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Test of NACA 66,2-116, a =0.6 airfoil section fitted with pressure balanced and slotted flaps for the wing of the XP-63 airplane

Wind tunnel investigation of control surface characteristics.12 - Various cover-plate alinements on the NACA 0015 airfoil with a 30 percent chord flap and large sealed internal balance

Performance of NACA eight-stage axial-flow compressor designed on the basis of airfoil theory

The NACA balanced-diaphragm dynamometer-torque indicator

Wind-tunnel tests of a blunt-nose aileron with beveled trailing edge on an NACA 66(215)-216 airfoil with several modification of aileron nose and adjacent airfoil contour

Investigations at supersonic speeds of 22 triangular wings representing two airfoil sections for each of 11 apex angles

Aerodynamic characteristics of several 6-percent-thick airfoils at angles of attack from 0 to 20 degrees at high subsonic speeds

Aerodynamic characteristics of a delta wing with leading edge swept back 45 degrees, aspect ratio 4, and NACA 65A006 airfoil section.Transonic-bump method

Investigation of the NACA-4-(3)(08)-03 two-blade propeller at forward Mach numbers to 0.925

Investigation of the NACA 4-(4)(06)-04 two-blade propeller at forward Mach numbers to 0.925

Aerodynamic characteristics of a wing with quarter-chord line swept back 45 degrees, aspect ratio 4, taper ratio 0.3, and NACA 65A006 airfoil section.Transonic-bump method

Tests of a small-scale NACA submerged inlet at transonic Mach numbers

An investigation of several NACA 1-series nose inlets with and without protruding central bodies at high-subsonic Mach numbers and at a Mach number of 1.2

Investigation of a simple device for preventing separation due to shock and boundary-layer interaction

Flight investigation at Mach numbers from 0.6 to 1.7 to determine drag and base pressures on a blunt-trailing-edge airfoil and drag of diamond and circular-arc airfoils at zero lift

Low-speed wind-tunnel investigation of a triangular sweptback air inlet in the root of a 45 degree sweptback wing

Lateral-control investigation of flap-type controls on a wing with quarter-chord line sweptback 35©�, aspect ratio 4, taper ratio 0.6, and NACA 65A006 airfoil section.Transonic-bump method

Aerodynamic investigation at Mach number 1.92 of a rectangular wing and tail and body configuration and Its components

Flight determination of the drag and pressure recovery of an NACA 1-40-250 nose inlet at Mach numbers from 0.9 to 1.8

Results of two free-fall experiments on flutter of thin unswept wings in the transonic speed range

An investigation at transonic speeds of the effects of thickness ratio and of thickened root sections on the aerodynamic characteristics of wings with 47©� sweepback, aspect ratio 3.5, and taper ratio 0.2 in the slotted test section of the Langley 8-foot high-speed tunnel

Aerodynamic characteristics of a leading-edge slat on a 35 degree swept-back wing for Mach numbers from 0.30 to 0.88

Miscellaneous directional-stability data for several airplane-like configurations from rocket-model tests at transonic speeds

Factors affecting transition at supersonic speeds

Fuel characteristics pertinent to the design of aircraft fuel systems.Supplement 1 - Additional information on MIL-F-7914(AER) Grade JP-5 fuel and several fuel oils

Supersonic flutter of a 60©� delta wing encountered during the flight test of a rocket-propelled model

Normal force, center of pressure, and zero-lift drag of several ballistic-type missiles at Mach numbers of 4.05

Some effects of external wing tip stores on the rolling effectiveness and drag of plain and half-delta tip ailerons on a 4-percent-thick tapered, unswept wing

Investigation of the aerodynamic characteristics at high supersonic Mach numbers of a family of delta wings having double-wedge sections with the maximum thickness at 0.18 chord

Effects of some external-store mounting arrangements and store shapes on the buffet and drag characteristics of wingless rocket-powered models at Mach numbers from 0.7 to 1.4

Effects of overhang balance on the hinge-moment and effectiveness characteristics of an unswept trailing-edge control on a 60 degree delta wing at transonic and supersonic speeds

Statistical survey of icing data measured on scheduled airline flights over the United States and Canada from November 1951 to June 1952

A survey of methods for turbojet thrust measurement applicable to flight installation

Combustion of aluminum borohydride in a supersonic wind tunnel

Vertical and drag ground-reaction forces developed in landing impacts of a large airplane

The rolling moment due to sideslip of swept wings at subsonic and transonic speeds

An experimental study of a method of designing the sweptback-wing - fuselage juncture for reducing the drag at transonic speeds

Aerodynamic-heating data obtained from free-flight tests between Mach numbers of 1 and 5

Effect of surface roughness on characteristics of spherical shock waves

Some observations on loss of static strength due to fatigue cracks

Preliminary investigation of the failure of pressurized stiffened cylinders

Preliminary investigation of the compressive strength and creep lifetime of 2024-T3 (formerly 24S-T3) aluminum-alloy plates at elevated temperatures

Tensile properties of some sheet materials under rapid-heating conditions

A study of the response of panels to random acoustic excitation

A free-flight investigation of the effects of simulated sonic turbojet exhaust on the drag of a boattail body with various jet sizes from Mach number 0.87 to 1.50

Free-flight measurements of aerodynamic heat transfer to Mach number 3.9 and of drag to Mach number 6.9 of a fin-stabilized cone-cylinder configuration

Initial experimental investigation of the aerodynamic load on the wing of a model caused by a blast-induced gust that increases the angle of attack into the stall region

Experimental aerodynamic forces and moments at low speed of a missile model during simulated launching from the midsemispan location of a 45 degree sweptback wing-fuselage combination

Theoretical analysis of the longitudinal behavior of an automatically controlled supersonic interceptor during the attack phase against maneuvering and nonmaneuvering targets

Transonic wind-tunnel investigation of the effects of sweepback and thickness ratio on the wing loads of a wing-body combination of aspect ratio 4 and taper ratio 0.6


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