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Lateral-control investigation of flap-type controls on a wing with upswept quarter-chord line, aspect ratio 4, taper ratio 0.6, and NACA 65A006 airfoil section : transonic-bump method

Lateral-control investigation of flap-type controls on a wing with quarter-chord line swept back 60 degrees, aspect ratio 4, taper ratio 0.6, and NACA 65A006 airfoil section : transonic bump method

Longitudinal-stability characteristics of the Northrop X-4 airplane (USAF No. 46-677)

Low-speed investigation of leading-edge and trailing-edge flaps on a 47.5 degree sweptback wing of aspect ratio 3.4 at a Reynolds number of 4.4 x 10(exp 6)

Measurement of uniform flame movement in carbon monoxide - air mixtures containing either added D2O or H2O

Measurements of the drag and pressure distribution on a body of revolution throughout transition from subsonic to supersonic speeds

Temperature survey of the wake of two closely located parallel jets

Free-spinning tunnel tests of a 1/20-scale model of the McDonnell XF3H-1 airplane : TED No. NACA DE 343

Free-jet investigation of a 16-inch ram jet at Mach numbers of 1.35, 1.50, and 1.73

Free-jet performance of 16-inch ram-jet engine with several fuels

Heat-transfer and operating characteristics of aluminum forced-convection and stainless-steel natural-convection water-cooled single-stage turbines

Note on some observed effects of rocket motor operation on the base pressures of bodies in free light

Free-flight performance of 16-inch-diameter supersonic ram-jet units 2: five units designed for combustion-chamber-inlet Mach number of 0.16 at free-stream Mach number of 1.60 (units B-1, B-2, B-3, B-4, and B-5)

Flight measurements with the Douglas D-558-II (BuAero No. 37974) research airplane : determination of the aerodynamic center and zero-lift pitching-moment coefficient of the wing-fuselage combination by means of tail-load measurements in the Mach num

Effect of fuel volatility on altitude starting limits of a turbojet engine

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


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