[aerohead]

With faster machine I was able to get the two new tables posted.Again,I'm placing all tables together up top @ #1 permalink.
*These are for wing/strut section 2-D flow, drag as a function of trailing edge truncation.
*The delta-C is a function of the entire wing chord,not just the trailing portion.
*The formula for calculating the new Cd is presented as a function of section thickness only.
*Any section which has it's maximum thickness at around 30% of chord is fair game.
*A sample calculation is presented for a 20.5% thickness G'o'ttingen airfoil.
*I've reversed the original table so as to always have the body attacking the air from left-to-right,as in the other tables.
--------------------------------------------------------------------------
*The second table is a drag curve calculated from the equation using the G'o'ttingen airfoil shown.
--------------------------------------------------------------------------
'WARNING Will Robinson!!!!!!!!!!!!!!'
Sections don't behave as streamline bodies or half-bodies.
*They suffer tremendous drag increase with a 'Kamm' truncation of any amount.
*It's better to pull the sides into a boat tail even if it's too steep.
*I've got another section table for this 'J',or Jaray-form section treatment in the works and will try for next Saturday to post.
*This research was conducted by K-Fachsenfeld at the FKFS (now Mercedes-Benz' wind tunnel) under the supervision of Kamm.
*Junkers did similar studies and I've got that to look at also.