The proposed program of work will show that it is possible to predict the behavior of flight vehicles in response to external stimuli such as microbursts or wake-vortex encounters, using tractable high-speed computational methodologies. In the Phase I work outlined in this proposal, computational tools, based on well tried configuration modeling methods and structural analysis techniques, will be applied in the time domain, and their performance demonstrated modeling typical aircraft in representative situations. Certain extensions to the numerical flow method would be investigated with a view to speeding up the calculations when treating the complex vortex wake/surface interactions. In a subsequent Phase II, the method would be formalized and implemented, and its performance validated through comparison between the calculated results and results obtained from flight and wind-tunnel tests of representative aircraft. Reduced reliance of wind-tunnel testing of scale modelsReduced prototype development timeReduced prototype development costsReduced technical risk during developmentReduced overall program cost for new aircraft
Keywords: Phase_I, NASA, Abstract, FY94
