8/24/2023 0 Comments Shadow blade vortex 3.0![]() Vortex-Core Reversal Dynamics: Towards Vortex Random Access MemoryĪn energy-efficient, ultrahigh-density, ultrafast, and nonvolatile solid-state universal memory is a long-held dream in the field of information-storage technology. ![]() Comparison with available data indicates that: the present method is generally accurate in predicting the lift and induced drag coefficients but the predicted pitching moment is too positive the spanwise lifting pressure distributions estimated by the one vortex core solution of the present method are significantly better than the results of Mehrotra's method relative to the pressure peak values for the flat delta the two vortex core system applied to the double delta and strake wing produce overall aerodynamic characteristics which have good agreement with data except for the pitching moment and the computer time for the present method is about two thirds of that of Mehrotra's method. Semiempirical but simple methods were used to determine the initial positions of the free sheet and vortex core. Insights gained from this work should enable improved modeling of rotary-wing aerodynamics, as well as provide a framework for improved experimental investigations of rotor a n d advanced propeller wakes.Ī method for predicting aerodynamic characteristics of slender wings with edge vortex separation was developed. Third, and lastly, vortex core size initially decreases for low axial-flow advance ratios, but for large advance ratios core size asymptotically increases to a nominal upper limit. Second, the more efficient a rotor is with respect to induced power losses, the smaller the resulting vortex core size. First, the greater the rotor thrust, t h e larger the vortex core size in the rotor near-wake. In general, three conclusions can be drawn from the work in this paper. Experimental data from the literature is compared to the analytical results derived in this paper. The influence of thrust, induced power losses, advance ratio, and vortex structure on rotor vortex core size is assessed. Using a kinetic energy conservation approach, a number of simple analytic expressions are derived for estimating the core size of tip vortices in the near-wake of rotors in hover and axial-flow flight. Comparison with available data indicates that: (1) the present method is generally accurate in predicting the lift and induced drag coefficients but the predicted pitching moment is too positive (2) the spanwise lifting pressure distributions estimated by the one vortex core solution of the present method are significantly better than the results of Mehrotra's method relative to the pressure peak values for the flat delta (3) the two vortex core system applied to the double delta and strake wings produce overall aerodynamic characteristics which have good agreement with data except for the pitching moment and (4) the computer time for the present method is about two thirds of that of Mehrotra's method. Semi-empirical but simple methods were used to determine the initial positions of the free sheet and vortex core. A vortex-filament and core model for wings with edge vortex separationĪ vortex filament- vortex core method for predicting aerodynamic characteristics of slender wings with edge vortex separation was developed.
0 Comments
Leave a Reply. |
AuthorWrite something about yourself. No need to be fancy, just an overview. ArchivesCategories |