Recent content by Steven Que

You really enjoy your retire life. Congratulation!

good!!0.0

??????? Here. Many type of A6M fighter,trainer,and float version. Excited! include A7M.

Finally I found them on my old forum. Then I find them in a Russia webside.:shock:

Hello guys I ever find some 3-face pictures of A6M and have A7M too. They are looks so nice and detail. But I lose these pictures now:cry: Maybe I format my disk and forgot to save them... Someone will help me to find out them again? I sware I find them on a webside which is not...

nice file of this hand book8)

You can sit into the cockpit and take film. said "Hey~I kick the Nazi's ass!! wohoooo!!":D

Hey~so cool!!! very very good landing.

looks so nice8)

HI Peril, I wonder the coefficient of lift with NN-21 when AOA is 0 degree I can not find out the data from my program which have more than 300 airfoil's data But have no data of NN-21... Thanks

Hi Micdrow I like these data of aircraft because it is very detail. But in this forum I think P-39 may not popular aircraft for many members. No reply for these P-39 data still now. But I am sure someone like P-39 and they will amazing these data. good luck:)

They are looks so great!! Nice data Thanks:)

Thanks Now I have enough data to analyse use program with airfoil to get lift coefficient and use your data of center of gravity then use some equations to got some coefficient But I feel it is not easy to fly because it's cockpit is too simple then can not let pilot know the flying...

OK guys Maybe judge the issue that how to know the data or get it is difficulty Then I have some idea with these data they give me. ====find out aerodynamic center==== Assume the fuselage is not mention with whole aircraft's aerodynamic center (Actually it is not true for real aircraft)...

Hmm~Looks so great I know the aerodynamic center is at 0.25 camber of the airfioil many points link into a line(red line) is straight But...not 90 degree with the axis of fuselage are you sure the gravity of center is at the 0.25 camber of the airfoil of wing's root? I ever think if...