Search Results

1

Calculation of symmetric and asymmetric vortex separation on cones and tangent ogives based on discrete vortex models /

by Chin, S.
Washington, D.C. : National Aeronautics and Space Administration, Scientific and Technical Information Division, 1988

Government Document Book

2

Validation tests of TASS for application to 3-D vortex simulations /

by Switzer, George F.
Hampton, Va. : Springfield, VA : National Aeronautics and Space Administration, Langley Research Center ; Available from the National Technical Information Service, 1996

Book

3

Vortex flow aerodynamics : proceedings of a conference /

Washington, D.C. : National Aeronautics and Space Administration, Scientific and Technical Information Branch, 1986

Book

4

Wake geometry effects on rotor blade-vortex interaction noise directivity /

Washington, D.C. : Springfield, Va. : National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Division ; For sale by the National Technical Information Service, 1990

Government Document Book

5

A Study of scattering, production, and stimulated emission of sound by vortex flows /

by Yates, John E.
Washington, D.C. : [Springfield, Va.] : National Aeronautics and Space Administration, Scientific and Technical Information Office ; [For sale by the National Technical Information Service], 1979

Government Document Book

6

An experimental investigation of vortex stability, tip shapes, compressibility, and noise for hovering model rotors /

by Tangler, James L.
Washington, D.C. : [Springfield, Va.] : National Aeronautics and Space Administration ; [For sale by the National Technical Information Service], 1973

Government Document Book

7

Wind tunnel simulation of full scale vortices /

by Rorke, James B.
Washington, D.C. : [Springfield, Va.] : National Aeronautics and Space Administration ; [For sale by the National Technical Information Service], 1973

Government Document Book

8

An experimental study of rotor blade-vortex interaction /

by Surendraiah, Makam
Washington, D.C. : National Aeronautics and Space Administration, 1970

Government Document Book

9

Vortex equations : singularities, numerical solution, and axisymmetric vortex breakdown /

by Bossel, Hartmut H. (Helmut Hans)
Washington, D.C. : [Springfield, Va.] : National Aeronautics and Space Administration ; [For sale by the National Technical Information Service], 1972

Government Document Book

10

The lateral-directional characteristics of a 74-degree delta wing employing gothic planform vortex flaps /

by Grantz, Arthur C.
Washington, D.C. : Springfield, Va. : National Aeronautics and Space Administration, Scientific and Technical Information Branch ; For sale by the National Technical Information Service, 1984

Government Document Book

11

Experimental investigation of the subwing tip and its vortex structure /

by Tangler, James L.
[Washington] : Springfield, Va. : National Aeronautics and Space Administration, Scientific and Technical Information Office ; For sale by the National Technical Information Service, 1978

Government Document Book

12

Flow field over the wing of a delta-wing fighter model with vortex control devices at Mach 0.6 to 1.2 /

by Bare, E. Ann
Washington, D.C. : National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program, 1992

Government Document Book

13

Theoretical and experimental longitudinal aerodynamic characteristics of an aspect ratio 0.25 sharp-edge delta wing at subsonic, supersonic, and hypersonic speeds /

by Fox, Charles H.
Washington, D.C. : [Springfield, Va.] : National Aeronautics and Space Administration ; [For sale by the National Technical Information Service], 1974

Government Document Book

14

Wind-tunnel free-flight investigation of a 0.15-scale model of the F-106B airplane with vortex flaps /

by Yip, Long P.
Washington, D.C. : Springfield, Va. : National Aeronautics and Space Administration, Scientific and Technical Information Office ; For sale by the National Technical Information Service, 1987

Government Document Book

15

Prediction of subsonic vortex shedding from forebodies with chines /

by Mendenhall, M. R.
Washington, D.C. : Springfield, Va. : National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Division ; For sale by the National Technical Information Service, 1990

Government Document Book

16

Design and preliminary tests of a blade tip air mass injection system for vortex modification and possible noise reduction on a full-scale helicopter rotor /

Washington, D.C. : [Springfield, Va.] : National Aeronautics and Space Administration ; [For sale by the National Technical Information Service], 1975

Government Document Book

17

Surface-pressure and flow-visualization data at Mach number of 1.60 for three 65° delta wings varying in leading-edge radius and camber /

Hampton, Va. : Springfield, VA : National Aeronautics and Space Administration, Langley Research Center ; For sale by the National Technical Information Service, 1996

Book

18

A Three-dimensional viscous flow analysis for the helicopter tip vortex generation problem /

Washington, D.C. : Springfield, Va. : National Aeronautics and Space Administration, Scientific and Technical Information Branch ; For sale by the National Technical Information Service, 1985

Government Document Book

19

Effects of wing leading-edge radius and Reynolds number on longitudinal aerodynamic characteristics of highly swept wing-body configurations at subsonic speeds /

by Henderson, William P.
Washington : Springfield, Va. : National Aeronautics and Space Administration ; For sale by the National Technical Information Service, 1976

Government Document Book

20

Wind tunnel investigation of the interaction and breakdown characteristics of slender-wing vortices at subsonic, transonic, and supersonic speeds /

by Erickson, Gary E.
Washington, D.C. : National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program, 1991

Government Document Book

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