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This book rigorously examines supersonic laminar boundary layer dynamics around thin airfoils, aiming for breakthroughs in aerodynamic efficiency and fuel savings in high-speed aerospace applications. By integrating analytical modeling, computational simulations, and experimental validation, this research refines traditional supersonic flow models. Employing advanced boundary layer theory and introducing a local linkage Mach number m, the model captures critical interactions such as shock waves, compressibility effects, and adverse pressure gradients with remarkable accuracy. The model's precision is confirmed through high-fidelity Ansys Fluent simulations and experimental AF300 wind tunnel tests on NACA airfoils, achieving accuracies within 3% for drag and 5% for lift. These results not only validate the model's robustness but also set a new standard for high-speed aerodynamics, offering a pathway for optimized airfoil design in civil and military applications. This foundational work supports future exploration into flow hybrid control techniques, promising to revolutionize maneuverability and efficiency in supersonic flight in civil and military aviation.
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Hinweis: Dieser Artikel kann nur an eine deutsche Lieferadresse ausgeliefert werden.