User:Readro/Aero definitions

$p = ρ R T$

$U_{\infty}=M_{\infty}a=M_{\infty} \sqrt{\gamma R T}$

$Re = \frac{\rho U_{\infty} L}{\mu}$

$T_{0}=T+\frac{u^2}{C_{p}}$

$T_0 = T \left( 1 + \frac{\gamma -1}{2} M_{\infty}^2 \right)$

$y^+ = \frac{\rho y u^*}{\mu}$

$u^* = \sqrt{\frac{\tau_w}{\rho}}$

$\tau_w = \frac{1}{2} C_f \rho u^2$

$C_f = 0.027 Re^{- \frac{1}{7}} \bar c$

$\delta = 0.14 Re^{- \frac{1}{7}} \bar c$

where c is the M.A.C.

$\frac{\mu}{\mu_{0}} = \left( \frac{T}{T_0} \right)^{\frac{3}{2}} \frac{T_0 + 110}{T + 110}$

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