Wind-tunnel force and flow visualization data at Mach numbers from 1.6 to 4.63 for a series of bodies of revolution at angles of attack from -4 ̊to 60 ̊/

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 experiments on divergence of forward-swept wings /

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

January 1980

Subject Category 05."August 1980"--Cover."Langley Research Center."Includes bibliographical referenc...

Dynamic and static wind-tunnel tests of a flow-direction vane /

Richardson, Norman R.
Langley Research Center.
United States. National Aeronautics and Space Administration.

January 1971

Prepared at Langley Research Center."April 1971."Cover title.Includes bibliographical references (p....

Pressure and force data for a flat wing and a warped conical wing having a shockless recompression at Mach 1.62 /

Miller, David S.
United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch.
Langley Research Center.

January 1981

"April 1981"--Cover."Langley Research Center."Includes bibliographical references.Mode of access: In...

Wind-tunnel force and flow visualization data at Mach numbers from 1.6 to 4.63 for a series of bodies of revolution at angles of attack from minus 4 deg to 60 deg

Babb, C. D.
Landrum, E. J.

March 1979

Flow visualization and force data for a series of six bodies of revolution are presented without ana...

Computer analysis of flow pertubations generated by placement of choke bumps in a wind tunnel /

Campbell, Richard L. (Richard Lawson), 1952-
Langley Research Center.
United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch.

January 1981

"August 1981"--Cover."Langley Research Center."Includes bibliographical references.Mode of access: I...

Aerodynamic and flow-visualization studies of variations in the geometry of irregular planform wings at a Mach number of 20.3 /

Stone, David R. (David Ray)
Spencer, Bernard, 1932-
Langley Research Center.

January 1974

Prepared at Langley Research Center.Cover title.Includes bibliographical references (p. 10-11).Mode ...

Wind-tunnel results for a modified 17-percent-thick low-speed airfoil section /

McGhee, Robert J.
Beasley, William D.
United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch.
Langley Research Center.

January 1981

"November 1981"--Cover."Langley Research Center."Includes bibliographical references.Mode of access:...

Flow visualization studies of a general research fighter model employing a strake-wing concept at subsonic speeds /

Luckring, James M.
Langley Research Center.
United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch.

January 1979

Subject category 02."Langley Research Center.""August 1979"--Cover.Includes bibliographical referenc...

Flow visualization in a cryogenic wind tunnel using holography /

Burner, Alpheus W.
Goad, William K.
United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch.
Langley Research Center.

January 1982

"November 1982"--Cover.Subject category 35."Langley Research Center."Includes bibliographical refere...

Evaluation of wind-tunnel gust response technique correlations with analytical and flight test results /

Redd, L. Tracy.
Wynne, Eleanor C.
Hanson, Perry W.
United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch.
Langley Research Center.

January 1979

"November 1979"--Cover."Langley Research Center."Includes bibliographical references.Mode of access:...

Wind-tunnel investigation of static aerodynamic characteristics of a 1/9-scale model of a Project Mercury capsule at mach numbers from 1.60 to 4.65 /

Shaw, David S.
Turner, Kenneth L.
United States. National Aeronautics and Space Administration.

"July 1960."Cover title.Includes bibliographical references (p. 7).Mode of access: Internet

Exploratory investigation of the aerodynamic characteristics of a biwing vehicle at Mach 20.3 /

Bernot, Peter T.
Langley Research Center.

January 1985

Prepared at Langley Research Center."February 1985"--Cover.Includes bibliographical references (p. 4...

Wind-tunnel investigation at mach numbers from 0.50 to 1.14 of the static aerodynamic characteristics of a model of a Project Mercury capsule /

Pearson, Albin O.
United States. National Aeronautics and Space Administration.

"July 1960."Cover title.Includes bibliographical references (p. 6).Mode of access: Internet

Low-speed stability and control wind-tunnel investigation of effects of spanwise blowing on fighter flight characteristics at high angles of attack /

Satran, Dale R.
Anglin, Ernie L.
Gilbert, William P.
Langley Research Center.

January 1985

Prepared at Langley Research Center."May 1985"--Cover.Includes bibliographical references (p. 9-10)....

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 experiments on divergence of forward-swept wings /

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

January 1980

Subject Category 05."August 1980"--Cover."Langley Research Center."Includes bibliographical referenc...

Dynamic and static wind-tunnel tests of a flow-direction vane /

Richardson, Norman R.
Langley Research Center.
United States. National Aeronautics and Space Administration.

January 1971

Prepared at Langley Research Center."April 1971."Cover title.Includes bibliographical references (p....

Pressure and force data for a flat wing and a warped conical wing having a shockless recompression at Mach 1.62 /

Miller, David S.
United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch.
Langley Research Center.

January 1981

"April 1981"--Cover."Langley Research Center."Includes bibliographical references.Mode of access: In...

Wind-tunnel force and flow visualization data at Mach numbers from 1.6 to 4.63 for a series of bodies of revolution at angles of attack from minus 4 deg to 60 deg

Babb, C. D.
Landrum, E. J.

March 1979

Flow visualization and force data for a series of six bodies of revolution are presented without ana...

Computer analysis of flow pertubations generated by placement of choke bumps in a wind tunnel /

Campbell, Richard L. (Richard Lawson), 1952-
Langley Research Center.
United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch.

January 1981

"August 1981"--Cover."Langley Research Center."Includes bibliographical references.Mode of access: I...

Aerodynamic and flow-visualization studies of variations in the geometry of irregular planform wings at a Mach number of 20.3 /

Stone, David R. (David Ray)
Spencer, Bernard, 1932-
Langley Research Center.

January 1974

Prepared at Langley Research Center.Cover title.Includes bibliographical references (p. 10-11).Mode ...

Wind-tunnel results for a modified 17-percent-thick low-speed airfoil section /

McGhee, Robert J.
Beasley, William D.
United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch.
Langley Research Center.

January 1981

"November 1981"--Cover."Langley Research Center."Includes bibliographical references.Mode of access:...

Flow visualization studies of a general research fighter model employing a strake-wing concept at subsonic speeds /

Luckring, James M.
Langley Research Center.
United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch.

January 1979

Subject category 02."Langley Research Center.""August 1979"--Cover.Includes bibliographical referenc...

Flow visualization in a cryogenic wind tunnel using holography /

Burner, Alpheus W.
Goad, William K.
United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch.
Langley Research Center.

January 1982

"November 1982"--Cover.Subject category 35."Langley Research Center."Includes bibliographical refere...

Evaluation of wind-tunnel gust response technique correlations with analytical and flight test results /

Redd, L. Tracy.
Wynne, Eleanor C.
Hanson, Perry W.
United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch.
Langley Research Center.

January 1979

"November 1979"--Cover."Langley Research Center."Includes bibliographical references.Mode of access:...

Wind-tunnel investigation of static aerodynamic characteristics of a 1/9-scale model of a Project Mercury capsule at mach numbers from 1.60 to 4.65 /

Shaw, David S.
Turner, Kenneth L.
United States. National Aeronautics and Space Administration.

"July 1960."Cover title.Includes bibliographical references (p. 7).Mode of access: Internet

Exploratory investigation of the aerodynamic characteristics of a biwing vehicle at Mach 20.3 /

Bernot, Peter T.
Langley Research Center.

January 1985

Prepared at Langley Research Center."February 1985"--Cover.Includes bibliographical references (p. 4...

Wind-tunnel investigation at mach numbers from 0.50 to 1.14 of the static aerodynamic characteristics of a model of a Project Mercury capsule /

Pearson, Albin O.
United States. National Aeronautics and Space Administration.

"July 1960."Cover title.Includes bibliographical references (p. 6).Mode of access: Internet

Low-speed stability and control wind-tunnel investigation of effects of spanwise blowing on fighter flight characteristics at high angles of attack /

Satran, Dale R.
Anglin, Ernie L.
Gilbert, William P.
Langley Research Center.

January 1985

Prepared at Langley Research Center."May 1985"--Cover.Includes bibliographical references (p. 9-10)....

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 experiments on divergence of forward-swept wings /

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

January 1980

Subject Category 05."August 1980"--Cover."Langley Research Center."Includes bibliographical referenc...

Dynamic and static wind-tunnel tests of a flow-direction vane /

Richardson, Norman R.
Langley Research Center.
United States. National Aeronautics and Space Administration.

January 1971

Prepared at Langley Research Center."April 1971."Cover title.Includes bibliographical references (p....

Wind-tunnel force and flow visualization data at Mach numbers from 1.6 to 4.63 for a series of bodies of revolution at angles of attack from -4 ̊to 60 ̊/

Abstract

Extracted data

Wind-tunnel force and flow visualization data at Mach numbers from 1.6 to 4.63 for a series of bodies of revolution at angles of attack from -4 ̊to 60 ̊/

Abstract

Extracted data

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