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• W2141304231 abstract "Increasing interest in natural laminar flow technology has created a need for improved techniques for predicting instability growth and transition for aircraft. At the conceptualdesign stage, there is a need for rapid and reliable methods that facilitate exploration of a large number of designs. While it is believed that linear stability theory in conjunction with the e n criterion provides adequate accuracy for conceptual design, existing linear stability codes are too slow to be used so early in the design process, often requiring significant user interaction and human-in-the-loop iteration to yield reasonable results. In this paper, we present an improved methodology for rapid and robust transition prediction. The technique uses a database of linear stability results on representative boundary layers and constructs a machine-learning fit to those results. Unlike many fit-based transition prediction methods, we do not attempt to model the behavior of n-factor envelopes. Rather, we closely mimic the procedure followed in linear stability computations by modeling the local growth rate of individual modes as a function temporal frequency, spatial wave number, and several boundary-layer parameters. This enables us to reproduce sophisticated n-factor behavior that previous techniques could not. While there have been other techniques that use databases, they have generally been restricted to incompressible flows and provide no way of extending their applicability or improving their accuracy. Our methodology is far less restrictive and is easily extended to specific applications by adding relevant data based on flow conditions and aircraft geometries of interest. Recent additions to the methodology include a modal description of the velocity and temperature profiles using singular value decomposition." @default.
• W2141304231 created "2016-06-24" @default.
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• W2141304231 date "2013-01-05" @default.
• W2141304231 modified "2023-09-23" @default.
• W2141304231 title "Extensible Rapid Transition Prediction for Aircraft Conceptual Design Using Modal Decomposition" @default.
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• W2141304231 doi "https://doi.org/10.2514/6.2013-231" @default.
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