The Wing weight function¶
The Wing weight function of Forrester et al. (2008) is a recurrent test case for modeling purpose and sensitivity analysis in aerospace context. This function is extracted and adapted from the Raymer handbook for aircraft design. It is representative of a Cessna C172 Skyhawk wing aircraft. It depends on the wing area, the weight of fuel in the wing, the aspect ratio, the quarter-chord sweep angle, the dynamic pressure at cruise, the taper ratio, the airfoil thickness to chord ratio, the ultimate load factor, the flight design gross weight and the paint weight.
![use case geometry](../_images/wingweight.png)
The function is defined as follows:
with:
, the wing area (ft^2)
, the weight of fuel in the wing (lb)
, the aspect ratio (-)
, the quarter-chord sweep angle (deg)
, the dynamic pressure at cruise (lb/ft^2)
, the taper ratio (-)
, the airfoil thickness to chord ratio (-)
, the ultimate load factor (-)
, the flight design gross weight (lb)
, the paint weight (lb/ft^2)
We assume that the input variables are independent.
References¶
Forrester, A., Sobester, A., & Keane, A. (2008). Engineering design via surrogate modelling: a practical guide. Wiley.
Moon, H., Dean, A. M., & Santner, T. J. (2012). Two-stage sensitivity-based group screening in computer experiments. Technometrics, 54(4), 376-387.
Raymer D.P. (2018). Aircraft Design: a conceptual approach. American Institute of Aeronautics and Astronautics.
Load the use case¶
We can load this model from the use cases module as follows:
>>> from openturns.usecases import wingweight_function
>>> # Load the Wing weight use case
>>> ww = wingweight_function.WingWeightModel()
API documentation¶
See WingWeightModel
.