TRAIL - Technical Report Archive and Image Library

Aerodynamic characteristics at high and low subsonic Mach numbers of four NACA 6-series airfoil sections at angles of attack from -2 to 31 degrees

An experimental investigation at subsonic and supersonic speeds of the torsional damping characteristics of a constant-chord control surface of an aspect ratio 2 triangular wing

Experimental investigation of a 0.4 hub-tip diameter ratio axial-flow compressor inlet stage at transonic inlet relative Mach numbers I : rotor design and over-all performance at tip speeds from 60 to 100 percent of design

Effects of rate of flap deflection on flap hinge moment and wing lift through the Mach number range from 0.32 to 0.87

Free-flight performance of a rocket-boosted, air-launched 16-inch-diameter ram-jet engine at Mach numbers up to 2.20

Free-flight tests of three 1/9-scale models of the wing-ram-jet configuration of the Grumman XSSM-N-6A (Rigel) missile to investigate the possibility of flutter : TED No. NACA DE 223

Free-flight-tunnel investigation of the low-speed stability and control characteristics of a canard airplane model

Free-flight longitudinal-stability investigation including some effects of wing elasticity from Mach numbers of 0.85 to 1.34 of a tailless missile configuration having a 45 degree sweptback wing of aspect ratio 5.5

Ignition delays of some nonaromatic fuels with low-freezing red fuming nitric acid in temperature range -40 to -105 degrees F

Internal performance characteristics of variable-throat plug- and vaned-type convergent-divergent nozzles

Effect of axially staged fuel introduction on performance of one-quarter sector of annular turbojet combustor

Comparison of pressure-loss characteristics of several tail-cone air-induction systems for air-cooled gas-turbine rotors

The effects of fences on the high-speed longitudinal stability of a swept-wing airplane

Comparison of the aerodynamic characteristics at transonic speeds of a plane wing and a cambered and twisted wing, both having 45 degrees of sweepback and an aspect ratio of 6

Comparison of theoretical and experimental zero-lift drag-rise characteristics of wing-body-tail combinations near the speed of sound

Effect of leading-edge chord-extensions on the aerodynamic characteristics of a 45 degree sweptback wing-fuselage combination at Mach numbers of 0.40 to 1.03

Effect of leading-edge chord-extensions on subsonic and transonic aerodynamic characteristics of three models having 45 degrees sweptback wings of aspect ratio 4

Effects of slot location and geometry on the flow in a square tunnel at transonic Mach numbers

Effects of slot size and geometry on the flow in rectangular tunnels at Mach numbers up to 1.4

Effects of leading-edge slats on the aerodynamic characteristics of a 45 degree sweepback wing-fuselage configuration at Mach numbers of 0.4 to 1.03

Internal performance of several types of jet-exit configurations for supersonic turbojet aircraft

A study of the effects of body shape on the vortex wakes of inclined bodies at a Mach number of 2

Acceleration of high-pressure-ratio single-spool turbojet engine as determined from component performance characteristics 1: effect of air bleed at compressor outlet

Comparison of the experimental and theoretical distribution of lift on a slender inclined body of revolution at M = 2

Experimental investigation of the effects of support interference on the pressure distribution of a body of revolution at a Mach number of 3.12 and Reynolds numbers from 2 x 10(exp 6) to 14 x 10(exp 6)

Effect of rotor- and stator-blade modifications on surge performance of an 11-stage axial-flow compressor 2: redesigned compressor for XJ-40-WE-6 engine

Effect of rotor-and stator-blade modifications on surge performance of an 11-stage axial-flow compressor 1: original production compressor of XJ40-WE-6 engine

Performance of a supersonic mixed-flow rotor with a swept leading edge and 0.52 inlet radius ratio

Performance of a swept leading edge rotor of the supersonic type with mixed flow

Investigation at supersonic speeds of an inlet employing conical flow separation from a probe ahead of a blunt body

Test of an aerodynamically heated multiweb wing structure (MW-1) in a free jet at Mach number 2

Method for estimating combustion efficiency at altitude flight conditions from combustor tests at low pressures

Spark ignition of flowing gases III : effect of turbulence promoter on energy required to ignite a propane-air mixture

Lift, drag, and pitching moment of low-aspect-ratio wings at subsonic and supersonic speeds

Investigation of translating-spike supersonic inlet as means of mass-flow control at Mach numbers of 1.5, 1.8, and 2.0

Utilization of external-compression diffusion principle in design of shock-in-rotor supersonic compressor blading

Thermal shock resistance and high-temperature strength of a molybdenum disilicide - aluminum oxide ceramic

Wind-Tunnel Investigation of a 1/15-Scale Model of the Republic MX-1554 Airplane at Mach Numbers of 1.45 and 1.90

Wind-tunnel investigation of a 45 degree sweptback wing having a symmetrical root and a highly cambered tip, including the effects of fences and lateral controls

Wind-tunnel investigation at transonic speeds of a spoiler-slot-deflector combination on an unswept NACA 65A006 wing

Wind-tunnel investigation at subsonic and supersonic speeds of a model of a tailless fighter airplane employing a low-aspect-ratio swept-back wing : effects of external fuel tanks and rocket packets on the drag characteristics

Wind-Tunnel Investigation of a Modified 1/20-Scale Model of the Convair MX-1554 Airplane at Mach Numbers of 1.41 and 2.01

Matched performance characteristics of a 16-stage axial-flow compressor and a 3-stage turbine

Lift, drag, and hinge moments at supersonic speeds of an all-movable triangular wing and body combination

Lift, drag and pitching moment of low-aspect-ratio wings at subsonic and supersonic speeds : comparison of three wings of aspect ratio 2 of rectangular, swept-back and triangular plan form, including effects of thickness distribution

Mechanical design analysis of several noncritical air-cooled turbine disks and a corrugated-insert air-cooled turbine rotor blade

Preliminary drag and heat-transfer data obtained from air-launched cone-cylinder test vehicle over Mach number range from 1.5 to 5.18

Magnesium-slurry combustion performance in 6.5-inch-diameter ram-jet engine mounted in connected-pipe facility

Performance of a turbojet engine with adjustable first-stage turbine stator and variable-area exhaust nozzle

Photographic investigation of combustion in a two-dimensional transparent rocket engine

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