将高速滑体制成相似的机翼模型，进行风洞试验，即可测定滑坡凌空飞行的空气动力学参数，从而计算大型高速滑坡凌空飞行的空气动力升力、飞行速度和飞行距离等。

If we make a wing model which is similar to sliding mass, we can determine aerodynamic parameters by the wind tunnel testing and thus calculate the lift.

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通过调整襟翼，可使翼帆低端的升力达到最高，从而产生大量动力，并减少上端升力，产生较少的侧向力。

The flaps can be adjusted to maximize lift on the wing's lower end, generating a lot of power, and to reduce it up top, generating less heeling, or tipping, force.

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在空气动力学上，升力是重量，推力和阻力(空气阻力)的相关的函数。

In aerodynamic terms, lift is a function of weight, thrust and drag (air resistance).

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