The vortex-embedded potential method for the prediction of hover performance is described with emphasis on the ongoing process of engineering development of the code. It is demonstrated that this compressible/transonic CFD (Computation Fluid Dynamics) code provides rapidly converging, free-wake solutions with the speed, accuracy and convenience required of an engineering tool. Excellent comparisons are obtained between computed power and UH-60A model data. The effects of some geometric variations on this rotor are used to illustrate the ability to predict the effects of twist, seep, taper and blade number on induced power. It is shown that the location of the tip vortex, especially the radial location is a powerful determinant of hover efficiency and that blade geometry can influence overall performance by its' effect on this radial location.
Hover performance prediction using CFD
Eine Prognose zur Leistungsbewertung für den Schwebeflug eines Hubschraubers mittels der rechnerischen Fluiddynamik
Forum, Annual Forum, American Helicopter Society, 50 ; 2 ; 1259-1273
1994
15 Seiten, 14 Bilder, 12 Quellen
Conference paper
English
Evaluation of hover performance prediction codes
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