Transonic Wind-tunnel Investigation of the Effects of Sweepback and Thickness Ratio on the Wing Loads of a Wing-body Combination of Aspect Ratio 4 and Taper Ratio 0.6 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 Transonic Wind-tunnel Investigation of the Effects of Sweepback and Thickness Ratio on the Wing Loads of a Wing-body Combination of Aspect Ratio 4 and Taper Ratio 0.6 PDF full book. Access full book title Transonic Wind-tunnel Investigation of the Effects of Sweepback and Thickness Ratio on the Wing Loads of a Wing-body Combination of Aspect Ratio 4 and Taper Ratio 0.6 by Robert J. Platt. Download full books in PDF and EPUB format.
Author: Robert J. Platt
Publisher:
ISBN:
Category : Aerodynamic load
Languages : en
Pages : 50
Get Book
Book Description
A transonic investigation of the effects of sweepback and thickness ratio on the wing loads of a wing in the presence of a body has been made in the Langley 8-foot transonic pressure tunnel. The tests covered wings with a thickness ratio of 6 percent for sweepback angles of 0, 25, and 45 degrees and a thickness ratio of 4 percent for an unswept wing.
Author: Robert J. Platt
Publisher:
ISBN:
Category : Aerodynamic load
Languages : en
Pages : 50
Get Book
Book Description
A transonic investigation of the effects of sweepback and thickness ratio on the wing loads of a wing in the presence of a body has been made in the Langley 8-foot transonic pressure tunnel. The tests covered wings with a thickness ratio of 6 percent for sweepback angles of 0, 25, and 45 degrees and a thickness ratio of 4 percent for an unswept wing.
Author: Thomas C. Kelly
Publisher:
ISBN:
Category : Aerodynamic load
Languages : en
Pages : 82
Get Book
Book Description
Pressure data have been obtained in the Langley 8-foot transonic tunnel at Mach numbers from 0.80 to 1.115 and angles of attack from 0 to 20 degrees for wing-body configurations employing a thin trapezoidal wing in combination with basic and indented bodies. The wing had 26.6 degrees sweepback of the quarter-chord line, an aspect ratio of 2.61, a taper ratio of 0.211, and 2-percent-thick symmetrical circular-arc airfoil sections parallel to the plane of symmetry. Results are also presented for the basic body alone. Reynolds numbers for the tests were on the order of 2,600,000, based on the wing mean aerodynamic chord.
Author: Don D. Davis (Jr.)
Publisher:
ISBN:
Category : Aerodynamics, Transonic
Languages : en
Pages : 22
Get Book
Book Description
Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 388
Get Book
Book Description
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 818
Get Book
Book Description
Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 508
Get Book
Book Description
Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages :
Get Book
Book Description
Includes the Committee's Technical reports no. 1-1058, reprinted in v. 1-37.
Author:
Publisher:
ISBN:
Category : Mechanics, Applied
Languages : en
Pages : 630
Get Book
Book Description
Author: James W. Wiggins
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 56
Get Book
Book Description
An investigation was performed in the Langley high-speed 7- by 10-foot tunnel in order to determine the rolling derivatives for swept-wing-body configurations at angles of attack from 0 degrees to 13 degrees and at high subsonic Mach numbers. The wings had sweep angles of 3.6 degrees, 32.6 degrees, 45 degrees, and 60 degrees at the quarter-chord line, an aspect ratio of 4, a taper ratio of 0.6, and an NACA 65A006 airfoil section parallel to the free stream. The results indicate a reduction in the damping-in-roll derivative at the higher test angles of attack. Of the wings tested, instability of the damping-in-roll derivative was experienced over the largest ranges of angle of attack and Mach number for the 32.6 sweptback wing.
Author: United States. National Aeronautics and Space Administration
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 448
Get Book
Book Description
