Low-speed Static Lateral Stability Characteristics of a Canard Model Having a 60© Triangular Wing and Horizontal Tail PDF Download
Are you looking for read ebook online? Search for your book and save it on your Kindle device, PC, phones or tablets. Download Low-speed Static Lateral Stability Characteristics of a Canard Model Having a 60© Triangular Wing and Horizontal Tail PDF full book. Access full book title Low-speed Static Lateral Stability Characteristics of a Canard Model Having a 60© Triangular Wing and Horizontal Tail by William R. Bates. Download full books in PDF and EPUB format.
Author: William R. Bates
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 38
Get Book Here
Book Description
Author: William R. Bates
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 38
Get Book Here
Book Description
Author: William R. Bates
Publisher:
ISBN:
Category :
Languages : en
Pages : 16
Get Book Here
Book Description
Author: William R. Bates
Publisher:
ISBN:
Category :
Languages : en
Pages : 29
Get Book Here
Book Description
Author: John W. Draper
Publisher:
ISBN:
Category : Aerofoils
Languages : en
Pages : 43
Get Book Here
Book Description
An investigation has been made of the low-speed static stability characteristics of a canard model with a 45 degree sweptback wing and a 60 degree triangular horizontal control surface. The model had practically no allowable center-of-gravity range because of longitudinal instability that occurred at moderate and high lift coefficients with horizontal-control-surface incidences of 10 degrees or less. The horizontal control surface produced a sidewash which, at an incidence of 15 degrees at angles of attack greater than 7 degrees, was strong enough to make the model directionally stable with the vertical tail off. This sidewash caused a vertical tail mounted on the fuselage to be destabilizing at angles of attack above 11 degrees. Twin vertical tails mounted at the wing tips did not produce a similar destabilizing effect because they were located outside the sidewash field.
Author: William I. Scallion
Publisher:
ISBN:
Category : Delta wing airplanes
Languages : en
Pages : 64
Get Book Here
Book Description
Author: Thomas G. Gainer
Publisher:
ISBN:
Category : Aerodynamic measurements
Languages : en
Pages : 24
Get Book Here
Book Description
Author: Clarence D. Cone (Jr.)
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 76
Get Book Here
Book Description
Author: John M. Riebe
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 32
Get Book Here
Book Description
An investigation was made in the Langley 300 MPH 7- by 10-foot tunnel to determine the static stability characteristics of a cambered-delta-wing model. The cambered delta wing was derived from a segment of a cone selected so that the projected plan form with a wing dihedral angle of zero degrees was the same as a 60 degree delta wing. The projected plan form had an aspect ratio of 2.31.
Author: William C. Steeman
Publisher: BiblioGov
ISBN: 9781289265311
Category :
Languages : en
Pages : 50
Get Book Here
Book Description
The present investigation was conducted in the Langley high-speed 7-by 10-foot tunnel to determine the static longitudinal and lateral stability characteristics at high subsonic speeds of two canard airplane configurations previously tested at supersonic speeds. The Mach number range of this investigation extended from 0.60 to 0.94 and a maximum angle-of-attack range of -2dewg to 24deg was obtained at the lowest test Mach number. Two wing plan forms of equal area were studied in the present tests; one was a 60deg delta wing and the other was a trapezoid wing having an aspect ratio of 3, taper ratio of 0.143, and an unswept 80-percent-chord line. The canard control had a trapezoidal plan form and its area was approximately 11.5 percent of the wing area. The model also had a low-aspect-ratio highly swept vertical tail and twin ventral fins. The longitudinal control characteristics of the models were consistent with past experience at low speed on canard configurations in that stalling of the canard surface occurred at moderate and high control deflections for moderate values of angle of attack. This stalling could impose appreciable limitations on the maximum trim-lift coefficient attainable. The control effectiveness and maximum value of trim-lift was significantly increased by addition of a body flap having a conical shape and located slightly behind the canard surface on the bottom of the body. Addition of the canard surface at 0deg deflection had relatively little effect on overall directional stability of the delta-wing configuration; however, deflection of the canard surface from 0deg to 10deg had a large favorable effect on directional stability at high angles of attack for both the trapezoid- and delta-wing configurations.
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 26
Get Book Here
Book Description
