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ride-wave intakes

rousseau

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Greetings:

Here is a complicated question share with us.

We've known that shock wave caused by upside board of F-22's inlet covering inlet jaw lip make a low velocity of air flow and high air press inside inlet antrum, which means this atitude of air flow just in what jet engine needed in supersonic working. Otherwisem, the shockwave also lead to a downward flow, which means a little bite additional lift.

That's is a sort of inlet we call it ride wave inlet

Now, the question our faced is why the DSI also be called ride wave inlet?
How the air flow caused by bump cover the inlet, as the shape of shock wave caused by bump is subulate wherease the inlet is multi-side shape?
 

Sundog

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I'm not quite sure what you're asking. The F-22 and F-23 have 3D oblique shocks. That means there is an extra sweep in the mach angle, as opposed to a 2D inlet like on the F-14 and F-15, which aids pressure recovery even more.

When you say DIS, are you referring to the inlet like on the F-35? The bump in front of the F-35 inlet is designed to "part" the boundary layer and keep it from entering the inlet which makes it easier to make it stealthy since you don't have to make a boundary layer splitter at the inlet and probably makes construction easier. At supersonic speeds I would think it would act just like a half shock cone inlet.
 

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