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- W2321813496 abstract "This paper demonstrates the use of CFD as a critical tool to provide increased fidelity of the aerodynamic analysis for a generic blended wing body UCAV constructed at a conceptual design level. Although the high level of accuracy typically required for a preliminary design was not necessary, a relatively accurate assessment for aerodynamic forces and moments became important even at this stage of design when one has to consider the feasibility in carrier landing. The UCAV designed with low observables in mind typically has issues with the pitch control and generation of sufficient lift for a low speed landing. In this paper, the tailless UCAV with four flaps and elevons on each side was studied to find the optimal location and shape of an additional lift enhancing device such as a belly flap. With the addition of a belly flap, values close to the required maximum lift condition were obtainable. It was also shown that landing pitch trim would be possible with the best flap/elevon deflection schedule and an added rotating canard. Since this study was to support a conceptual design level vehicle, optimal shape design of the aircraft body, flaps/elevons, belly flap or the canard was not attempted but the results were sufficient to help the designers." @default.
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- W2321813496 date "2010-01-04" @default.
- W2321813496 modified "2023-09-26" @default.
- W2321813496 title "Landing Pitch Control Analysis of a Blended Wing Body UCAV" @default.
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- W2321813496 doi "https://doi.org/10.2514/6.2010-1035" @default.
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