Pressure distributions and aerodynamic characteristics of several spoiler controls on a 40 degree sweptback wing at a Mach number of 1.61 /

Effect of body-mounted lateral controls and speed brakes on the aerodynamic load distribution over a 45 degree swept wing at mach numbers from 0.80 to 0.98 /

West, F. E.
United States. National Aeronautics and Space Administration.

Cover title." November 1960."Aerodynamics, aircraft; Aircraft; Stability and control; Stresses and l...

Effects at Mach numbers of 1.61 and 2.01 of camber and twist on the aerodynamic characteristics of three swept wings having the same planform /

Landrum, Emma Jean.
Czarnecki, K. R.
United States. National Aeronautics and Space Administration.

Cover title."August 1961."Major NASA subject terms: Aerodynamics, aircraft; Stability and control.In...

Local pressure distribution on a blunt delta wing for angles of attack up to 35 degrees at Mach numbers of 3.4 and 4.7

Kussoy, Marvin.
United States. National Aeronautics and Space Administration.

Cover title."December 1962."Includes bibliographical references.Mode of access: Internet

Effects of spoiler-slot-deflector control on the aerodynamic characteristics at a mach number of 2.01 of a variable-wing-sweep configuration with the outer wing panels swept back 75° /

Foster, Gerald V.
United States. National Aeronautics and Space Administration.

"April 1960."Cover title.Includes bibliographical references (p. 5).Mode of access: Internet

Aerodynamic characteristics of a spoiler-slot-deflector control on a 45° sweptback-wing-fuselage model at high subsonic speeds /

Hammond, Alexander D.
United States. National Aeronautics and Space Administration.

"January 1960."Cover title.Includes bibliographical references (p. 10-11).Mode of access: Internet

Spanwise loadings and aerodynamic characteristics for a series of trailing-edge controls on a 40° sweptback wing at Mach numbers of 1.61 and 2.01/

Landrum, Emma Jean.
Czarnecki, K. R.
Langley Research Center.

January 1962

"November 1962."Cover title.Includes bibliographical references (p. 9).Mode of access: Internet

Effects of a lower surface jet on the lift-drag ratio of a 45° sweptback wing at a Mach number of 2.01 /

Landrum, Emma Jean.
Langley Research Center.

January 1960

"NASA TN D-183.""Langley Research Center, Langley Field, Va.""March 1960."Title from cover.Includes ...

Aerodynamic damping at Mach numbers of 1.3 and 1.6 of a control surface on a two-dimensional wing by the free-oscillation method /

Tuovila, W. J. (Weimer J.)
Hess, R. W. (Robert W.)
Langley Research Center.

January 1960

"NASA TN D-116.""Langley Research Center, Langley Field, Va.""February 1960."Title from cover.Includ...

Pressure distributions on blunt-delta wings at angles of attack up to 90 degrees and Mach number of 6.85 /

Bernot, Peter T.
United States. National Aeronautics and Space Administration.

Cover title."July 1963."Includes bibliographical references.Mode of access: Internet

Pressure distributions induced by elevon deflections on swept wings and adjacent end-plate surfaces at Mach 6 /

Kaufman, Louis G., II.
Johnson, Charles B.
Langley Research Center.
United States. National Aeronautics and Space Administration.

Prepared by Langley Research Center, Hampton, VA 23665.Includes bibliographical references (p. 13-1...

A transonic investigation of changing indentation design Mach number on the aerodynamic characteristics of a 45 degree sweptback-wing-body combination designed for high performance /

Loving, Donald L.
United States. National Aeronautics and Space Administration.

Cover title."October 1961."Major NASA subject terms:Aerodynamics, aircraft; Aircraft; Stability and ...

Pressure measurements on two 60° swept delta wings with blunt leading edges and dihedral angles of 0° and 45° at a Mach number of 4.95. Calvin Stainback.

Stainback, P. Calvin.
United States. National Aeronautics and Space Administration.

January 1962

Cover title."April 1962."Aerodynamics, aircraft; Aerodynamics, missiles; Fluid mechanics; Stresses a...

Investigation at transonic speeds to determine lateral control effectiveness of blowing laterally over surfaces of 30° and 45° swept wings /

Hammond, Alexander D.
McKinney, Linwood W.
Langley Research Center.

January 1959

"NASA TN D-42.""Langley Research Center, Langley Field, Va.""October 1959."Title from cover.Includes...

The effects of an inverse-taper leading-edge flap on the aerodynamic loading characteristics of a 45° sweptback wing at Mach numbers to 0.90 /

Demele, Fred A.
Ames Research Center.

January 1959

"NASA TN D-138.""Ames Research Center, Moffett Field, Calif.""December 1959."Title from cover.Includ...

A limited flight and wind-tunnel investigation of paddle spoilers as lateral controls /

Mungall, Robert G.
Alford, William L.
Johnson, Harold I.
Langley Research Center.

January 1959

"NASA TN D-32.""Langley Research Center, Langley Field, Va.""September 1959."Title from cover.Includ...

Effect of body-mounted lateral controls and speed brakes on the aerodynamic load distribution over a 45 degree swept wing at mach numbers from 0.80 to 0.98 /

West, F. E.
United States. National Aeronautics and Space Administration.

Cover title." November 1960."Aerodynamics, aircraft; Aircraft; Stability and control; Stresses and l...

Effects at Mach numbers of 1.61 and 2.01 of camber and twist on the aerodynamic characteristics of three swept wings having the same planform /

Landrum, Emma Jean.
Czarnecki, K. R.
United States. National Aeronautics and Space Administration.

Cover title."August 1961."Major NASA subject terms: Aerodynamics, aircraft; Stability and control.In...

Local pressure distribution on a blunt delta wing for angles of attack up to 35 degrees at Mach numbers of 3.4 and 4.7

Kussoy, Marvin.
United States. National Aeronautics and Space Administration.

Cover title."December 1962."Includes bibliographical references.Mode of access: Internet

Effects of spoiler-slot-deflector control on the aerodynamic characteristics at a mach number of 2.01 of a variable-wing-sweep configuration with the outer wing panels swept back 75° /

Foster, Gerald V.
United States. National Aeronautics and Space Administration.

"April 1960."Cover title.Includes bibliographical references (p. 5).Mode of access: Internet

Aerodynamic characteristics of a spoiler-slot-deflector control on a 45° sweptback-wing-fuselage model at high subsonic speeds /

Hammond, Alexander D.
United States. National Aeronautics and Space Administration.

"January 1960."Cover title.Includes bibliographical references (p. 10-11).Mode of access: Internet

Spanwise loadings and aerodynamic characteristics for a series of trailing-edge controls on a 40° sweptback wing at Mach numbers of 1.61 and 2.01/

Landrum, Emma Jean.
Czarnecki, K. R.
Langley Research Center.

January 1962

"November 1962."Cover title.Includes bibliographical references (p. 9).Mode of access: Internet

Effects of a lower surface jet on the lift-drag ratio of a 45° sweptback wing at a Mach number of 2.01 /

Landrum, Emma Jean.
Langley Research Center.

January 1960

"NASA TN D-183.""Langley Research Center, Langley Field, Va.""March 1960."Title from cover.Includes ...

Aerodynamic damping at Mach numbers of 1.3 and 1.6 of a control surface on a two-dimensional wing by the free-oscillation method /

Tuovila, W. J. (Weimer J.)
Hess, R. W. (Robert W.)
Langley Research Center.

January 1960

"NASA TN D-116.""Langley Research Center, Langley Field, Va.""February 1960."Title from cover.Includ...

Pressure distributions on blunt-delta wings at angles of attack up to 90 degrees and Mach number of 6.85 /

Bernot, Peter T.
United States. National Aeronautics and Space Administration.

Cover title."July 1963."Includes bibliographical references.Mode of access: Internet

Pressure distributions induced by elevon deflections on swept wings and adjacent end-plate surfaces at Mach 6 /

Kaufman, Louis G., II.
Johnson, Charles B.
Langley Research Center.
United States. National Aeronautics and Space Administration.

Prepared by Langley Research Center, Hampton, VA 23665.Includes bibliographical references (p. 13-1...

A transonic investigation of changing indentation design Mach number on the aerodynamic characteristics of a 45 degree sweptback-wing-body combination designed for high performance /

Loving, Donald L.
United States. National Aeronautics and Space Administration.

Cover title."October 1961."Major NASA subject terms:Aerodynamics, aircraft; Aircraft; Stability and ...

Pressure measurements on two 60° swept delta wings with blunt leading edges and dihedral angles of 0° and 45° at a Mach number of 4.95. Calvin Stainback.

Stainback, P. Calvin.
United States. National Aeronautics and Space Administration.

January 1962

Cover title."April 1962."Aerodynamics, aircraft; Aerodynamics, missiles; Fluid mechanics; Stresses a...

Investigation at transonic speeds to determine lateral control effectiveness of blowing laterally over surfaces of 30° and 45° swept wings /

Hammond, Alexander D.
McKinney, Linwood W.
Langley Research Center.

January 1959

"NASA TN D-42.""Langley Research Center, Langley Field, Va.""October 1959."Title from cover.Includes...

The effects of an inverse-taper leading-edge flap on the aerodynamic loading characteristics of a 45° sweptback wing at Mach numbers to 0.90 /

Demele, Fred A.
Ames Research Center.

January 1959

"NASA TN D-138.""Ames Research Center, Moffett Field, Calif.""December 1959."Title from cover.Includ...

A limited flight and wind-tunnel investigation of paddle spoilers as lateral controls /

Mungall, Robert G.
Alford, William L.
Johnson, Harold I.
Langley Research Center.

January 1959

"NASA TN D-32.""Langley Research Center, Langley Field, Va.""September 1959."Title from cover.Includ...

Effect of body-mounted lateral controls and speed brakes on the aerodynamic load distribution over a 45 degree swept wing at mach numbers from 0.80 to 0.98 /

West, F. E.
United States. National Aeronautics and Space Administration.

Cover title." November 1960."Aerodynamics, aircraft; Aircraft; Stability and control; Stresses and l...

Effects at Mach numbers of 1.61 and 2.01 of camber and twist on the aerodynamic characteristics of three swept wings having the same planform /

Landrum, Emma Jean.
Czarnecki, K. R.
United States. National Aeronautics and Space Administration.

Cover title."August 1961."Major NASA subject terms: Aerodynamics, aircraft; Stability and control.In...

Local pressure distribution on a blunt delta wing for angles of attack up to 35 degrees at Mach numbers of 3.4 and 4.7

Kussoy, Marvin.
United States. National Aeronautics and Space Administration.

Cover title."December 1962."Includes bibliographical references.Mode of access: Internet

Pressure distributions and aerodynamic characteristics of several spoiler controls on a 40 degree sweptback wing at a Mach number of 1.61 /

Abstract

Extracted data

Pressure distributions and aerodynamic characteristics of several spoiler controls on a 40 degree sweptback wing at a Mach number of 1.61 /

Abstract

Extracted data

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