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Aerodynamic Theory: A General Review of Progress Under a by William Frederick Durand

By William Frederick Durand

Dieser Buchtitel ist Teil des Digitalisierungsprojekts Springer ebook records mit Publikationen, die seit den Anfängen des Verlags von 1842 erschienen sind. Der Verlag stellt mit diesem Archiv Quellen für die historische wie auch die disziplingeschichtliche Forschung zur Verfügung, die jeweils im historischen Kontext betrachtet werden müssen. Dieser Titel erschien in der Zeit vor 1945 und wird daher in seiner zeittypischen politisch-ideologischen Ausrichtung vom Verlag nicht beworben.

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Extra info for Aerodynamic Theory: A General Review of Progress Under a Grant of the Guggenheim Fund for the Promotion of Aeronautics

Example text

1/ 1. fnd shields-18Dmmtfium ... p 13D .. ~ 90" I/. Wifflout end shields .. o Fig. 13. Lift and drag coefficients for a rotating cylinder. effect). 5 for normal and something like 2 to 4 for slotted and suction wings respectively. Nevertheless, such procedure can scarcely be carried out in practice since in order to obtain such lift-coefficients the surface velocity of the cylinders must be of the order of three times the velocity of the airplane. This involves such high velocities of rotation in airplanes moving with the high speeds now usual, that the technical difficulties make the solution of the problem very difficult if not impossible.

K~ 1\ I "'''' "''F \\l .......... ~ '"'1' ~ 1'-.. :: <:> "- Ie? "'" ~1 t--... --r--:: r-,.. -. ,1 '"1 '"'F 7 - l-~<;I--~-~- - ... among those observations where the influence of systematic changes of form can be detected. S. A. are available, they have been preferred for inclusion, on account of the large Reynolds numbers Vely involved. These measurements have occasionally been undertaken with various 42 J II. PROPERTIES OF TYPICAL PROFILES Reynolds numbers so that the effect of the Reynolds number can be detected.

1) which has no resultant lift, but a pure moment, has however, an angle of incidence (see Fig. 8) The more general cross-sections obtained by superimposing this crosssection on to a circular arc profile of angle of incidence zero will also have an angle of incidence rxs. In order to have the ordinates still measured from the chord, it is therefore necessary to subtract the ordinates z = - (1/2) c rxs ~ of a flat plate with angle of incidence rxs' Similarly in obtaining the values of the forces and moments for an arbitrary angle of incidence rx (superposition of a flat plate) it is necessary to observe that only the difference rx - rxs = rx - uI6 is effective as an additional angle of incidence.

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