However, the mitigation of sonic booms, which can cause serious environmental problems for supersonic transport (SST), remains one of the biggest technical challenges for supersonic flight. Since the 21st century, a revived interest in civil supersonic flight has rekindled sonic boom research. For energy saving, the suction and injection slots can be selectively opened, which are opened when the supersonic aircraft flies over the city but are closed when the aircraft flies over the sea. From the viewpoint of aerodynamics, opening the suction and injection slots will have no adverse effect on the aerodynamic performances of the supersonic aircraft and even increase the lift-drag ratio under some circumstances. And the reduction of the sonic boom intensity is more sensitive to the injection near the trailing edge than the suction near the leading edge. The results show that the optimized airfoils with the suction and injection have benefits in both sonic boom reduction and wave drag reduction. The effects of the suction and injection location, the suction and injection slot size, the mass flow rate and the attack angle on the ground boom signature and drag coefficient are studied in detail. The diamond and NACA0008 airfoils are adopted as the baseline airfoil to verify the capability of the proposed design method. To make sure of a zero net mass flux flow control, the mass flow sucked in near the leading edge is equal to the mass flow injected near the trailing edge. This paper provides a novel concept for supersonic aircraft to reduce the sonic boom and drag coefficient, wherein a suction slot near the leading edge and an injection slot near the trailing edge on the airfoil suction surface are opened. In case you face any issues setting up or running the simulation, refer to the corresponding initial and final Case and Data files.Sonic boom reduction has been an urgent need for the development of future supersonic transport, because of the heavy damage of noise pollution. Follow the instructions below to set up this simulation in Ansys Fluent starting with the Mesh file. Setupĭownload the Mesh file needed for setting up the simulation and the associated Case & Data files here.
Also, you will learn the characteristics of the subsonic and supersonic flows in which there are different types of shock waves.
SUPERSONIC AIRFOIL HOW TO
In this simulation example, we will investigate the features and characteristics of a flow over a NACA 0012 2D airfoil as it moves through different flow regimes as the Mach number varies from 0.6 to 1.2.įrom this example, you will find out how to simulate a compressible flow using Fluent. One was the Concorde and the other was the Tupolev Tu-144. So far, there were only two supersonic airliners that operated commercially. For instance, the cruise speed of large commercial jet airliners lies in the transonic regime. These regimes are incompressible, compressible subsonic, transonic and supersonic. Based on the magnitude of the Mach number, the flow around the wings will fall into one of the four flow regimes.
An aircraft moves at different speeds during different stages of a flight.
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