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

Aerodynamic characteristics of a supersonic fighter aircraft model at Mach 0.40 to 2.47 /

Capone, Francis J.
Arbiter, Dorothy.
Bare, E. Ann.
Langley Research Center.

January 1986

Prepared at Langley Research Center."April 1986"--Cover.Includes bibliographical references (p. 15-1...

Wind tunnel simulation of full scale vortices /

Rorke, James B.
Moffitt, Robert C.
Langley Research Center.
United Aircraft Corporation. Sikorsky Aircraft Division.

January 1973

"Prepared by Sikorsky Aircraft Division, United Aircraft Corporation ... for Langley Research Center...

Investigation of flow-field development for a series of sonic-boom wind-tunnel models /

Runyan, Harry L.
United States. National Aeronautics and Space Administration.
Langley Research Center.

January 1971

Prepared at Langley Research Center.N71-20156.Issued Mar. 1971.Mode of access: Internet

Influence of airfoil geometry on delta wing leading-edge vortices and vortex-induced aerodynamics at supersonic speeds /

Wood, Richard M.
Wesselmann, Gary F.
Byrd, James E.
Langley Research Center.

January 1992

Prepared at Langley Research Center.Includes bibliographical references (p. 6).Mode of access: Inter...

Study of lee-side flows over conically cambered delta wings at supersonic speeds /

Wood, Richard M.
Watson, Carolyn B.
Langley Research Center.

January 1987

Prepared at Langley Research Center.Bibliography: v. 1, p. 26.Mode of access: Internet

Theoretical and experimental flow fields for a supersonic cruise fighter forebody /

Yaros, Steven F.
Langley Research Center.

January 1985

Prepared at Langley Research Center."November 1984"--Cover.Includes bibliographical references (p. 7...

Low subsonic flight and force investigation of a supersonic transport model with a double-delta wing /

Freeman, Delma C.
Langley Research Center.
United States. National Aeronautics and Space Administration.

January 1968

Work performed at Langley Research Center.N68-18250.Includes bibliographical references (p. 17).Mode...

Investigation of a supersonic cruise fighter model flow field /

Reubush, David E.
Bare, E. Ann.
Langley Research Center.

January 1985

Prepared at Langley Research Center."November 1985"--Cover.Includes bibliographical references (p. 8...

Lee-side flow over delta wings at supersonic speeds /

Miller, David S.
Wood, Richard M.
Langley Research Center.

January 1985

Prepared at Langley Research Center."June 1985"--Cover.Includes bibliographical references (p. 150)....

Transonic flutter study of a 50.5 ̊cropped-delta wing with two rearward-mounted nacelles /

Sandford, M. C. (Maynard C.)
Abel, Irving.
Ruhlin, Charles L.
Langley Research Center.

January 1974

Prepared at Langley Research Center.Cover title.Includes bibliographical references (p. 13).Mode of ...

Wind tunnel investigation of vortex flows on F/A-18 configuration at subsonic through transonic speeds /

Erickson, Gary E.
Langley Research Center.

January 1991

Prepared at Langley Research Center.Includes bibliographical references (p. 20).Mode of access: Inte...

Dynamic response of a forward-swept-wing model at angles of attack up to 15 at a Mach number of 0.8 /

Doggett, Robert V.
Ricketts, Rodney H.
Langley Research Center.
United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch.

January 1980

Nov. 1980."Langley Research Center."Includes bibliographical references.Mode of access: Internet

Wind-tunnel investigation to determine the low-speed yawing stability derivatives of a twin-jet fighter model at high angles of attack /

Coe, Paul L.
Newsom, William A.
Langley Research Center.

January 1974

Prepared at Langley Research Center.Cover title.Includes bibliographical references (p. 8).Mode of a...

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

Yip, Long P.
Langley Research Center.

January 1987

Prepared at Langley Research Center."May 1987"--Cover.Includes bibliographical references (p. 7).Mod...

Exhaust-nozzle characteristics for a twin-jet variable-wing-sweep fighter airplane model at Mach numbers to 2.2 /

Reubush, David E.
Mercer, Charles E.
Langley Research Center.

January 1974

Prepared at Langley Research Center.Cover title.Includes bibliographical references (p. 15).Mode of ...

Aerodynamic characteristics of a supersonic fighter aircraft model at Mach 0.40 to 2.47 /

Capone, Francis J.
Arbiter, Dorothy.
Bare, E. Ann.
Langley Research Center.

January 1986

Prepared at Langley Research Center."April 1986"--Cover.Includes bibliographical references (p. 15-1...

Wind tunnel simulation of full scale vortices /

Rorke, James B.
Moffitt, Robert C.
Langley Research Center.
United Aircraft Corporation. Sikorsky Aircraft Division.

January 1973

"Prepared by Sikorsky Aircraft Division, United Aircraft Corporation ... for Langley Research Center...

Investigation of flow-field development for a series of sonic-boom wind-tunnel models /

Runyan, Harry L.
United States. National Aeronautics and Space Administration.
Langley Research Center.

January 1971

Prepared at Langley Research Center.N71-20156.Issued Mar. 1971.Mode of access: Internet

Influence of airfoil geometry on delta wing leading-edge vortices and vortex-induced aerodynamics at supersonic speeds /

Wood, Richard M.
Wesselmann, Gary F.
Byrd, James E.
Langley Research Center.

January 1992

Prepared at Langley Research Center.Includes bibliographical references (p. 6).Mode of access: Inter...

Study of lee-side flows over conically cambered delta wings at supersonic speeds /

Wood, Richard M.
Watson, Carolyn B.
Langley Research Center.

January 1987

Prepared at Langley Research Center.Bibliography: v. 1, p. 26.Mode of access: Internet

Theoretical and experimental flow fields for a supersonic cruise fighter forebody /

Yaros, Steven F.
Langley Research Center.

January 1985

Prepared at Langley Research Center."November 1984"--Cover.Includes bibliographical references (p. 7...

Low subsonic flight and force investigation of a supersonic transport model with a double-delta wing /

Freeman, Delma C.
Langley Research Center.
United States. National Aeronautics and Space Administration.

January 1968

Work performed at Langley Research Center.N68-18250.Includes bibliographical references (p. 17).Mode...

Investigation of a supersonic cruise fighter model flow field /

Reubush, David E.
Bare, E. Ann.
Langley Research Center.

January 1985

Prepared at Langley Research Center."November 1985"--Cover.Includes bibliographical references (p. 8...

Lee-side flow over delta wings at supersonic speeds /

Miller, David S.
Wood, Richard M.
Langley Research Center.

January 1985

Prepared at Langley Research Center."June 1985"--Cover.Includes bibliographical references (p. 150)....

Transonic flutter study of a 50.5 ̊cropped-delta wing with two rearward-mounted nacelles /

Sandford, M. C. (Maynard C.)
Abel, Irving.
Ruhlin, Charles L.
Langley Research Center.

January 1974

Prepared at Langley Research Center.Cover title.Includes bibliographical references (p. 13).Mode of ...

Wind tunnel investigation of vortex flows on F/A-18 configuration at subsonic through transonic speeds /

Erickson, Gary E.
Langley Research Center.

January 1991

Prepared at Langley Research Center.Includes bibliographical references (p. 20).Mode of access: Inte...

Dynamic response of a forward-swept-wing model at angles of attack up to 15 at a Mach number of 0.8 /

Doggett, Robert V.
Ricketts, Rodney H.
Langley Research Center.
United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch.

January 1980

Nov. 1980."Langley Research Center."Includes bibliographical references.Mode of access: Internet

Wind-tunnel investigation to determine the low-speed yawing stability derivatives of a twin-jet fighter model at high angles of attack /

Coe, Paul L.
Newsom, William A.
Langley Research Center.

January 1974

Prepared at Langley Research Center.Cover title.Includes bibliographical references (p. 8).Mode of a...

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

Yip, Long P.
Langley Research Center.

January 1987

Prepared at Langley Research Center."May 1987"--Cover.Includes bibliographical references (p. 7).Mod...

Exhaust-nozzle characteristics for a twin-jet variable-wing-sweep fighter airplane model at Mach numbers to 2.2 /

Reubush, David E.
Mercer, Charles E.
Langley Research Center.

January 1974

Prepared at Langley Research Center.Cover title.Includes bibliographical references (p. 15).Mode of ...

Aerodynamic characteristics of a supersonic fighter aircraft model at Mach 0.40 to 2.47 /

Capone, Francis J.
Arbiter, Dorothy.
Bare, E. Ann.
Langley Research Center.

January 1986

Prepared at Langley Research Center."April 1986"--Cover.Includes bibliographical references (p. 15-1...

Wind tunnel simulation of full scale vortices /

Rorke, James B.
Moffitt, Robert C.
Langley Research Center.
United Aircraft Corporation. Sikorsky Aircraft Division.

January 1973

"Prepared by Sikorsky Aircraft Division, United Aircraft Corporation ... for Langley Research Center...

Investigation of flow-field development for a series of sonic-boom wind-tunnel models /

Runyan, Harry L.
United States. National Aeronautics and Space Administration.
Langley Research Center.

January 1971

Prepared at Langley Research Center.N71-20156.Issued Mar. 1971.Mode of access: Internet

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

Abstract

Extracted data

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

Abstract

Extracted data

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