Study on a Rapid Aerodynamic Optimization Method of Flying Wing Aircraft for Conceptual Design

Table 2

Relative error between the results output by the surrogate model and the results calculated by the vortex lattice method.

Variable	Average error	Maximum error	Square root of error	squared
	0.01849	0.11353	0.0282	0.98714
	0.00722	0.03325	0.00988	0.99815
	0.00414	0.02158	0.00601	0.99934