Longitudinal aerodynamic characteristics at a mach number of 1.97 of a series of related winged reentry configurations for angles of attack from 0 deg to 90 deg
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Foster, G. V.↗
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Results for “Angle of attack”
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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Study program of local angle-of-attack effects on vehicle dynamic response Final report
Effects of flexible body aerodynamics on launch vehicles
Bradley, D.↗
Experimental stagnation point velocity gradients and heat transfer coefficients for a family of blunt bodies at Mach 8 and angles of attack
Stagnation pressure and heat transfer measurements of blunt axisymmetric bodies
Ellison, J. C.↗
Heat transfer to the windward side of a fineness-ratio-2.9 cylinder with nearly spherical ends at a Mach number of 6 and angles of attack of 50 deg, 70 deg, and 90 deg
Heat transfer to windward side of scale model for graphite lunar module fuel cylinder
Hunt, J. L.↗
Pressures and heat transfer on a 75 degree swept delta wing with trailing-edge flap at Mach 6 and angles of attack to 90 degrees
Pressure and heat transfer on swept delta wing with trailing-edge flap
Keyes, J. W.↗
Interpretation of wind-tunnel data in terms of dynamic behaviour of aircraft at high angles of attack
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Stone, R. W., Jr.↗
An approximate solution of additive-drag coefficient and mass-flow ratio for inlets utilizing right circular cones at zero angle of attack
Incompressible approximation solution of additive drag coefficient and mass flow ratio for inlets with right circular cones
Mascitti, V. R.↗
Application of the method of characteristics to noncircular bodies at angle of attack
Method of characteristics for flow field analysis on elliptical winged body
Rakich, J. V.↗
Low-subsonic aerodynamic characteristics of a model of a fixed-wing space shuttle concept at angles of attack to 76 deg
Low subsonic aerodynamic characteristics of fixed wing space shuttle model
Decker, J. P.↗
The compressible laminar boundary layer with heat transfer on a yawed cone at small angle of attack
Perturbation method for calculating velocity, temperature profiles, skin friction, and heat transfer coefficients in compressible laminar boundary of supersonic stream
Bodonyi, R. J.↗
A computer program for calculating inviscid, adiabatic flow about blunt bodies traveling at supersonic and hypersonic speeds at angle of attack
Computer program for determining inviscid flow around blunt bodies at supersonic and hypersonic speeds - users manual
Barnwell, R. W.↗
A method for calculating the aerodynamic loading on wing-body combinations at small angles of attack in supersonic flow
Theoretical method for calculating aerodynamic loading on wing-body combinations
Jackson, C. M., Jr.↗
Research on blunt faced entry configuration at angles of attack between 60 and 90 degrees
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Phillips, W. H.↗
Results of a study of Mach number and Reynolds number effects on the lee side vortex flow field characteristics of an ogive-cylinder-frustum-cylinder at angles of attack to 25 degrees. Volume 2: Appendix
A listing of the data reduction computer program output for the analysis of the lee side vortex flow about an ogive-cylinder-frustum-cylinder is presented. A computed local flow property for the flow field location array at a specific body station and freestream condition is listed. Significant local flow properties are computed. The local circulation strengths in the radial and circumferential directions are analyzed.
Foley, J. E.↗
The use of a finite difference technique to predict cascade, stator, and rotor deviation angles and optimum angles of attack.
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Dodge, P. R.↗
Viscous flow over spinning cones at angle of attack.
A numerical finite-difference method is developed for evaluating the Magnus coefficients on spinning cones in laminar flow. The merged layer, the strong interaction region, and the downstream boundary layer are all considered. The numerical method is a predictor-corrector scheme developed for three-dimensional flows with or without crossflow diffusion. This method is particularly useful in problems in which a symmetry plane does not exist. Several contributions to the Magnus force and moments are considered. These include asymmetries in displacement thickness, centrifugal force and crossflow shear, and the effects of crossflow separation and vortex formation. Comparisons are made with experimental data and other analyses.
Lin, T. C.↗
A study of numerical methods for predicting flow about bodies at angle of attack
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Gallo, W. F.↗