I have some aerodynamics homework to finish up, and I am not really sure how to do one part.(adsbygoogle = window.adsbygoogle || []).push({});

Question is: What is the corresponding zero Mach number lift coefficient

I can't find an equation in my book or anything. Can someone maybe shed some light?

My first two questions were to find freestream Mach number and wing lift coefficient if that helps any.

Thanks.

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# Zero Mach number lift coefficient

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