- #1

kevcrl

- 2

- 2

I'd like to talk about the formulas about aerodynamic calculations.

Let's focus on the lift force.

As you may know, the lift force is computed as

The CL coefficient can be decomposed with a Taylor serie which is

Now, each coefficient can be rewritten in detail as:

As we can see, there is a ratio of of the horizontal surface tail to the wing surface Sh/S

However, how has this parameter to be used in case of a delta wing aircraft with no horizontal tail

Shall we do consider the Sh surface as zero ?

Thanks