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Search indexed NASA NTRS and DOE OSTI research on propulsion, heat transfer, battery materials and energy systems. Follow report and document links to the original sources.
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Origin & distribution of supersonic store interference/measurement of individual forces - swept-wing heavy bomber with large store figure
Origin of supersonic store interference from measurements of individual forces - swept-wing fighter-bomber with large & small stores
Static longitudinal and lateral aerodynamic characteristics of V/STOL aircraft with variable sweep wing
Aerodynamic center shifts of rigid wing-body combinations at increased Mach numbers
Wind tunnel tests to determine longitudinal aerodynamic characteristics of large scale semispan V/STOL tilt-wing configuration with single propeller
Longitudinal aerodynamic characteristics of large scale semispan V/STOL tilt-wing configuration having single propeller
Explore the source record for details and available documents.
Explore the source record for details and available documents.
Explore the source record for details and available documents.
Explore the source record for details and available documents.
Transonic wind tunnel study of control span and large wing-tip nacelles results on effectiveness of spoiler-slot-deflector controls on fighter aircraft
Aerodynamic characteristics of large semi-span V/STOL tilt-wing with single propeller tested for modes of propeller rotation
Aerodynamic pressure distribution on semispan tilting wing-propeller combination of V/STOL aircraft
Wind tunnel tests of delta wind and straight wing space shuttle orbiter models to determine static stability and control
A brief exploratory flight program was conducted at Ames Research Center to investigate the vortex wake hazard of a powered-lift STOL aircraft. The study was made by flying an instrumented Cessna 210 aircraft into the wake of the augmentor wing jet STOL research aircraft at separation distances from 1 to 4 n.mi. Characteristics of the wake were evaluated in terms of the magnitude of the upset of the probing aircraft. Results indicated that within 1 n.mi. separation the wake could cause rolling moments in excess of roll control power and yawing moments equivalent to rudder control power of the probe aircraft. Subjective evaluations by the pilots of the Cessna 210 aircraft, supported by response measurements, indicated that the upset caused by the wake of the STOL aircraft was comparable to that of a DC-9 in the landing configuration.
The results of a parametric wing design study using a modern laminar flow airfoil designed to exhibit desirable stall characteristics while maintaining high cruise performance are presented. It was found that little is sacrificed in cruise performance when satisfying the stall margin requirements if a taper ratio of 0.65 or greater is used.
The results of an integrated study of structures, aerodynamics, and controls using the STARS program on two advanced airplane configurations are presented. Results for the X-29A include finite element modeling, free vibration analyses, unsteady aerodynamic calculations, flutter/divergence analyses, and an aeroservoelastic controls analysis. Good correlation is shown between STARS results and various other verified results. The tasks performed on the Oblique Wing Research Aircraft include finite element modeling and free vibration analyses.
High-incidence vortical flow about a 65-deg sweep delta wing undergoing static roll and large-amplitude, high-rate-of-roll oscillations is simulated numerically using the time-dependent, three-dimensional, Reynolds-averaged, Navier-Stokes equations. Turbulent computations are presented for static roll angles up through 42 degrees. The effects of roll angle on the vortex aerodynamics are discussed, and the solution accuracy is evaluated by comparison with experimental data. The effects of grid refinement and zonal boundary condition treatment on solution accuracy are assessed at zero roll angle. Numerical simulation of a forced periodic roll motion is also presented.