Search
Search U.S. government technical reports digitized or harvested by TRAIL.
Keyword Search
7169 results returnedSearch results
- Theoretical lift due to wing incidence of slender wing-body-tail combinations at zero angle of attack
- Visualization of rotor tip secondary flows with blade tip air discharge and suction in a low-speed turbine
- Wind-tunnel investigation of two vertical-takeoff-and-landing jet bomber airplane configurations at Mach numbers of 1.94 and 2.40
- Wind-tunnel investigation to determine the horizontal- and vertical-tail contributions to the static lateral stability characteristics of a complete-model swept-wing configuration at high subsonic speeds
- Experimental investigation at high subsonic speed of the rolling stability derivatives of a complete model having a clipped-delta wing and a high horizontal tail
- An experimental investigation at Mach numbers from 2.1 to 3.0 of circular-internal-contraction inlets with translating centerbodies
- Flight investigation of the stability and control characteristics of vertically rising airplane research model with swept or unswept wings and x- or +-tails
- Experimental investigation of a high subsonic Mach number turbine having high rotor blade suction-surface diffusion
- Experimental investigation of air-flow uniformity and pressure level on wire cloth for transpiration-cooling applications
- Experimental investigation of air-side performance of liquid-metal to air heat exhangers
- Experimental investigation of a high subsonic Mach number turbine having low rotor suction-surface diffusion
- Experimental investigation of a transonic compressor rotor with a 1.5-inch chord length and an aspect ratio of 3.0 III : blade-element and over-all performance at three solidity levels
- Free-flight tests of 1/10-scale Republic F-105 airplane wings in the subsonic to low supersonic speed range to investigate the possibility of flutter : COORD. No. AF-224
- Flight measurements of horizontal-tail loads on the Douglas X-3 research airplane
- Static strength of aluminum-alloy specimens containing fatigue cracks
- An evaluation of four experimental methods for measuring mean properties of a supersonic turbulent boundary layer
- Effect of several design variables on internal performance of convergent-plug exhaust nozzles
- An investigation of the lift, drag, and static-stability characteristics of a triangular-wing airplane configuration at Mach numbers from 3.00 to 6.28
- An investigation of the loads on the vertical tail of a jet-bomber airplane resulting from flight through rough air
- Investigation of boundary-layer transition on 10 degree cone in langley 4- by 4-foot supersonic pressure tunnel at Mach numbers of 1.41, 1.61, and 2.01
- Coking of JP-4 fuels in electrically heated metal tubes
- Effects of compressor interstage bleed and adjustable inlet guide vanes on compressor stall characteristics of a high-pressure-ratio turbojet engine at altitude
- Effects of external stores on the static longitudinal aerodynamic characteristics of a model of a 45 degree swept-wing fighter airplane at Mach numbers of 1.61 and 2.01
- The effect of leading-edge extensions on the longitudinal characteristics at Mach numbers up to 0.92 of a wing-fuselage-tail combination having a 40 degree sweptback wing with NACA 64A thickness distribution
- Effect of large negative dihedral of the horizontal tail on longitudinal and lateral stability characteristics of a swept-wing configuration at transonic speeds
- Effect of leading-edge droop on the aerodynamic and loading characteristics of a 4-percent-thick unswept-wing-fuselage combination at transonic speeds
- Application of Tchebichef form of harmonic analysis to the calculation of zero-lift wave drag of wing-body-tail combinations
- Application of area suction to leading-edge and trailing-edge flaps on a 44 degree swept-wing model
- Spreading characteristics of a jet expanding from choked nozzles at Mach 1.91
- Static longitudinal and lateral stability characteristics at low speed of unswept-midwing models having wings with an aspect ratio of 2, 4, or 6
- Full-scale wind-tunnel tests of a 35 degree swept-wing fighter airplane with a spoiler-slot-deflector lateral control system
- Comparison of experimental and theoretical normal-force distributions (including Reynolds number effects) on an ogive-cylinder body at Mach number 1.98
- Comparison of the experimental and theoretical distributions of lift on a slender inclined body of revolution at M = 2
- Wind-tunnel investigation of an external-flow jet-augmented slotted flap suitable for application to airplanes with pod-mounted jet engines
- A study of a missile designed to fly at low speed with its longitudinal axis aligned with the flight path
- Review of experimental investigations of liquid-metal heat transfer
- A reevaluaion of data on atmospheric turbulence and airplane gust loads for application in spectral calculations
- A relation between burning velocity and quenching distance
- Analysis of cooling-air requirements of corrugated-insert-type turbine blades suitable for a supersonic turbojet engine
- Wind-tunnel investigation at low speeds to determine the effect of aspect ratio and end plates on a rectangular wing with jet flaps deflected 85 degrees
- Wear of typical carbon-base sliding seal materials at temperatures to 700 F
- Weight-flow and thrust limitations due to use of rotating combustors in a turbojet engine
- Calculation of the forces and moments on a slender fuselage and vertical fin penetrating lateral gusts
- Calculation and compilation of the unsteady-lift functions for a rigid wing subjected to sinusoidal gusts and to sinusoidal sinking oscillations
- Temperatures in a J47-25 turbojet-engine turbine section during steady-state and transient operation in an altitude test stand
- Comparison between experimental and predicted downwash at a Mach number of 0.25 behind a wing-body combination having a triangular wing of aspect ratio of 2.0
- Thermal stability of pentaborane in the range 329 to 419 F
- A factor affecting transonic leading-edge flow separation
- On slender-body theory and the area rule at transonic speeds
- The effects upon body drag of jets exhausting from wing-mounted nacelles