The development of a finite volume scheme for computing potential flow around a rotating propeller is presented. First, the governing potential equations are derived. General mesh properties, as well as the method of mesh generation, are discussed. Solution of the Mach 0.6 flow around an SR1 propeller is given. Near the leading edge, a low-density region terminated by a strong shock wave is indicated. The result is further confirmed by two-dimensional calculations of the airfoil section. At Mach 0.8, the calculation diverges with an indication of a separated cavity near the leading edge. The ability of the code to compute a high-speed flow is demonstrated by the calculation of Mach 0.8 flow around a fictitious propeller with an NACA 0012 cross section. A physical picture of a two-scale flowfield is conjectured for high-speed flow around a blade with a sharp leading edge. With the assumption that the local leading-edge flow does not affect the global flow, a solution of Mach 0.8 flow around an SR1 propeller can be obtained.
Finite volume calculation of three-dimensional potential flow around a propeller
Die finite Volumen Berechnung der dreidimensionalen Umstroemung einer Luftschraube
AIAA Journal ; 21 , 10 ; 1360-1364
1983
5 Seiten, 12 Bilder, 10 Quellen
Aufsatz (Zeitschrift)
Englisch
British Library Conference Proceedings | 1995
|