Andy Ross wrote:
Oh, I didn't include the surface.cpp patch in the diff file. I only mentioned it in the mail. For easier test I've enclosed the diff for wing.cpp and surface.cpp.Maik Justus wrote:Andy Ross wrote:As I read the code, you would get 1N of force per fuselage surfaceNo, it's 1 multiplied with 0.5f*rho*vel*vel*_c0.Heh, so it is. You'd think I'd remember this stuff better. Well, at least it's being checked in along with another potentially aircraft-breaking solver change. :)
I've changed as a test (not included to this diff) the surfaces generated by fuselages to be never in stall. Some aircrafts get the same solver results, most get similar solver results (delta < 1%) and the largest effect is on a4 and spitfireIIa (they seem to have (from a aerodynamically point of view) the largest fuselages. I've tested the a4 very short, it is still flyable. I would expect fuselages to be not in stall in most conditions, but this is only gut feeling. What do you think?
Maik
YASim.diff.gz
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