Supersonic lift and pitching moment of thin sweptback tapered wings produced by constant vertical acceleration. Subsonic leading edges and supersonic trailing edges /

Lift, pitching moment, and span load characteristics of wings at low speed as affected by variations of sweep and aspect ratio /

Hopkins, Edward J.
United States. National Advisory Committee for Aeronautics.

January 1951

Lift, pitching-moment, and pressure distribution were measured on a wing which was swept -40, -30, 0...

NACA Technical Reports

Cohen, Doris

January 1951

The method of superposition of linearized conical flows has been applied to the calculation of the a...

NACA Technical Reports

Brown, Clinton E

January 1946

A method is derived for calculating the lift and the drag due to lift of point-forward triangular wi...

Theoretical lift and damping in roll of thin sweptback wings of arbitrary taper and sweep at supersonic speeds : Subsonic leading edges and trailing edges /

Malvestuto, Frank S.
Ribner, Herbert S.
Margolis, Kenneth.
United States. National Advisory Committee for Aeronautics.

January 1949

Design curves are presented which permit rapid estimation of the lift-curve slope and damping-in-rol...

NACA Technical Reports

Malvestuto, Frank S , Jr
Margolis, Kenneth
Ribner, Herbert S

January 1950

On the basis of linearized supersonic-flow theory, generalized equations were derived and calculatio...

Rolling and yawing moments for swept-back wings in sideslip at supersonic sppeds /

Lampert, Seymour.
United States. National Advisory Committee for Aeronautics.

January 1951

A method is presented for determining the rolling and yawing moments of swept-back wings in steady s...

Some theoretical characteristics of trapezoidal wings in supersonic flow and a comparison of several wing-flap combinations /

Piland, Robert O.
United States. National Advisory Committee for Aeronautics.

January 1951

The theoretical lift and pitching moment due to angle of attack and pitching and the lateral force a...

THEORETICAL CALCULATIONS OF THE LATERAL FORCE AND YAWING MOMENT DUE TO ROLLING AT SUPERSONIC SPEEDS FOR SWEPTBACK TAPERED WINGS WITH

Kenneth Margolis
D Washington
Kenneth Margolis

January 1950

On the basis of linearized-supersonic-flow theory, the lateral force and yawing moment due to combin...

Aerodynamic characteristics at supersonic speeds of a series of wing-body combinations having cambered wings with an aspect ratio of 3.5 and a taper ratio of 0.2 : effects of sweep angle and thickness ratio on the aerodynamic characteristics in pitch at M = 2.0 /

Robinson, Ross B.
Langley Aeronautical Laboratory.
United States. National Adviosry Committee for Aeronautics. NACA research memorandum.

January 1952

"July 28, 1952."Includes bibliographical references (p. 7-8).Mode of access: Internet

Theoretical lift and damping in roll at supersonic speeds of thin sweptback tapered wings with streamwise tips, subsonic leading edges, and supersonic trailing edges

Margolis, Kenneth
Ribner, Herbert S
Malvestuto, Frank S , Jr

On the basis of linearized supersonic-flow theory, generalized equations were derived and calculatio...

Aerodynamic characteristics at supersonic speeds of a series of wing-body combinations having cambered wings with an aspect ratio of 3.5 and a taper ratio of 0.2 : effect at M = 1.60 of nacelle shape and position on the aerodynamic characteristics in pitch of two wing-body combinations with a 47©� sweptback wings /

Hasel, Lowell E.
Sevier, John R.
Langley Aeronautical Laboratory.
United States. National Adviosry Committee for Aeronautics. NACA research memorandum.

January 1952

"Januayr 12, 1952."Includes bibliographical references (p. 7).Mode of access: Internet

Theoretical loading at supersonic speeds of flat swept-back wings with interacting trailing and leading edges /

Cohen, Doris.
United States. National Advisory Committee for Aeronautics.

January 1949

By the method of superposition of conical flows, the load distribution is calculated for regions of ...

Lift, Drag, and Pitching Moment of Low-aspect-ratio Wings at Subsonic and Supersonic Speeds : Twisted and Cambered Triangular Wing of Aspect Ratio 2 with NACA 0003-63 Thickness Distribution

Hall, Charles F
Heitmeyer, John C

June 1951

This report presents the results of an investigation to ascertain the lift, drag, and pitching momen...

The effects of sideslip, aspect ratio, and Mach number on the lift and pitching moment of triangular, trapezoidal, and related plan forms in supersonic flow /

Jones, Arthur L.
Lindler, Elizabeth E.
Sorenson, Robert M.
United States. National Advisory Committee for Aeronautics.

January 1949

The variations of lift and pitching moment with sideslip in supersonic flow have been calculated for...

OF LEADINGEDGEAT SUBSONIC AND

Q Wi
E. Wetzel
E. Wetzel

January 1955

The results of a wind-tunnel investigation are presented which show the effect of the variation of t...

Lift, pitching moment, and span load characteristics of wings at low speed as affected by variations of sweep and aspect ratio /

Hopkins, Edward J.
United States. National Advisory Committee for Aeronautics.

January 1951

Lift, pitching-moment, and pressure distribution were measured on a wing which was swept -40, -30, 0...

NACA Technical Reports

Cohen, Doris

January 1951

The method of superposition of linearized conical flows has been applied to the calculation of the a...

NACA Technical Reports

Brown, Clinton E

January 1946

A method is derived for calculating the lift and the drag due to lift of point-forward triangular wi...

Theoretical lift and damping in roll of thin sweptback wings of arbitrary taper and sweep at supersonic speeds : Subsonic leading edges and trailing edges /

Malvestuto, Frank S.
Ribner, Herbert S.
Margolis, Kenneth.
United States. National Advisory Committee for Aeronautics.

January 1949

Design curves are presented which permit rapid estimation of the lift-curve slope and damping-in-rol...

NACA Technical Reports

Malvestuto, Frank S , Jr
Margolis, Kenneth
Ribner, Herbert S

January 1950

On the basis of linearized supersonic-flow theory, generalized equations were derived and calculatio...

Rolling and yawing moments for swept-back wings in sideslip at supersonic sppeds /

Lampert, Seymour.
United States. National Advisory Committee for Aeronautics.

January 1951

A method is presented for determining the rolling and yawing moments of swept-back wings in steady s...

Some theoretical characteristics of trapezoidal wings in supersonic flow and a comparison of several wing-flap combinations /

Piland, Robert O.
United States. National Advisory Committee for Aeronautics.

January 1951

The theoretical lift and pitching moment due to angle of attack and pitching and the lateral force a...

THEORETICAL CALCULATIONS OF THE LATERAL FORCE AND YAWING MOMENT DUE TO ROLLING AT SUPERSONIC SPEEDS FOR SWEPTBACK TAPERED WINGS WITH

Kenneth Margolis
D Washington
Kenneth Margolis

January 1950

On the basis of linearized-supersonic-flow theory, the lateral force and yawing moment due to combin...

Aerodynamic characteristics at supersonic speeds of a series of wing-body combinations having cambered wings with an aspect ratio of 3.5 and a taper ratio of 0.2 : effects of sweep angle and thickness ratio on the aerodynamic characteristics in pitch at M = 2.0 /

Robinson, Ross B.
Langley Aeronautical Laboratory.
United States. National Adviosry Committee for Aeronautics. NACA research memorandum.

January 1952

"July 28, 1952."Includes bibliographical references (p. 7-8).Mode of access: Internet

Theoretical lift and damping in roll at supersonic speeds of thin sweptback tapered wings with streamwise tips, subsonic leading edges, and supersonic trailing edges

Margolis, Kenneth
Ribner, Herbert S
Malvestuto, Frank S , Jr

On the basis of linearized supersonic-flow theory, generalized equations were derived and calculatio...

Aerodynamic characteristics at supersonic speeds of a series of wing-body combinations having cambered wings with an aspect ratio of 3.5 and a taper ratio of 0.2 : effect at M = 1.60 of nacelle shape and position on the aerodynamic characteristics in pitch of two wing-body combinations with a 47©� sweptback wings /

Hasel, Lowell E.
Sevier, John R.
Langley Aeronautical Laboratory.
United States. National Adviosry Committee for Aeronautics. NACA research memorandum.

January 1952

"Januayr 12, 1952."Includes bibliographical references (p. 7).Mode of access: Internet

Theoretical loading at supersonic speeds of flat swept-back wings with interacting trailing and leading edges /

Cohen, Doris.
United States. National Advisory Committee for Aeronautics.

January 1949

By the method of superposition of conical flows, the load distribution is calculated for regions of ...

Lift, Drag, and Pitching Moment of Low-aspect-ratio Wings at Subsonic and Supersonic Speeds : Twisted and Cambered Triangular Wing of Aspect Ratio 2 with NACA 0003-63 Thickness Distribution

Hall, Charles F
Heitmeyer, John C

June 1951

This report presents the results of an investigation to ascertain the lift, drag, and pitching momen...

The effects of sideslip, aspect ratio, and Mach number on the lift and pitching moment of triangular, trapezoidal, and related plan forms in supersonic flow /

Jones, Arthur L.
Lindler, Elizabeth E.
Sorenson, Robert M.
United States. National Advisory Committee for Aeronautics.

January 1949

The variations of lift and pitching moment with sideslip in supersonic flow have been calculated for...

OF LEADINGEDGEAT SUBSONIC AND

Q Wi
E. Wetzel
E. Wetzel

January 1955

The results of a wind-tunnel investigation are presented which show the effect of the variation of t...

Lift, pitching moment, and span load characteristics of wings at low speed as affected by variations of sweep and aspect ratio /

Hopkins, Edward J.
United States. National Advisory Committee for Aeronautics.

January 1951

Lift, pitching-moment, and pressure distribution were measured on a wing which was swept -40, -30, 0...

NACA Technical Reports

Cohen, Doris

January 1951

The method of superposition of linearized conical flows has been applied to the calculation of the a...

NACA Technical Reports

Brown, Clinton E

January 1946

A method is derived for calculating the lift and the drag due to lift of point-forward triangular wi...

Supersonic lift and pitching moment of thin sweptback tapered wings produced by constant vertical acceleration. Subsonic leading edges and supersonic trailing edges /

Abstract

Extracted data

Supersonic lift and pitching moment of thin sweptback tapered wings produced by constant vertical acceleration. Subsonic leading edges and supersonic trailing edges /

Abstract

Extracted data

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