| 摘要 |
Aircraft having a lambda-box wing configuration, comprising a fuselage (1 ), a propulsion system (5), a first pair of swept-back airfoils (2), connected to the top forward portion of the fuselage (1 ), a second pair of swept-forward airfoils (3), connected to the lower rear portion of the fuselage (1 ) at a point of the said fuselage (1 ) aft of the connection of the swept-back airfoils (2), and a third pair of substantially vertical airfoils (4), the tips of the swept-forward airfoils (3) being connected to the lower side of the swept-back airfoils (2) at an intermediate point of the span of the said swept-back airfoils (2), by means of the substantially vertical airfoils (4), the swept-back airfoils (2) having a higher aspect ratio than that of the swept-forward airfoils (3), which makes the swept-back airfoils (2) have a reduced induced drag without penalizing the weight thereof.
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