I am using a GWA-1 airfoil. It's trailing edge is blunt, 1/2 inch thick.
Supposedly as the wing reaches it's stalling angle, a rotating horizontal
vortex develops along this trailing edge. The higher pressure on the
underside and lower pressure on the top forces the vortex to rotate such
that i
The GAW-1 airfoil is a spin off from the first Supercritical airfoil
tested in flighton the Navy 2TC trainerand as I said in my eariler post
we used thickness of 0.075 at the trailing edge. Yours is slightly
thicker but should be O.K. This airfoil is also used on the very easy
wing and was shown t
Hi Harold,
Attempting to climb an aircraft at anything close to the stall is a mugs
game. Climb out at a safe 1.3 factor.
Unless you have a VP prop or a prop that is designed for very low speed
flight, it is probable that your prop will be producing very poor lift at
the speeds close to the stall
>
>Attempting to climb an aircraft at anything close to the stall is a mugs
>game. Climb out at a safe 1.3 factor.
>Pete
+
Unless I have obstacles to clear, and I seldom do, I climb out
at closer to 2.0. My rate of climb seems to remain the
sa
I will admit up front that I, like all of you, am getting older so sometimes
things may get a little fuzzy without taking the time to go back and check
things out. My memory of the GAW1 is that it had some sudden stall
characteristics. Dr Whitcomb developed the GAW 2 which had the same laminar
Yep Larry, I agree 100%, I should have said at least 1.3
Pete
>
>
> Unless I have obstacles to clear, and I seldom do, I climb out
> at closer to 2.0. My rate of climb seems to remain the
> same , within a couple hundred feet, from 70 to 110 mph.
> The higher speeds gives better visibility, be
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