rtfm
Well-Known Member
Hi,
It occurred to me that the size of the h-stab must bear an inverse relationship with the degree of auto stability of the wing. Is this correct?
In the extreme case of a fully auto stable wing we have no need of a h-stab at all. These are the flying planks of the world. At the other extreme, we have planes which use airfoils with extreme lift and extreme pitching moments. These aircraft need correspondingly large h-stabs.
Somewhere in between must exist aircraft with very low pitching moment airfoils (eg: NACA 23012, NACA747a315) which require relatively small h-stabs. Is this reasoning correct?
Duncan
It occurred to me that the size of the h-stab must bear an inverse relationship with the degree of auto stability of the wing. Is this correct?
In the extreme case of a fully auto stable wing we have no need of a h-stab at all. These are the flying planks of the world. At the other extreme, we have planes which use airfoils with extreme lift and extreme pitching moments. These aircraft need correspondingly large h-stabs.
Somewhere in between must exist aircraft with very low pitching moment airfoils (eg: NACA 23012, NACA747a315) which require relatively small h-stabs. Is this reasoning correct?
Duncan
