Numerical Investigation on the Drags Trait of a Supersonic Inlet Curved Duct Near the Exit
The matching design of thrust and drag is the core issue in the design of air-breathing vehicles.In order to obtain the drag trait of the inlet and reduce the interior drag,and then improve the overall performance of the air-breathing vehicles,a study on the cold-flow drag trait of a supersonic,twin-duct inlet is conducted with a CFD method.By comparing the flow characteristics and drag trait of the inlets with different length,turning angle,divergence ratio of the curved ducts,drag allocation proportion of different parts of the inlet is acquired and effects of the geometric parameters on the flow structure and drag are attained.Results indicate that a flow separation will probably generate in the curved duct of a twin-duct inlet at a cold-flow condition,which results in a large loss of the flow.It is noted that the drag of the curved duct accounts for majority of the entire inlet when there is no spilled flow.The drag of the curved duct can be reduced by decreasing the turning angle or increasing the divergence ratio of the curved duct.However,due to the interrelationship between the curved ducts'length and turning radius,the drag of the curved duct firstly reduces and then turns to rising with the increment of the curved ducts'length at a fixed design condition.
supersonic inletdragcurved ductloss of the flowseparation
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