Patent ID: 8887482

Claim:
An active flow control system, comprising: an ignition source; a first pulse detonation tube coupled to the ignition source and comprising a fuel inlet, the first pulse detonation tube configured to create a detonation wave from a deflagration wave after ignition of fuel within the first pulse detonation tube via the ignition source; and a first outlet coupled to an aerodynamic surface and configured to direct the detonation wave into an ambient airflow over the aerodynamic surface; a second pulse detonation tube having a second outlet coupled to the aerodynamic surface and configured to direct a detonation wave from the second pulse detonation tube into the ambient airflow over the aerodynamic surface; and a pulse detonation controller configured to determine a presence of a shock wave, and in response to determining the presence of the shock wave, coordinating the ignition of the first pulse detonation tube and the second pulse detonation tube such that the shock wave is eliminated or moved forward or aft.