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At least 343 records · Page 19

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NASA NTRS1973

Low-subsonic aerodynamic characteristics of a 60 deg swept delta wing space shuttle orbiter

An investigation was conducted in the Langley low-turbulence pressure tunnel to determine Reynolds number effects on the low-subsonic areodynamic characteristics and longitudinal control effectiveness of a North American Rockwell phase B delta-wing orbiter concept designated 134D. The model was tested over a range of Reynolds numbers, based on body length, from 5.25 million to 29.4 million, at Mach numbers less than 0.35, at angles of attack from approximately -2 to 28, and at angles of sideslip of 0 and -6.

Freeman, D. C., Jr.↗

NASA NTRS1991

An efficient DSMC algorithm applied to a delta wing

A new algorithm for 3D direct simulation Monte Carlo (DSMC) is tested and numerical results are compared with wind tunnel data and results obtained earlier with a more traditional DSMC code. The test case is the flowfield around a delta wing at incidence at Knudsen number of 0.016 and Mach number of 20.2. The results are shown to compare favorably with both experimental and earlier numerical results. The new algorithm is described with special emphasis placed on its distinctive features: Cartesian/unstructured combination grid, special body surface definition, discretization in physical space.

Rault, D. F. G.↗

NASA NTRS1956

Tabulated Pressure Data for a Series of Controls on a 60 Degree Delta Wing at Mach Numbers of 1.61 and 2.01

An investigation has been made at Mach numbers of 1.61 and 2.01 and Reynolds numbers from 1.7 X 10 to 7.6 X 10 to determine the pressure distributions over a 60 deg. delta wing having 20 different control configurations. Measurements were made at angles of attack from O deg to 15 deg for control deflections from -30 deg to 30 deg. This report presents the complete tabulated pressure data for the range of test conditions.

Lord, Douglas R↗

NASA NTRS1972

Space shuttle: Heat transfer rate distributions on McDonnell-Douglas delta wing orbiter determined by phase-change paint technique for nominal Mach number of 8

The results are reported of the phase-change paint tests conducted at Mach 8, to determine the aerodynamic heat transfer distributions on the McDonnell Douglas delta wing orbiter. Model details, test conditions, and reduced heat transfer data are presented.

Matthews, R. K.↗

NASA NTRS1991

Nonequilibrium turbulence modeling effects on transonic vortical flows about delta wings

The Johnson-King turbulence model that is a viable method for calculating two dimensional transonic separated flows was extended into three dimensions. The implementation was done for Navier Stokes flow solvers written in general curvilinear coordinates. The present approach used in turbulence modeling is based on streamwise integration of an ordinary differential equation (o.d.e.) that governs the maximum Reynolds shear stress behavior. Streamwise integration of the o.d.e. approach was found to offer great mathematical simplicity and economy for three dimensional Navier Stokes methods. Thus, the new method is quick, simple, and very cheap. The new method was first checked against the data of a well known transonic axisymmetric bump experiment, and a good agreement was obtained. Later, the new method was used to compute the flow around a low aspect ratio wing in a transonic wind tunnel. Finally it was employed to study the nonequilibrium turbulence effects on the transonic vortical flows about a 65 deg sweep round leading edge delta wing.

Unver Kaynak↗

NASA NTRS1991

Visualization of leading edge vortices on a series of flat plate delta wings

A summary of flow visualization data obtained as part of NASA Grant NAG2-258 is presented. During the course of this study, many still and high speed motion pictures were taken of the leading edge vortices on a series of flat plate delta wings at varying angles of attack. The purpose is to present a systematic collection of photographs showing the state of vortices as a function of the angle of attack for the four models tested.

Payne, Francis M.↗

NASA NTRS1990

Visualization of the flow about a delta wing maneuvering in pitch to very high angle of attack

An experimental program of unsteady aerodynamic measurements has been carried out in one of the 7 ft by 10 ft low-speed wind tunnels at NASA Ames Research Center. Flow-visualization measurements on a delta wing model of AR = 1.0 with sharp leading edges were carried out by means of a thin planar sheet of laser light fixed in the test section at a convenient angle to the flow direction. Smoke images of the fluid motion and vortex structure above the model were recorded photographically and later analyzed to determine such information as the positions of the cores and occurrence of bursting. Large amplitude transient motion involving post stall angle of attack excursions produced significant hysteresis in the vortex burst location and was reflected in the measured aerodynamic loads.

Jarrah, M. A. M.↗

NASA NTRS1952