Abstract
The objective of this dissertation is to investigate and usher in CoFlow Jet (CFJ) active flow control as a novel technology to enhance supersonic aircraft performance for the first time in two crucial areas:
1) Substantially increasing the maximum lift coefficient for highly swept and thin supersonic wings at low speeds;
2) Substantially increasing the stability range of supersonic inlets and efficiency at supersonic speeds.
The major intellectual contributions of this dissertation are:
1) Developed the CFJ AFC methodology and demonstrated for the first time that supersonic highly swept wing with low aspect ratio and thin airfoil can break the conventional C Lmax limit with the magnitude increased more than 100% using CFJ AFC.
2) The conceptual design indicates that a breakthrough for a Mach 4 supersonic aircraft, which benefits from the CFJ C Lmax enhancement with range substantially increased, takeoff speed and runway lengths substantially reduced, engine thrust and the community noise substantially decreased.
3) Developed for the first time a zero-net-mass-flux flow control using CFJ for supersonic inlet to increase the operating stability and reduce energy consumption by avoiding dumping the bleed mass flow withdrawn at the throat.
4) Investigated and provided a guideline to design CFJ distribution along span to enhance the performance and efficiency for flap application.