GT400

I think I get it now. 171,000kg is total limit for wing loads of Su-27S/Sk. I also forgot to remember as you increase altitude, air density decreases. Thank you Yo-Yo.

So how is permissible clmax of 1.6 different than clmax of 1.85? When the Su-27sk flight manual book 1 says 171,000kg is the max allowed static force put on the wing under mach .85, which clmax are they using to get that figure? Also in flight manual book 2 (again apologies in that I cannot read Cyrillic) in the first column it lists at mach .5 a clmax of 1.85 at 24 AOA and then under that in a second column also at mach .5 a clmax of 1.61 at 20AOA ? Is this the permissible clmax here? If using permissible clmax 1.6 in equation I get: (I figured for sea level and not 200 meters as TsAGI em chart) lift = 1/2*v^2*reference wing area*air density *cl lift = 1/2* 170m/s^2*62*1.225*1.6 lift= 1755964/9.81=178,997 and if using clmax of 1.85 in equation I get 206,965 neither of those numbers at mach .5 (170m/s at sl) get you to the 171,000kg. What am I doing wrong here?

I have a few questions about Su-27, and my apologies in that I cannot understand Cyrillic. But in TsAGI Su-27S paper, what does 1.6, 1.08, 1.4 numbers represent for Su-27, F-15, F-16? Also, so once Su-27S and SK are are equal or less than 19,000kg they can both pull 9G? 171000/9=19000kg and as long as it's less than mach .85? Lastly, I get it that in the TsAGI report it lists 18920kg as design flight mass at 50% fuel reserve, but does any one know the exact amount of fuel that is and the Su-27S operating weight? (easier to write it as operating weight?+fuel?= 18920kg) Thank you.

This USMC pilot talks about fighting the F-14D, and I think he is flying Lot 11 Hornets (non uprated engine). So the Hornet is not a slouch in a dogfight. https://hushkit.net/2020/03/16/flying-fighting-in-the-f-a-18-hornet-interview-with-a-usmc-hornet-veteran/