gemseo.problems.uncertainty.wing_weight package#

The wing weight problem.

The function of the wing weight problem

\[f(A,\ell,\Lambda,N_z,q,S_w,t_c,W_{dg},W_{fw},W_p) = 0.036 S_w^{0.758} W_{fw}^{0.0035} \left(\frac{A}{\cos(\pi / 180 \Lambda)^2}\right)^{0.6} q^{0.006} \ell^{0.04} \left(\frac{100 t_c}{\cos(\pi / 180 \Lambda)}\right)^{-0.3} (N_z W_{dg})^{0.49} + S_w W_p\]

is commonly studied through the random input vector \(W_w=f(A,\ell,\Lambda,N_z,q,S_w,t_c,W_{dg},W_{fw},W_p)\) whose components are independent random variables uniformly distributed:

  • \(A\sim\mathcal{U}([6.0, 10.0])\), the aspect ratio (-),

  • \(\ell\sim\mathcal{U}([0.5, 1.0])\), the taper ratio (-),

  • \(\Lambda\sim\mathcal{U}([-10.0, 10.0])\), the quarter-chord sweep angle (deg),

  • \(N_z\sim\mathcal{U}([2.5, 6.0])\), the ultimate load factor (-),

  • \(q\sim\mathcal{U}([16, 45])\), the dynamic pressure at cruise (lb/ft^2),

  • \(S_w\sim\mathcal{U}([150, 200])\), the wing area (ft^2),

  • \(t_c\sim\mathcal{U}([0.08, 0.18])\), the airfoil thickness to chord ratio (-),

  • \(W_{dg}\sim\mathcal{U}([1700, 2500])\), the flight design gross weight (lb),

  • \(W_{fw}\sim\mathcal{U}([220, 300])\), the weight of fuel in the wing (lb),

  • \(W_p\sim\mathcal{U}([0.025, 0.08])\), the paint weight (lb/ft^2).

The wing weight problem is presented in [FSK08] and the description given here is based on that of OpenTURNS.

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