>That trailing edge cusp does several different things. the pitch moment >will be more negative >boundary layer separation will tend to stay closer to the trailing edge >coefficient of lift of the two different airfoils .... the same, but the >cusped airfoil will reach it >at lower angle of attack
>OK for a wing root but will be a poor choice for a control surface. >Aileron control forces will be high. It is a less than optimum choice for >an airfoil that is intended to be laminar over a wide range angle of >attack. Thank you - so nice to get a straight factual (informed) answer relative to what was asked. I have played with your 2D software and believe that you are strong on this topic - no debate with you on wing sedctions. Pity about the these effects - I has hoped to use the 15 % Ashok section as an outboard partner to the P51 Mustang section at the root. The P51 tip section looks really strange so I am back to the drawing boad. Someone posted a URL to a airfoil website (profilli) - it is real good and has many section - not your NACA 747A315 - I cannot find that at all - sods law. Your Airplane looks realy good but I can't help feeling that the nose is too long. Thanks again Ron _________________________________________________________________ Get rid of annoying pop-up ads with the new MSN Toolbar FREE! http://toolbar.msn.com/go/onm00200414ave/direct/01/
