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Zur Aerodynamik des Ringflügels

Zur Aerodynamik des Ringflügels

Johannes Weissinger

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Editorial:
Springer Nature B.V.
Año de edición:
1957
Materia
Ciencia: cuestiones generales
ISBN:
9783663041559
72,96 €
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Die Wirkung eines Ruderausschlags auf die Druckverteilung eines unend­ lich dünnen, nahezu kreiszylindrischen Ringflügels (Länge L, Durchmesser D = 2R, Vorder- bzw. Hinterkante bei x = -L/2 bzw. x = L/2) kann im Prinzip nach dem in [2J beschriebenen Verfahren berechnet werden: Ist (in Zylinderkoordinaten x, r, f; vgl. Abb. 1, S. 24) 0() (1 ,1 ) c;(. (~,~) = L oln (§) cos n y?, n=o die Fourierentwicklung des (symmetrisch in ~ angenommenen) lokalen An­ stellwinkels, so ergibt sich die Zirkulationsverteilung ~ der Ringwirbel (und daraus die Druckdifferenz ß p = ~ V l) als 00 (1 ,2) wobei sich die Fourierkoeffizienten gn(3) aus der Integralgleichung 1 2~ ) -1 1 (1 ,3) n = 0, 1, 2, •••• (11) d ~’ , + ~ ) gn (5’) U n -1 LID bestimmen. Die Kerne Un(~) sind in [2J formelmäßig und für n = 0,1,2 als Schaubild angegeben, im vorliegenden Bericht sind sie für n = 0,1, 2, 3, 5 vertafelt bzw. aufgezeichnet (Tabelle 1, S. 17, 18, 19 und 20 und Abbildung 2, S. 24). Die Lösung von (1,3) erfolgt durch Entwicklung von gn(~) bzw. ~n(j) in eine Birnbaum- bzw. Fourier-Reihe: 00 ß = c ctg- - cos ß gn(~) c'’n sin l’ ~ , +L on 2 5 )’ =1 oe a on (1 ,5) L . = -2- + o(n (3) a 9 n cos s> S .

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