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
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
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 : 86
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: Robert J. Platt
Author: Robert J. Platt
Author: Thomas C. Kelly
Author: United States. National Advisory Committee for Aeronautics
Author: Don D. Davis (Jr.)
Author: 
Author: United States. National Advisory Committee for Aeronautics
Author: United States. National Advisory Committee for Aeronautics
Author: 
Author: 
Author: United States. National Aeronautics and Space Administration