Swept and Delta Wing Sense
Author:
Publisher:
Published: 1955
Total Pages: 44
ISBN-13:
DOWNLOAD EBOOKRead and Download eBook Full
Author:
Publisher:
Published: 1955
Total Pages: 44
ISBN-13:
DOWNLOAD EBOOKAuthor: Richard Shepherd Shevell
Publisher: Pearson Education India
Published: 1989
Total Pages: 468
ISBN-13: 9788177587425
DOWNLOAD EBOOKAuthor: Captain Eric Brown CBE DSC AFC QCVSA RN
Publisher: The History Press
Published: 2012-03-01
Total Pages: 176
ISBN-13: 0752476912
DOWNLOAD EBOOKIn December 1943, a top secret contract (E.24/43) was awarded to Miles Aircraft. The contract was to build the world's first supersonic jet capable of 1000mph. The only reliable source of data on supersonic objects came from the Armament Research Dept and their wind tunnel tests on ammunition. From this, Miles developed an exceptionally thin-winged, bullet-shaped aircraft. the research was inexplicably passed to the Americans in 1944. By December 1945, one prototype was virtually complete. The second, destined for an attempt at the sound barrier was 80 per cent complete. In February 1946, Capt Eric Brown was confirmed as the test pilot and October 1946 was set for the supersonic trials. However, on 12 February 1946, Miles were ordered to stop production. No plausible explanation was given for the cancellation when Britain was within six months of breaking the sound barrier. Eric Brown and others directly involved including Dennis Bancroft, the Chief Aerodynamicist on the M.52, have now come together to try and finally solve the mystery behind the cancellation.
Author:
Publisher:
Published: 1975
Total Pages: 2834
ISBN-13:
DOWNLOAD EBOOKAuthor: United States. Superintendent of Documents
Publisher:
Published: 1968
Total Pages: 1366
ISBN-13:
DOWNLOAD EBOOKAuthor: Arnold Polak
Publisher:
Published: 1970
Total Pages: 48
ISBN-13:
DOWNLOAD EBOOKThe flow of a perfect gas over the slab portion of a blunted delta wing flying at hypersonic speeds is studied. A set of approximate equations is derived and a solution - for an inviscid flow - is obtained. Using this solution as a representation for the inviscid flow problem, a formulation to the laminar boundary-layer equations is presented; one which is applicable to the flow field's azimuthal planes where the crossflow gradients are not too large. Numerical solutions to these boundary-layer equations have been obtained; however, these are restricted to the azimuthal planes and near to the leading edges. The results indicate the presence of a dividing surface streamline since a numerical solution could not be obtained near the centerplane of the wing, where the crossflow velocity is large. (Author).
Author: Thomas R. Yechout
Publisher: AIAA
Published: 2003
Total Pages: 666
ISBN-13: 9781600860782
DOWNLOAD EBOOKBased on a 15-year successful approach to teaching aircraft flight mechanics at the US Air Force Academy, this text explains the concepts and derivations of equations for aircraft flight mechanics. It covers aircraft performance, static stability, aircraft dynamics stability and feedback control.
Author: Alexander Lippisch
Publisher: Iowa State Press
Published: 1981
Total Pages: 144
ISBN-13:
DOWNLOAD EBOOKDen tyske flykonstruktør beskriver her udviklingen og forsøgene med Tailless- og Delta Wing- flytyper.