An aircraft is to be designed to ensure that it has enough excess power to achieve steady climb at flight path angle, $\gamma=10$ degrees, maintaining $\frac{C_{L}}{C_{D}}=10.0$. The numerical value of the thrust to weight ratio of the complete aircraft to meet the above requirement under standard atmospheric condition will be ______________$\quad$ (in three decimal place).
An aircraft is to be designed to ensure that it has enough excess power to achieve steady climb at flight path angle, $\gamma=10$ degrees, maintaining $\frac{C_{L}}{C_{D}}=10.0$. The numerical value of the thrust to weight ratio of the complete aircraft to meet the above requirement under standard atmospheric condition will be ______________$\quad$ (in three decimal place).