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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).



Question ID - 155592 | SaraNextGen Top Answer

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).

1 Answer
127 votes
Answer Key / Explanation : (0.270 to 0.280) -

0.270 to 0.280

127 votes


127