thank to all for response.

wing is 3.2 metre.

i look at polar for airfoils, root is hq2.5/9 then next section hq2.5/8.5 then next section is hq2.5/8 then tip is hq2.5/7.5

and i think hq2.5/8 and hq2.5/7.5 need a bit of washout so to stall them later than root.

but what if i desing lift distribution eliptical and c/l stronger at tip?

i mean local c/l much higher at tip maybe no washout needed then?

so even though thinner tip airfoils produce less lift washout not needed because I desing wing with much higher local c/l at tip to compsate?


thanks.



Hai Dang