Re: R: [問題]同軸反轉螺旋槳 (代po)消失
缺乏mi-6的資料
為估計垂直爬升時,短翼會造成多少主旋翼升力損失
改拿ch-47和v-22來估計
ch-47和v-22都是雙主旋翼
ch-47發動機最大功率3529kW *2
v-22發動機最大功率4590kW *2
ch-47的Maximum takeoff weight是50000 lb
v-22的Maximum vertical takeoff weight是52600 lb
(50000*4590/3529-52600)/52600=0.23636
所以v-22的短翼會造成23.636%主旋翼升力損失?
那麼高,難怪mi-6之後的運輸直昇機都不裝短翼
這樣估計法還算能參考嗎?
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