The conformal vortex generator (CVG) developed by Edge Aerodynamix is a flow control device that has been shown to reduce drag on commercial aircraft. However, questions remain about what drag reduction mechanisms are active. The current work focuses on studying the evolution of a boundary layer downstream of a CVG with a laminar inlet boundary layer. A proposed scaling law is presented based on a basic working model, which is then tested with flight scale testing on a general aviation aircraft (Piper Arrow) and laboratory testing. The laboratory testing was performed in a water tunnel on a flat plate model using two-dimensional two-component particle image velocimetry. Comparison of results between the water tunnel and flight scale testing are consistent with the proposed scaling law.
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