Thrust (T)

Thrust << refers to the force generated by the powerplant; it is equal to the Drag Polar at steady level flight; it is affected by the Weight (W) and the Lift (L)/Drag Polar Ratio of the aircraft general equation ;; $T=D\text{ @ steady level flight unaccelerated flight}=\frac{W}{\frac{L}{D}}=\frac{W}{\frac{C_l}{C_d}}$

Minimum Thrust Required << refers to the minimum amount of powerplant output required to Lift (L) the aircraft regardless of velocity achieved coefficient relations;; $C_{d0}=C_{di}$, $C_l=\sqrt{\frac{C_{d0}}{k}}$

$V\text{ @ }{T}_{r-min}$ >> $\sqrt{\frac{2W}{\rho s\sqrt{\frac{C_{d0}}{k}}}}$

$V$ @ $T_a$ >> $\sqrt{\frac{\rho T_a\pm \sqrt{T_r^2+4(C_{d0}k(W^2))}}{s{C}_{d0}}}$