Static Stability Characteristics of a Delta- Winged Airplane Configuration with Nacelles, a Trapezoidal Canard and a Drooped Tail at Mach Numbers from 0.70 to 3.52 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 Static Stability Characteristics of a Delta- Winged Airplane Configuration with Nacelles, a Trapezoidal Canard and a Drooped Tail at Mach Numbers from 0.70 to 3.52 PDF full book. Access full book title Static Stability Characteristics of a Delta- Winged Airplane Configuration with Nacelles, a Trapezoidal Canard and a Drooped Tail at Mach Numbers from 0.70 to 3.52 by . Download full books in PDF and EPUB format.
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 68
Get Book Here
Book Description
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 68
Get Book Here
Book Description
Author: LeRoy S. Fletcher
Publisher:
ISBN:
Category :
Languages : en
Pages : 108
Get Book Here
Book Description
Author: William R. Bates
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 38
Get Book Here
Book Description
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 36
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: Victor L. Peterson
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 31
Get Book Here
Book Description
The results of an investigation of the static longitudinal stability and control characteristics of a canard airplane configuration are presented without analysis for the Mach number range from 0.70 to 2.22. The configuration consisted of an aspect ratio vertical tail, and a Sears-Haack body. The hinge line of the canard was in the extended chord plane of the wing, 1.15 wing mean aerodynamic chords ahead of the reference center of moments. The ratio of the area of the exposed canard panels to the total area of the wing is 8.1 percent. Data are presented for various combinations of the canard, wing, and vertical tail for an angle-of-attack range from -6 to 18 degrees. The canard deflection angles ranged from 0 to 20 degrees.
Author: M. Leroy Spearman
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 36
Get Book Here
Book Description
Author: Victor L. Peterson
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 29
Get Book Here
Book Description
The results of an investigation of the static longitudinal stability and control characteristics of a canard airplane configuration are presented without analysis for the Mach number range from 0.70 to 2.22. The configuration consisted of an aspect ratio 3.1 unswept wing, an aspect ratio 3.0 unswept canard, a low aspect ratio vertical tail, and a Sears-Haack body. The hinge line of the canard was in the extended chord plane of the wing, 1.33 wing mean aerodynamic chords ahead of the reference center of moments. The ratio of the area of the exposed canard panels to the total area of the wing is 8.1 percent. Data are presented for various combinations of the canard, wing, and vertical tail for an angle-of-attack range from -6 to 18 degrees. The canard deflection angles ranged from 0 to 20 degrees.
Author: Victor L. Peterson
Publisher:
ISBN:
Category :
Languages : en
Pages : 1
Get Book Here
Book Description
The static aerodynamic characteristics of a canard airplane configuration having twin vertical stabilizing surfaces are presented. The model consisted of a wing and canard both of triangular plan form and aspect ratio 2 mounted on a Sears-Haack body of fineness ratio 12.5 and two swept and tapered wing-mounted vertical tails of aspect ratio 1.35. Data are presented for Mach numbers from 0.70 to 2.22 and for angles of attack from -6 degrees to +18 degrees at 0 degrees and 5 degrees sideslip. Tests were made with the canard off and with the canard on. Nominal canard deflection angles ranged from 0 degrees to 10 degrees. The Reynolds number was 3.68 times 10 to the 6th power based on the wing mean aerodynamic chord. Selected portions of the data obtained in this investigation are compared with previously published results for the same model having a single vertical tail instead of twin vertical tails. (Author).
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 1466
Get Book Here
Book Description
