6, and NACA 65A004 airfoil section : transonic-bump method

Aerodynamic characteristics of NACA RM-10 missile in 8- by 6-foot supersonic wind tunnel at Mach numbers from 1.49 to 1.98 2: presentation and analysis of force measurements

Aerodynamic characteristics with fixed and free transition of a modified delta wing in combination with fuselage at high subsonic speeds

Comparison of large scale flight measurements of zero lift drag at Mach numbers from 0.9 to 1.7 of two wing-body combinations having similar 60 degree triangular wings with NACA 65A003 sections

An investigation of three transonic fuselage air inlets at Mach numbers from 0.4 to 0.94 and at a Mach number of 1.19

Characteristics of perforated diffusers at free-stream Mach number 1.90

The effect of tip tanks on the rolling characteristics at high subsonic Mach numbers of a wing having an aspect ratio of 3 with quarter-chord line swept back 35 degrees

Effect of wing-tank location on the drag and trim of a swept-wing model as measured in flight at transonic speeds

Effects of leading-edge radius and maximum thickness-chord ratio on the variation with Mach number of the aerodynamic characteristics of several thin NACA airfoil sections

Effects of inlet icing on performance of axial-flow turbojet engine in natural icing conditions

Effect of ram-jet pressure pulsations on supersonic-diffuser performance

Evaluation of a ducted-fan power plant designed for high output and good cruise fuel economy

Effect of Mach number on over-all performance of single-stage axial-flow compressor designed for high pressure ratio

Effects of molding conditions on some physical properties of glass-fabric unsaturated-polyester laminates

Effects of sweep on the maximum-lift characteristics of four aspect-ratio-4 wings at transonic speeds

Experimental damping in pitch of 45 degree triangular wings

Experimental investigation of the effectiveness of various suction-slot arrangements as a means for increasing the maximum lift of the NACA 65(sub 3)-018 airfoil section

Experimental investigation of supersonic flow with detached shock waves for Mach numbers between 1.8 and 2.9

Internal film cooling experiments in 4-inch duct with gas temperatures to 2000 degrees F

Tabulated pressure coefficients and aerodynamic characteristics measured on the wing of the Bell X-1 airplane in pull-ups at Mach numbers from 0.53 to 0.99

Study of flow conditions and deflection angle at exit of two-dimensional cascade of turbine rotor blades at critical and supercritical pressure ratios

Study of compressor systems for a gas-generator engine

Summary report of results obtained during demonstration tests of the Northrop X-4 airplanes

An 8-foot axisymmetrical fixed nozzle for subsonic Mach numbers up to 0.99 and for a supersonic Mach number of 1.2

Preliminary Investigation of Reflections of Oblique Waves from a Porous Wall

Experimental Investigation of Air-Cooled Turbine Blades in Turbojet Engine: 1: Rotor Blades With 10 Tubes in Cooling-Air Passages

Wind-Tunnel Investigation of a 1/6-Scale Model of the Bumblebee XPM Missile at High Subsonic Speeds

Wind-Tunnel Investigation of a 0.6-Scale Model of Hughes MX-904 Tail Surface at Supersonic Speeds: Tail Attached to a Segment of the Foreshortened Body

Experimental Investigation of Air-Cooled Turbine Blades in Turbojet Engine 2: Rotor Blades With 15 Fins in Cooling-Air Passages

Effect of Nose Shape and Wing Thickness Ratio on the Drag at Zero Lift of a Missile Having Triangular Wings and Tails

Investigation of Power Requirements for Ice Prevention and Cyclical De-Icing of Inlet Guide Vanes with Internal Electric Heaters

Model Ditching Investigations of Three Airplanes Equipped With Hydro-Skis

Photomicrographic Investigation of Spontaneous Freezing Temperatures of Supercooled Water Droplets

The Spanwise Distribution of Lift for Minimum Induced Drag of Wings Having a Given Lift and a Given Bending Moment

Investigation of Aerodynamic and Icing Characteristics of Water-Inertia-Separation Inlets for Turbojet Engines

Improvements in Heat Transfer for Anti-Icing of Gas-Heated Airfoils with Internal Fins and Partitions


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