Drag reduction by suction of the boundary layer separated behind shock wave formation at high Mach numbers / by B. Regenscheit.

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Bibliographic Details
Main Author: Regenscheit, B.
Corporate Author: United States. National Advisory Committee for Aeronautics
Format: Government Document Book
Language:English
Published: Washington, D.C. : National Advisory Commitee for Aeronautics, [1947]
Series:Technical memorandum (United States. National Advisory Committee for Aeronautics) ; no. 1168.
Subjects:

MARC

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245 1 0 |a Drag reduction by suction of the boundary layer separated behind shock wave formation at high Mach numbers /  |c by B. Regenscheit. 
260 |a Washington, D.C. :  |b National Advisory Commitee for Aeronautics,  |c [1947] 
300 |a 13 pages, 5 unnumbered pages :  |b illustrations ;  |c 27 cm. 
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490 1 |a Technical memorandums ;  |v no. 1168. 
500 |a "July 1947." 
500 |a NACA TM Number 1168. 
500 |a Translated from Zentrale fur wissenschaftliches Berichtswesen der Luftfahrtforschung des Generalluftzeugmeisters (ZWB), Forschungsbericht Nr. 1424, July 1, 1941, by the National Advisory Commitee for Aeronautics. 
504 |a Includes bibliographical references. 
520 3 |a With an approach of the velocity of flight of a ship to the velocity of sound, there occurs a considerable increase of the drag. The reason for this must be found in the boundary layer separation caused by formation of shock waves. It will be endeavored to reduce the drag increase by suction of the boundary layer. Experimental results showed that drag increase may be considerably reduced by this method. It was, also, observed that, by suction, the position of shock waves can be altered to a considerable extent. 
650 0 |a Boundary layer.  |0 http://id.loc.gov/authorities/subjects/sh85016095. 
650 0 |a Shock waves.  |0 http://id.loc.gov/authorities/subjects/sh85121715. 
650 0 |a Drag (Aerodynamics)  |0 http://id.loc.gov/authorities/subjects/sh85039270. 
650 7 |a Boundary layer.  |2 fast  |0 (OCoLC)fst00837095. 
650 7 |a Drag (Aerodynamics)  |2 fast  |0 (OCoLC)fst00897351. 
650 7 |a Shock waves.  |2 fast  |0 (OCoLC)fst01116729. 
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