Wind Tunnel Investigation Of Effect Of Yaw On Lateral Stability Characteristics
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Wind Tunnel Investigation Of Effect Of Yaw On Lateral Stability Characteristics
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Author : Isidore G. Recant
language : en
Publisher:
Release Date : 1942
Wind Tunnel Investigation Of Effect Of Yaw On Lateral Stability Characteristics written by Isidore G. Recant and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1942 with Airplanes categories.
Combinations of an NACA 23012 tapered wing and a circular fuselage having a wedge-shaped rear were tested in the NACA 7- by 10-foot wind tunnel to determine the effect of wing-fuselage interference on the lateral-stability of wing-fuselage interference on the lateral-stability characteristics. The model configurations represented a high-wing, a mid-wing, and a low-wing monoplane. For each configuration, tests were made with a partial-span split flap neutral and deflected 60 degrees and with and without a vertical tail. Tests of the fuselage alone and of the fuselage with the vertical tail were also made.
Wind Tunnel Investigation Of Effects Of Ventral Fins At Two Positions On Lateral Stability Derivatives Of 45 High Wing Model Oscillating In Yaw
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Author : Byron M. Jaquet
language : en
Publisher:
Release Date : 1957
Wind Tunnel Investigation Of Effects Of Ventral Fins At Two Positions On Lateral Stability Derivatives Of 45 High Wing Model Oscillating In Yaw written by Byron M. Jaquet and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1957 with Airplanes categories.
An investigation was made in the Langley stability tunnel to determine the effects of ventral fins at two positions (zero and -70 degrees dihedral) on the lateral stability derivatives of a 45 degrees swept high-wing model oscillating in yaw. The effect of the ventral fins on the stability derivatives was determined with and without the vertical and horizontal tails for an angle-of-attack range of zero to 30 degrees at a Mach number of 0.13 and a Reynolds number of 830,000, based on the wing mean aerodynamic chord. The steady-state derivatives for a similar model without ventral fins are also presented. No discussion of the data has been made in order to expedite their publication.
Wind Tunnel Investigation Of The Static Lateral Stability Characteristics Of Wing Fuselage Combinations At High Supersonic Speeds
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Author : Paul G. Fournier
language : en
Publisher:
Release Date : 1953
Wind Tunnel Investigation Of The Static Lateral Stability Characteristics Of Wing Fuselage Combinations At High Supersonic Speeds written by Paul G. Fournier and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1953 with Aerodynamics, Supersonic categories.
Wind Tunnel Investigation To Determine The Horizontal And Vertical Tail Contributions To The Static Lateral Stability Characteristics Of A Complete Model Swept Wing Configuration At High Subsonic Speeds
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Author : James W. Wiggins
language : en
Publisher:
Release Date : 1956
Wind Tunnel Investigation To Determine The Horizontal And Vertical Tail Contributions To The Static Lateral Stability Characteristics Of A Complete Model Swept Wing Configuration At High Subsonic Speeds written by James W. Wiggins and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1956 with Airplanes categories.
An investigation was conducted in the Langley high-speed 7- by 10-foot tunnel to determine the horizontal- and vertical-tail contributions to the static lateral stability of a complete-model swept-wing configuration at high subsonic speeds. The results indicate that, in a general, Mach number effects within the range studied and wing effects on the tail contribution were small and the overall trends of the data of the present investigation agreed with those which have been established at low speeds.
Determination Of The Stability And Control Characteristics Of Airplanes From Tests Of Powered Models
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Author : Isidore G. Recant
language : en
Publisher:
Release Date : 1942
Determination Of The Stability And Control Characteristics Of Airplanes From Tests Of Powered Models written by Isidore G. Recant and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1942 with Airplanes categories.
A technique of testing wind-tunnel powered models has been developed as a result of experience gained in the investigation of the static longitudinal and lateral stability and control characteristics of several powered models in the NACA 7- by 10-foot wind tunnel. As an important part of this technique, a minimum program of the tests considered necessary to specify satisfactorily the static stability and control characteristics for present-day airplanes has been tentatively established.
Wind Tunnel Investigation Of Effect Of Canopies On Directional Stability Characteristics Of A Single Engine Airplane Model
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Author : Robert MacLachlan
language : en
Publisher:
Release Date : 1946
Wind Tunnel Investigation Of Effect Of Canopies On Directional Stability Characteristics Of A Single Engine Airplane Model written by Robert MacLachlan and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1946 with Airplanes categories.
A low-wing, single-engine airplane model was tested in the Langley stability tunnel to obtain data showing the effect of canopy size and shape on the directional stability characteristics of the model.
Low Speed Wind Tunnel Investigation Of The Effect Of Strakes And Nose Chines On Lateral Directional Stability Of A Fighter Configuration
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Author : Jay M. Brandon
language : en
Publisher:
Release Date : 1986
Low Speed Wind Tunnel Investigation Of The Effect Of Strakes And Nose Chines On Lateral Directional Stability Of A Fighter Configuration written by Jay M. Brandon and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1986 with Fighter planes categories.
Transonic Wind Tunnel Investigation Of The Static Stability And Control Characteristics Of A Supersonic Fighter Bomber Airplane
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Author :
language : en
Publisher:
Release Date : 1961
Transonic Wind Tunnel Investigation Of The Static Stability And Control Characteristics Of A Supersonic Fighter Bomber Airplane written by and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1961 with categories.
Langley Full Scale Tunnel Investigation Of The Factors Affecting The Directional Stability And Trim Characteristics Of A Fighter Type Airplane
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Author : Harold H. Sweberg
language : en
Publisher:
Release Date : 1945
Langley Full Scale Tunnel Investigation Of The Factors Affecting The Directional Stability And Trim Characteristics Of A Fighter Type Airplane written by Harold H. Sweberg and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1945 with Aerodynamics categories.
Summary: Tests were made in the Langley full-scale tunnel of the Grumman XF6F-4 airplane in order to investigate the factors that affect the directional stability and trim characteristics of a typical fighter-type airplane. Eight representative flight conditions were investigated in detail. The separate contributions of the wing-fuselage combination, the vertical tail, and the propeller to the directional stability of the airplane in each condition were determined. Extensive air-flow surveys of sidewash angle and dynamic-pressure ratio along a line coincident with the rudder hinge line were made for each condition investigated to aid in evaluating the slipstream effects. The data obtained from the air-flow surveys were also used to investigate methods for calculating the contribution of the vertical tail to the airplane directional stability. The results of the tests showed that, for the conditions investigated, the directional stability of the airplane was smallest for the gliding condition with flaps retracted and was greatest for the wave-off condition with flaps deflected 50°. The variation of sidewash angle at the vertical tail with angle of yaw was destabilizing for all conditions investigated. Propeller operation increased the magnitude of the destabilizing sidewash but, at small angles of yaw, also increased the dynamic pressure at the vertical tail sufficiently to make the combined effect stabilizing.
The Effect Of Lateral Area On The Lateral Stability And Control Characteristics Of An Airplane As Determined By Tests Of A Model In The Langley Free Flight Tunnel
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Author : Hubert M. Drake
language : en
Publisher:
Release Date : 1946
The Effect Of Lateral Area On The Lateral Stability And Control Characteristics Of An Airplane As Determined By Tests Of A Model In The Langley Free Flight Tunnel written by Hubert M. Drake and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1946 with Aerodynamics categories.
The effects of large variations of lateral area on the lateral stability and control characteristics of a free-flying model when ailerons are used as the principal control have been determined by flight tests in the Langley free-flight tunnel. The effects of the lateral-force parameter (rate of change of lateral-force coefficient with angle of sideslip) were investigated for a wide range of values of the directional-stability parameter (rate of change of yawing-moment coefficient with angle of sideslip) and the rotary-damping-in-yaw parameter (rate of change of yawing-moment coefficient with yawing angular velocity).