Effect of Reynolds number on the lateral-stability derivatives at low speed of swept-back and delta-wing-fuselage combinations oscillating in yaw /

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...

Investigation of the Influence of Fuselage and Tail Surfaces on Low-speed Static Stability and Rolling Characteristics of a Swept-wing Model

Bird, John D
Lichtenstein, Jacob H
Jaquet, Byron M

July 1952

Results are presented of a wind-tunnel investigation to determine influence of the fuselage and tail...

Effects of twist and camber on the low-speed longitudinal stability characteristics of a 45©� swept-back wing of aspect ratio 8 at Reynolds numbers from 1.5 x 10⁶ to 4.8 x 10 as determined by pressure distributions, force tests, and calculations /

Pratt, George L.
Langley Aeronautical Laboratory.
United States. National Adviosry Committee for Aeronautics. NACA research memorandum.

January 1952

"December 19, 1952."Includes bibliographical references (p. 23-24).Mode of access: Internet

The effects on dynamic lateral stability and control of large artificial variations in the rotary stability derivatives /

Schade, Robert O.
Hassell, James L.
United States. National Advisory Committee for Aeronautics.

January 1952

The results of an experimental and theoretical investigation of the effects of large artificial vari...

Experimental Determination of Effects of Frequency and Amplitude on the Lateral Stability Derivatives for a Delta, a Swept, and Unswept Wing Oscillating in Yaw

Fisher, Lewis R

January 1958

Three wing models were oscillated in yaw about their vertical axes to determine the effects of syste...

A study of the use of experimental stability derivatives in the calculation of the lateral disturbed motions of a swept-wing airplane and comparison with flight results /

Bird, John D.
Jaquet, Byron M.
United States. National Advisory Committee for Aeronautics.

January 1950

Experimentally determined lateral-stability derivatives of a swept-wing airplane are presented to sh...

Dynamic stability derivatives of a twin-jet fighter model for angles of attack from -10 ̊to 110

Grafton, Sue B.
Libbey, Charles E.
Langley Research Center.
United States. National Aeronautics and Space Administration.

January 1971

A low-speed investigation was conducted to determine the dynamic stability derivatives in pitch, rol...

Wind-tunnel investigation to determine the low speed yawing stability derivatives of a twin jet fighter model at high angles of attack

Newsom, W. A., Jr.
Coe, P. L., Jr.

August 1974

An investigation was conducted to determine the low-speed yawing stability derivatives of a twin-jet...

DERIVATIVES OF A 60 ° DE15!A-WINGMODEL AS AFFECTED BY CHANGES IN VERTICAL POSITION OF THE WING AND IN RATIO OF FUSELAGE DIAMETER TO WIJ!JGSPAN

M. Jaquet
Herman S. Fletcher
M. Jaquet
Herman S. Fletcher

January 1956

An investigation was made in the Lsngley stability tunnel to deter-mine the effects on the steady-st...

Wind tunnel investigation of effect of yaw on lateral-stability characteristics. 4 - Symmetrically tapered wing with a circular fuselage having a wedge-shaped rear and a vertical tail /

Recant, I. G.
Wallace, Arthur R.
Langley Aeronautical Laboratory.
United States. National Advisory Committee for Aeronautics.

Combinations of an NACA 23012 tapered wing and a circular fuselage having a wedge-shaped rear were t...

Effect of Fuselage and Tail Surfaces on Low-speed Yawing Characteristics of a Swept-wing Model as Determined in Curved-flow Test Section of Langley Stability Tunnel

Jaquet, Byron M
Cowan, John W
Bird, John D

October 1951

Results are presented of a wind-tunnel investigation made to determine the influence of the fuselage...

Effects of wing position and fuselage size on the low-speed static rolling stability characteristics of a delta-wing model

Goodman, Alex
Thomas, David T , Jr

An investigation was made to determine the effects of wing position and fuselage size on the low-spe...

Low-Speed Investigation of the Effects of Frequency and Amplitude of Oscillation in Sideslip on the Lateral Stability Derivatives of a 60 deg Delta Wing, a 45 deg Sweptback Wing and an Unswept Wing

Williams, James L.
Lichtenstein, Jacob H.

May 1961

A low-speed investigation has been conducted in the Langley stability tunnel to study the effects of...

NACA Research Memorandums

Gillis, Clarence L.
Chapman, Rowe, Jr.

September 1956

Lateral-stability flight tests were made over the Mach number range from 0.7 to 1.3 of models of thr...

Lateral Oscillatory Characteristics of the Republic F-91 Airplane Calculated by Using Low-Speed Experimental Static and Rotary Derivatives

Fletcher, H. S.
Jaquet, Byron M.

August 1953

The present investigation was conducted to determine, from low-speed tests in the Langley stability ...

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...

Investigation of the Influence of Fuselage and Tail Surfaces on Low-speed Static Stability and Rolling Characteristics of a Swept-wing Model

Bird, John D
Lichtenstein, Jacob H
Jaquet, Byron M

July 1952

Results are presented of a wind-tunnel investigation to determine influence of the fuselage and tail...

Effects of twist and camber on the low-speed longitudinal stability characteristics of a 45©� swept-back wing of aspect ratio 8 at Reynolds numbers from 1.5 x 10⁶ to 4.8 x 10 as determined by pressure distributions, force tests, and calculations /

Pratt, George L.
Langley Aeronautical Laboratory.
United States. National Adviosry Committee for Aeronautics. NACA research memorandum.

January 1952

"December 19, 1952."Includes bibliographical references (p. 23-24).Mode of access: Internet

The effects on dynamic lateral stability and control of large artificial variations in the rotary stability derivatives /

Schade, Robert O.
Hassell, James L.
United States. National Advisory Committee for Aeronautics.

January 1952

The results of an experimental and theoretical investigation of the effects of large artificial vari...

Experimental Determination of Effects of Frequency and Amplitude on the Lateral Stability Derivatives for a Delta, a Swept, and Unswept Wing Oscillating in Yaw

Fisher, Lewis R

January 1958

Three wing models were oscillated in yaw about their vertical axes to determine the effects of syste...

A study of the use of experimental stability derivatives in the calculation of the lateral disturbed motions of a swept-wing airplane and comparison with flight results /

Bird, John D.
Jaquet, Byron M.
United States. National Advisory Committee for Aeronautics.

January 1950

Experimentally determined lateral-stability derivatives of a swept-wing airplane are presented to sh...

Dynamic stability derivatives of a twin-jet fighter model for angles of attack from -10 ̊to 110

Grafton, Sue B.
Libbey, Charles E.
Langley Research Center.
United States. National Aeronautics and Space Administration.

January 1971

A low-speed investigation was conducted to determine the dynamic stability derivatives in pitch, rol...

Wind-tunnel investigation to determine the low speed yawing stability derivatives of a twin jet fighter model at high angles of attack

Newsom, W. A., Jr.
Coe, P. L., Jr.

August 1974

An investigation was conducted to determine the low-speed yawing stability derivatives of a twin-jet...

DERIVATIVES OF A 60 ° DE15!A-WINGMODEL AS AFFECTED BY CHANGES IN VERTICAL POSITION OF THE WING AND IN RATIO OF FUSELAGE DIAMETER TO WIJ!JGSPAN

M. Jaquet
Herman S. Fletcher
M. Jaquet
Herman S. Fletcher

January 1956

An investigation was made in the Lsngley stability tunnel to deter-mine the effects on the steady-st...

Wind tunnel investigation of effect of yaw on lateral-stability characteristics. 4 - Symmetrically tapered wing with a circular fuselage having a wedge-shaped rear and a vertical tail /

Recant, I. G.
Wallace, Arthur R.
Langley Aeronautical Laboratory.
United States. National Advisory Committee for Aeronautics.

Combinations of an NACA 23012 tapered wing and a circular fuselage having a wedge-shaped rear were t...

Effect of Fuselage and Tail Surfaces on Low-speed Yawing Characteristics of a Swept-wing Model as Determined in Curved-flow Test Section of Langley Stability Tunnel

Jaquet, Byron M
Cowan, John W
Bird, John D

October 1951

Results are presented of a wind-tunnel investigation made to determine the influence of the fuselage...

Effects of wing position and fuselage size on the low-speed static rolling stability characteristics of a delta-wing model

Goodman, Alex
Thomas, David T , Jr

An investigation was made to determine the effects of wing position and fuselage size on the low-spe...

Low-Speed Investigation of the Effects of Frequency and Amplitude of Oscillation in Sideslip on the Lateral Stability Derivatives of a 60 deg Delta Wing, a 45 deg Sweptback Wing and an Unswept Wing

Williams, James L.
Lichtenstein, Jacob H.

May 1961

A low-speed investigation has been conducted in the Langley stability tunnel to study the effects of...

NACA Research Memorandums

Gillis, Clarence L.
Chapman, Rowe, Jr.

September 1956

Lateral-stability flight tests were made over the Mach number range from 0.7 to 1.3 of models of thr...

Lateral Oscillatory Characteristics of the Republic F-91 Airplane Calculated by Using Low-Speed Experimental Static and Rotary Derivatives

Fletcher, H. S.
Jaquet, Byron M.

August 1953

The present investigation was conducted to determine, from low-speed tests in the Langley stability ...

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...

Investigation of the Influence of Fuselage and Tail Surfaces on Low-speed Static Stability and Rolling Characteristics of a Swept-wing Model

Bird, John D
Lichtenstein, Jacob H
Jaquet, Byron M

July 1952

Results are presented of a wind-tunnel investigation to determine influence of the fuselage and tail...

Effects of twist and camber on the low-speed longitudinal stability characteristics of a 45©� swept-back wing of aspect ratio 8 at Reynolds numbers from 1.5 x 10⁶ to 4.8 x 10 as determined by pressure distributions, force tests, and calculations /

Pratt, George L.
Langley Aeronautical Laboratory.
United States. National Adviosry Committee for Aeronautics. NACA research memorandum.

January 1952

"December 19, 1952."Includes bibliographical references (p. 23-24).Mode of access: Internet

Effect of Reynolds number on the lateral-stability derivatives at low speed of swept-back and delta-wing-fuselage combinations oscillating in yaw /

Abstract

Extracted data

Effect of Reynolds number on the lateral-stability derivatives at low speed of swept-back and delta-wing-fuselage combinations oscillating in yaw /

Abstract

Extracted data

Related items

Related items