The basic model described above has two restrictions. First, its
domain of accuracy is small; it cannot correctly model flight
conditions such as advanced stall and spins. Second, the basic model
cannot simulate the many subtle effects (for example, how
changes with angle of attack), because there are no
terms to account for such effects. These subtle effects are small
compared to lift versus angle of attack, and are not easy to
calculate, and so they are not used in the basic model. However,
these effects are real, and not accounting for them limits the maximum
accuracy of the model.
The obvious solution to these problems is to use more terms in the polynomials. More terms can make the model more accurate, as well as increase its domain of accuracy. Unfortunately, as more terms are added, it becomes increasingly difficult to calculate the coefficients. Therefore, complex polynomial models use numerical methods of parameter fitting to determine the coefficients. The parameter fitting methods rely on test data (either from flight tests or wind tunnel tests).
However, before parameter fitting, one must choose which parameters
are needed. One possibility is to use brute force; simply choosing
any desired polynomial terms, and letting the optimizer decide whether
there is any relationship of significance. This method is problematic
for two reasons. First, the memory and computer time required for
this is very large. Second, as the degree of the polynomials
increase, it becomes increasingly likely that two terms may be nearly
linearly dependent with the given test data
.
This creates an ill-conditioned problem.
Reference 12 presents a method to determine a set of
terms that are not linearly dependent. It derives a method of
selecting terms that are orthogonal to each other based on the given
data set. (Suppose there are N data points, with each data point
listing the force F and the state variables
at some
point in time. Two terms
and
are orthogonal if