Are you looking for read ebook online? Search for your book and save it on your Kindle device, PC, phones or tablets. Download Wartime Report PDF full book. Access full book title Wartime Report by . Download full books in PDF and EPUB format.
Author: Publisher: ISBN: Category : Aeronautics Languages : en Pages : 690
Book Description
Reproductions of reports, some declassified, of research done at Langley Memorial Aeronautical Laboratory during World War II. The order of reports does not represent when they were chronologically issued. Reference to the original version of each report is included.
Author: Publisher: ISBN: Category : Aeronautics Languages : en Pages : 690
Book Description
Reproductions of reports, some declassified, of research done at Langley Memorial Aeronautical Laboratory during World War II. The order of reports does not represent when they were chronologically issued. Reference to the original version of each report is included.
Author: F. E. West Publisher: ISBN: Category : Aerofoils Languages : en Pages : 56
Book Description
The effects of compressibility on the lift, pressure, pitching-moment, and load characteristics of a 12-foot tapered wing having NACA 64-210 airfoil sections and aspect ratio of 6 is presented for Mach numbers up to 0.60 and an angle-of-attack range of -4 degrees up through the stall.
Author: E. O. Pearson Publisher: ISBN: Category : Aerodynamic load Languages : en Pages : 48
Book Description
Force and pressure-distribution measurements were made on a fighter-type wing model of conventional NACA 230-series airfoil sections in the Langley 16-foot high-speed tunnel to determine the effects of compressibility on the maximum lift characteristics and the span-wise load distribution. The range of angle of attack investigated was from -10 to +24 degrees. The Mach range of from 0.20 to 0.70 at small and medium angles of attack and from 0.15 to 0.625 at very large angles of attack. Maximum lift coefficient increased up to a Mach number of 0.3, decreased rapidly to a Mach number of 0.55, and then decreased moderately. At high speeds, maximum lift coefficient was reached at from 10 to 12 degrees beyond the stalling angle. In high-speed stalls, resultant load underwent a moderate shift outward.
Author: 
Author: United States. National Advisory Committee for Aeronautics
Author: 
Author: F. E. West
Author: E. O. Pearson
Author: 
Author: United States. National Advisory Committee for Aeronautics
Author: United States. National Advisory Committee for Aeronautics
Author: United States. National Advisory Committee for Aeronautics
Author: Stanley Corrsin
Author: