Jet Propulsion/Stage temperature ratio

Euler equation rewritten with fluid angles and mass flows

v₁ = u₁tan β_r1

v₂ = u₂tan β₂ = ωr₂ − u₂tan β_r2

$\frac{T_{t2}}{T_{t1}} = 1+ \frac{(\omega r_2)^2}{c_p T_{t1}} [1 - \frac {u_2} {\omega r_2} ( \tan \beta_{r2} + \frac {u_1 r_1}{u_2 r_2} \tan \beta_1 )]$

The blade speed dimensionless group:

$\frac{(\omega r_2)^2}{c_p T_{t1}}$