An Analysis of the Effects of Wing Aspect Ratio and Tail Location on Static Longitudinal Stability below the Mach Number of Lift Divergence /

Wind-tunnel investigation of the static lateral stability characteristics of wing-fuselage combinations at high supersonic speeds. Aspect-ratio series /

Fournier, Paul G.
Byrnes, Andrew L.
Langley Aeronautical Laboratory.
United States. National Adviosry Committee for Aeronautics. NACA research memorandum.

January 1953

"February 9, 1953."Includes bibliographical references (p. 9).Mode of access: Internet

Effect of some present-day airplane design trends on requirements for lateral stability /

Bamber, Millard. J.
United States. National Advisory Committee for Aeronautics.

January 1941

The results of the computations are presented in the form of diagrams of variations of fin area with...

MACH NUMBERS FROM 2.29 TO 4.63 *

Eloger H. Fournier
M. Jaquet
Roger H. Fournier

January 1958

An investigation was made in the high Mach number test section of the Langley Unitary Plan wind tunn...

An Analysis of the Effects of Wing Aspect Ratio and Tail Location on Static Longitudinal Stability Below the Mach Number of Lift Divergence

Axelson, John A.
Crown, J. Conrad

January 1948

An analysis is presented of the influence of wing aspect ratio and tail location on the effects of c...

Some effects of tail height and wing plan form on the static longitudinal stability characteristics of a small-scale model at high subsonic speeds /

Few, Albert G.
King, Thomas J.
Langley Aeronautical Laboratory.
United States. National Adviosry Committee for Aeronautics. NACA research memorandum.

January 1954

The drag due to lift increases with increasing sweep through the Mach number range. Some increase in...

Effects of aspect ratio on air flow at a high subsonic mach numbers /

Lindsey, W. F.
Humphreys, Milton D.
Langley Aeronautical Laboratory.
United States. National Adviosry Committee for Aeronautics. NACA research memorandum.

January 1948

Schlieren photographs were used in an investigation to determine the effects of changing the aspect ...

Compressibility effects on the longitudinal stability and control of a pursuit-type airplane as measured in flight /

Turner, William N.
Clousing, Lawrence A.
Steffen, Paul J.
Ames Research Center.
United States. National Advisory Committee for Aeronautics.

It was found that large increases in stability occurred at high Mach numbers, reducing the controlla...

Effect of horizontal-tail size and tail length on low-speed static longitudinal stability and damping in pitch of a model having 45©� sweptback wing and tail surfaces /

Lichtenstein, Jacob H.
United States. National Advisory Committee for Aeronautics.

January 1951

Wind-tunnel results of the effects of horizontal-tail size and length on the low-speed static longit...

EXPERIMENTAL INVESTIGATION OF THE EFFECT OF VERTICAL-TAIL SIZE AND LENGTH AND OF FUSELAGE SHAPE AND LENGTH ON THE STATIC IKrERAL STABILITY CHARACTERISTICS OF A MODEL WITH 45 ° SWEFTBACK WING AND TAIL SURFACES 1-

M. J. Queijo
Walteb D. ‘i’i’olhae

January 1049

An. investigation was made to determine the effects of certical-tail size and length and of fuselage...

Effects of forebody length on the stability and control characteristics at a Mach number of 2.01 of a canard airplane configuration with a trapezoidal aspect-ratio-3 wing /

Spearman, M. Leroy.
Driver, Cornelius.
United States. National Aeronautics and Space Administration.

Cover title."April 1962."Aerodynamics, aircraft; Aircraft; Stability, longitudinal-static.Includes b...

Effect of horizontal-tail location on low-speed static longitudinal stability and damping in pitch of a model having 45©� sweptback wing and tail surfaces /

Lichtenstein, Jacob H.
United States. National Advisory Committee for Aeronautics.

January 1951

Wind-tunnel results are presented to show the effect of changes in horizontal-tail location on the l...

Static lateral characteristics at high subsonic speeds of a complete airplane model with a highly tapered wing having the 0.80 chord line unswept and with several tail configuration. /

Goodson, Kenneth W.
United States. National Aeronautics and Space Administration.
Langley Research Center.

January 1961

An investigation was made at high subsonic speeds of a complete model having a highly tapered wing a...

Effects of wing-tip droop on the longitudinal characteristics of two highly swept wing-body combinations at Mach numbers from 0.6 to 1.4 /

Knechtel, Earl D.
Lee, George
Ames Research Center.
United States. National Advisory Committee for Aeronautics.

An investigation was conducted to determine the effects of wing-tip droop on the longitudinal stabil...

Effect of downwash on the estimated elevator deflection required for trim of the XS-1 airplane at supersonic speeds /

Matthews, James T.
Langley Aeronautical Laboratory.
United States. National Adviosry Committee for Aeronautics. NACA research memorandum.

January 1948

This report contains the results of an investigation to determine from linearized theory, which has ...

Effects of ground proximity on the longitudinal aerodynamic characteristics of an unswept aspect-ratio-10 wing /

Carter, Arthur W.
Langley Research Center.
United States. National Aeronautics and Space Administration.

January 1970

Ground proximity effects of unswept aspect ratio 10 wing on longitudinal aerodynamic characteristics...

Wind-tunnel investigation of the static lateral stability characteristics of wing-fuselage combinations at high supersonic speeds. Aspect-ratio series /

Fournier, Paul G.
Byrnes, Andrew L.
Langley Aeronautical Laboratory.
United States. National Adviosry Committee for Aeronautics. NACA research memorandum.

January 1953

"February 9, 1953."Includes bibliographical references (p. 9).Mode of access: Internet

Effect of some present-day airplane design trends on requirements for lateral stability /

Bamber, Millard. J.
United States. National Advisory Committee for Aeronautics.

January 1941

The results of the computations are presented in the form of diagrams of variations of fin area with...

MACH NUMBERS FROM 2.29 TO 4.63 *

Eloger H. Fournier
M. Jaquet
Roger H. Fournier

January 1958

An investigation was made in the high Mach number test section of the Langley Unitary Plan wind tunn...

An Analysis of the Effects of Wing Aspect Ratio and Tail Location on Static Longitudinal Stability Below the Mach Number of Lift Divergence

Axelson, John A.
Crown, J. Conrad

January 1948

An analysis is presented of the influence of wing aspect ratio and tail location on the effects of c...

Some effects of tail height and wing plan form on the static longitudinal stability characteristics of a small-scale model at high subsonic speeds /

Few, Albert G.
King, Thomas J.
Langley Aeronautical Laboratory.
United States. National Adviosry Committee for Aeronautics. NACA research memorandum.

January 1954

The drag due to lift increases with increasing sweep through the Mach number range. Some increase in...

Effects of aspect ratio on air flow at a high subsonic mach numbers /

Lindsey, W. F.
Humphreys, Milton D.
Langley Aeronautical Laboratory.
United States. National Adviosry Committee for Aeronautics. NACA research memorandum.

January 1948

Schlieren photographs were used in an investigation to determine the effects of changing the aspect ...

Compressibility effects on the longitudinal stability and control of a pursuit-type airplane as measured in flight /

Turner, William N.
Clousing, Lawrence A.
Steffen, Paul J.
Ames Research Center.
United States. National Advisory Committee for Aeronautics.

It was found that large increases in stability occurred at high Mach numbers, reducing the controlla...

Effect of horizontal-tail size and tail length on low-speed static longitudinal stability and damping in pitch of a model having 45©� sweptback wing and tail surfaces /

Lichtenstein, Jacob H.
United States. National Advisory Committee for Aeronautics.

January 1951

Wind-tunnel results of the effects of horizontal-tail size and length on the low-speed static longit...

EXPERIMENTAL INVESTIGATION OF THE EFFECT OF VERTICAL-TAIL SIZE AND LENGTH AND OF FUSELAGE SHAPE AND LENGTH ON THE STATIC IKrERAL STABILITY CHARACTERISTICS OF A MODEL WITH 45 ° SWEFTBACK WING AND TAIL SURFACES 1-

M. J. Queijo
Walteb D. ‘i’i’olhae

January 1049

An. investigation was made to determine the effects of certical-tail size and length and of fuselage...

Effects of forebody length on the stability and control characteristics at a Mach number of 2.01 of a canard airplane configuration with a trapezoidal aspect-ratio-3 wing /

Spearman, M. Leroy.
Driver, Cornelius.
United States. National Aeronautics and Space Administration.

Cover title."April 1962."Aerodynamics, aircraft; Aircraft; Stability, longitudinal-static.Includes b...

Effect of horizontal-tail location on low-speed static longitudinal stability and damping in pitch of a model having 45©� sweptback wing and tail surfaces /

Lichtenstein, Jacob H.
United States. National Advisory Committee for Aeronautics.

January 1951

Wind-tunnel results are presented to show the effect of changes in horizontal-tail location on the l...

Static lateral characteristics at high subsonic speeds of a complete airplane model with a highly tapered wing having the 0.80 chord line unswept and with several tail configuration. /

Goodson, Kenneth W.
United States. National Aeronautics and Space Administration.
Langley Research Center.

January 1961

An investigation was made at high subsonic speeds of a complete model having a highly tapered wing a...

Effects of wing-tip droop on the longitudinal characteristics of two highly swept wing-body combinations at Mach numbers from 0.6 to 1.4 /

Knechtel, Earl D.
Lee, George
Ames Research Center.
United States. National Advisory Committee for Aeronautics.

An investigation was conducted to determine the effects of wing-tip droop on the longitudinal stabil...

Effect of downwash on the estimated elevator deflection required for trim of the XS-1 airplane at supersonic speeds /

Matthews, James T.
Langley Aeronautical Laboratory.
United States. National Adviosry Committee for Aeronautics. NACA research memorandum.

January 1948

This report contains the results of an investigation to determine from linearized theory, which has ...

Effects of ground proximity on the longitudinal aerodynamic characteristics of an unswept aspect-ratio-10 wing /

Carter, Arthur W.
Langley Research Center.
United States. National Aeronautics and Space Administration.

January 1970

Ground proximity effects of unswept aspect ratio 10 wing on longitudinal aerodynamic characteristics...

Wind-tunnel investigation of the static lateral stability characteristics of wing-fuselage combinations at high supersonic speeds. Aspect-ratio series /

Fournier, Paul G.
Byrnes, Andrew L.
Langley Aeronautical Laboratory.
United States. National Adviosry Committee for Aeronautics. NACA research memorandum.

January 1953

"February 9, 1953."Includes bibliographical references (p. 9).Mode of access: Internet

Effect of some present-day airplane design trends on requirements for lateral stability /

Bamber, Millard. J.
United States. National Advisory Committee for Aeronautics.

January 1941

The results of the computations are presented in the form of diagrams of variations of fin area with...

MACH NUMBERS FROM 2.29 TO 4.63 *

Eloger H. Fournier
M. Jaquet
Roger H. Fournier

January 1958

An investigation was made in the high Mach number test section of the Langley Unitary Plan wind tunn...

An Analysis of the Effects of Wing Aspect Ratio and Tail Location on Static Longitudinal Stability below the Mach Number of Lift Divergence /

Abstract

Extracted data

An Analysis of the Effects of Wing Aspect Ratio and Tail Location on Static Longitudinal Stability below the Mach Number of Lift Divergence /

Abstract

Extracted data

Related items

Related items