Truncated-wing wind-tunnel aircraft mock-up for tests in a tunnel (11) of width W, which comprises a fuselage (21), a truncated wing (25), the length L1 of which is less than the length L of a full-scale wing (23), and additional components in the rear part of the aircraft such as, in particular, a horizontal tail stabilizer, which produces the same slipstream reaching said additional components as in a full-scale mock-up. The form of said truncated wing (25) may be designed so as to have a lift distribution (35) that is similar to the lift distribution (37) of a full-scale wing (23) along at least the maximum length L2 on the axis Y of any additional component in the rear part of the aircraft. The invention also relates to a method for designing said truncated wing (25).
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