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 /

Investigation of leading-edge flap performance on delta and double-delta wings at supersonic speeds /

Covell, Peter F.
Miller, David S.
Wood, Richard M.
Langley Research Center.

January 1987

Prepared at Langley Research Center."April 1987"--Cover.Includes bibliographical references (p. 6-7)...

Low-speed wind-tunnel investigation of blowing boundary-layer control on leading- and trailing-edge flaps of a full-scale, low-aspect-ratio, 42° swept-wing airplane configuration /

Maki, Ralph L.
Giulianetti, Demo J.
Ames Research Center.

January 1959

"NASA TN D-16.""Ames Research Center, Moffett Field, Calif.""August 1959."Cover title.Includes bibli...

Aerodynamic load measurements and opening characteristics of automatic leading-edge slats on a 45 degree sweptback wing at transonic speeds /

Arabian, Donald D.
Reid, Charles F.
Runckel, Jack F.
United States. National Aeronautics and Space Administration.

Cover title."September 1961."Aircraft; Stresses and loads.Includes bibliographical references.Mode o...

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 ...

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

Wind-tunnel investigation of the effects of steady rolling on the aerodynamic loading characteristics of a 45©� sweptback wing at high subsonic speeds /

Wiggins, James W.
Kuhn, Richard E.
Langley Aeronautical Laboratory.
United States. National Adviosry Committee for Aeronautics. NACA research memorandum.
United States. National Advisory Committee for Aeronautics.

January 1954

"November 6, 1953."Cover title.Includes bibliographical references (p. 6).Mode of access: Internet

Full-scale wind-tunnel tests of a low-aspect-ratio, straight-wing airplane with blowing boundary-layer control on leading- and trailing-edge flaps /

Kelly, Mark W.
Maki, Ralph L.
Tolhurst, William H.
Ames Research Center.

January 1959

"NASA TN D-135.""Ames Research Center, Moffett Field, Calif.""September 1959."Title from cover.Inclu...

Investigation of the effects of leading-edge chord-extensions and fences in combination with leading-edge flaps on the aerodynamic characteristics at Mach numbers of 0.40 to 0.93 of a 45©� sweptback wing of aspect ratio 4 /

Spreemann, Kenneth P.
Alford, William J.
Langley Aeronautical Laboratory.
United States. National Advisory Committee for Aeronautics.

January 1957

"April 1957."Includes bibliographical references (p. 13).Mode of access: Internet

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...

An investigation of the effects of a geometric twist on the aerodynamic loading characteristics of a 45©� sweptback wing-body configuration at transonic speeds /

Williams, Claude V.
Langley Aeronautical Laboratory.
United States. National Adviosry Committee for Aeronautics. NACA research memorandum.
United States. National Advisory Committee for Aeronautics.

January 1954

"Declassified September 17, 1958.""October 12, 1954."Cover title.Includes bibliographical references...

An analysis of incremental horizontal-tail loads measured on a swept-wing bomber airplane in sideslip maneuvers /

McGowan, William A.
Langley Research Center.

January 1959

"NASA TN D-100.""Langley Research Center, Langley Field, Va.""October 1959."Title from cover.Include...

Effects of wing incidence on the longitudinal trim characteristics of a cambered 70° delta-wing configuration at mach numbers 3.0 to 5.0 /

Ahtye, Warren F.
Ames Research Center.

January 1960

"September 1960."Cover title.Includes bibliographical references (p. 23).Mode of access: Internet

Surface pressure distributions on a large-scale 49©� sweptback wing-body-tail configuration with blowing applied over the flaps and wing leading edge /

McLemore, H. Clyde.
Fink, Marvin P.
Langley Aeronautical Laboratory.
United States. National Adviosry Committee for Aeronautics. NACA research memorandum.

"February 17, 1958."Cover title.Includes bibliographical references (p. 16).Mode of access: Internet

Aerodynamic loading characteristics in sideslip of a 45©� sweptback wing with and without a fence at high subsonic speeds /

Kuhn, Richard E.
Byrnes, Andrew L.
Langley Aeronautical Laboratory.
United States. National Adviosry Committee for Aeronautics. NACA research memorandum.

January 1955

"January 28, 1955."Includes bibliographical references (p. 9).Mode of access: Internet

Span loadings and aerodynamic characteristics for a series of tip and trailing-edge controls on a 60° delta wing at Mach numbers of 1.61 and 2.01 /

Czarnecki, K. R.
Lord, Douglas R.
Langley Research Center.

January 1959

"September 1959."Cover title.Includes bibliographical references (p. 17-18).Mode of access: Internet

Investigation of leading-edge flap performance on delta and double-delta wings at supersonic speeds /

Covell, Peter F.
Miller, David S.
Wood, Richard M.
Langley Research Center.

January 1987

Prepared at Langley Research Center."April 1987"--Cover.Includes bibliographical references (p. 6-7)...

Low-speed wind-tunnel investigation of blowing boundary-layer control on leading- and trailing-edge flaps of a full-scale, low-aspect-ratio, 42° swept-wing airplane configuration /

Maki, Ralph L.
Giulianetti, Demo J.
Ames Research Center.

January 1959

"NASA TN D-16.""Ames Research Center, Moffett Field, Calif.""August 1959."Cover title.Includes bibli...

Aerodynamic load measurements and opening characteristics of automatic leading-edge slats on a 45 degree sweptback wing at transonic speeds /

Arabian, Donald D.
Reid, Charles F.
Runckel, Jack F.
United States. National Aeronautics and Space Administration.

Cover title."September 1961."Aircraft; Stresses and loads.Includes bibliographical references.Mode o...

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 ...

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

Wind-tunnel investigation of the effects of steady rolling on the aerodynamic loading characteristics of a 45©� sweptback wing at high subsonic speeds /

Wiggins, James W.
Kuhn, Richard E.
Langley Aeronautical Laboratory.
United States. National Adviosry Committee for Aeronautics. NACA research memorandum.
United States. National Advisory Committee for Aeronautics.

January 1954

"November 6, 1953."Cover title.Includes bibliographical references (p. 6).Mode of access: Internet

Full-scale wind-tunnel tests of a low-aspect-ratio, straight-wing airplane with blowing boundary-layer control on leading- and trailing-edge flaps /

Kelly, Mark W.
Maki, Ralph L.
Tolhurst, William H.
Ames Research Center.

January 1959

"NASA TN D-135.""Ames Research Center, Moffett Field, Calif.""September 1959."Title from cover.Inclu...

Investigation of the effects of leading-edge chord-extensions and fences in combination with leading-edge flaps on the aerodynamic characteristics at Mach numbers of 0.40 to 0.93 of a 45©� sweptback wing of aspect ratio 4 /

Spreemann, Kenneth P.
Alford, William J.
Langley Aeronautical Laboratory.
United States. National Advisory Committee for Aeronautics.

January 1957

"April 1957."Includes bibliographical references (p. 13).Mode of access: Internet

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...

An investigation of the effects of a geometric twist on the aerodynamic loading characteristics of a 45©� sweptback wing-body configuration at transonic speeds /

Williams, Claude V.
Langley Aeronautical Laboratory.
United States. National Adviosry Committee for Aeronautics. NACA research memorandum.
United States. National Advisory Committee for Aeronautics.

January 1954

"Declassified September 17, 1958.""October 12, 1954."Cover title.Includes bibliographical references...

An analysis of incremental horizontal-tail loads measured on a swept-wing bomber airplane in sideslip maneuvers /

McGowan, William A.
Langley Research Center.

January 1959

"NASA TN D-100.""Langley Research Center, Langley Field, Va.""October 1959."Title from cover.Include...

Effects of wing incidence on the longitudinal trim characteristics of a cambered 70° delta-wing configuration at mach numbers 3.0 to 5.0 /

Ahtye, Warren F.
Ames Research Center.

January 1960

"September 1960."Cover title.Includes bibliographical references (p. 23).Mode of access: Internet

Surface pressure distributions on a large-scale 49©� sweptback wing-body-tail configuration with blowing applied over the flaps and wing leading edge /

McLemore, H. Clyde.
Fink, Marvin P.
Langley Aeronautical Laboratory.
United States. National Adviosry Committee for Aeronautics. NACA research memorandum.

"February 17, 1958."Cover title.Includes bibliographical references (p. 16).Mode of access: Internet

Aerodynamic loading characteristics in sideslip of a 45©� sweptback wing with and without a fence at high subsonic speeds /

Kuhn, Richard E.
Byrnes, Andrew L.
Langley Aeronautical Laboratory.
United States. National Adviosry Committee for Aeronautics. NACA research memorandum.

January 1955

"January 28, 1955."Includes bibliographical references (p. 9).Mode of access: Internet

Span loadings and aerodynamic characteristics for a series of tip and trailing-edge controls on a 60° delta wing at Mach numbers of 1.61 and 2.01 /

Czarnecki, K. R.
Lord, Douglas R.
Langley Research Center.

January 1959

"September 1959."Cover title.Includes bibliographical references (p. 17-18).Mode of access: Internet

Investigation of leading-edge flap performance on delta and double-delta wings at supersonic speeds /

Covell, Peter F.
Miller, David S.
Wood, Richard M.
Langley Research Center.

January 1987

Prepared at Langley Research Center."April 1987"--Cover.Includes bibliographical references (p. 6-7)...

Low-speed wind-tunnel investigation of blowing boundary-layer control on leading- and trailing-edge flaps of a full-scale, low-aspect-ratio, 42° swept-wing airplane configuration /

Maki, Ralph L.
Giulianetti, Demo J.
Ames Research Center.

January 1959

"NASA TN D-16.""Ames Research Center, Moffett Field, Calif.""August 1959."Cover title.Includes bibli...

Aerodynamic load measurements and opening characteristics of automatic leading-edge slats on a 45 degree sweptback wing at transonic speeds /

Arabian, Donald D.
Reid, Charles F.
Runckel, Jack F.
United States. National Aeronautics and Space Administration.

Cover title."September 1961."Aircraft; Stresses and loads.Includes bibliographical references.Mode o...

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 /

Abstract

Extracted data

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 /

Abstract

Extracted data

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