Numerical Investigation on Flow Separation Control for Aircraft Serpentine Intake with Coanda Injector
Introduction
Modern aircraft engines require efficient air intake systems to ensure stable performance and fuel efficiency. However, serpentine intakes—designed for stealth and compactness—often face the challenge of flow separation, which can reduce pressure recovery and compromise engine stability.Understanding Flow Separation
Flow separation occurs when the smooth flow of air along the intake surface breaks away, leading to turbulence and energy loss. This phenomenon is particularly significant in serpentine intakes, where the curved geometry creates complex airflow patterns. Controlling this separation is crucial for achieving optimal aerodynamic efficiency.Role of the Coanda Injector
The Coanda effect—the tendency of a fluid jet to attach itself to a nearby surface—is utilized in this research to control airflow. By injecting air strategically through Coanda injectors, the study explores how flow can be reattached to surfaces, minimizing separation zones and improving overall flow uniformity.Numerical Analysis and Findings
Through detailed numerical simulations, the study evaluates how variations in injector angle, velocity, and position affect the performance of the serpentine intake. Results show that the Coanda injector significantly enhances pressure recovery and reduces flow distortion, leading to smoother air delivery to the engine.Conclusion
This numerical investigation highlights the potential of Coanda-based flow control as a promising technique for future aerospace intake designs. By improving airflow behavior in serpentine ducts, the approach contributes to greater engine efficiency, reduced noise, and improved overall aircraft performance.Scientific World Research Awards🏆
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