Zero Mach number lift coefficient

AI Thread Summary
The discussion centers on determining the zero Mach number lift coefficient for an aerodynamics homework assignment. The user is struggling to find relevant equations in their textbook and seeks clarification on the relationship between zero Mach number and stagnation conditions, including temperature, pressure, and density. They mention needing to calculate the freestream Mach number and wing lift coefficient as part of their problem. Other participants inquire about the specific textbook being used to provide more targeted assistance. The conversation highlights the need for explicit formulas or guidance related to lift coefficients at zero Mach number.
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I have some aerodynamics homework to finish up, and I am not really sure how to do one part.

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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I believe the zero Mach number has to do with stagnation conditions at the T, P and density values, or whatever physical parameters go into the lift equation.

I am trying to find an explicit statement in my texts.

What textbook are you using?
 
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