Increasing Aircraft Fuel Efficiency with Boundary-Layer-Ingesting
Visualization of a characteristic NTF-CRM CFD solution computed using the LAVA curvilinear flow solver. Pressure coefficient is shown on the aircraft surface, while Mach number is shown on the aircraft symmetry plane and at selected spanwise cuts. Overall aerodynamic performance as well as quantities near the tail-cone thruster (TCT), shown above as the aft-mounted engine, are computed at multiple flow conditions to validate computational predictions against experimental data.
Image Credit: NASA/Ames, Leonardo Machado, Jared Duensing