
gta4 wrote:First thing first, Su-27 has only a usable Clmax of about 1.6.
1.83 is when tailing edge flaps are deployed (for low speed level flight)
I think Mach 0.5 is fast enough speed for dogfight TBH
gta4 wrote:F-15 also has a max Cl of about 1.6 (I can prove that with NASA test reports) and F-15 has lower wing loading, so F-15 has better Cl/wing loading ratio, which gives it a better instantaneous turn rate than Su-27. Surprise?![]()
TsAGI underestimated F-15's Cl to be 1.08 (rather than 1.6), which significantly underestimated F-15's instantaneous turn.
I dont think F-15 CL can reach 1.6 , it lacks most criteria for high CL value like LERX or LEF or Negative stability. CL of 1.6 looks like something belong to F-16 instead , and it only reach that vale below a certain G load


gta4 wrote:And again, in your figure Su-27 sustains a 20.8deg/sec in 18920kg flying weight, which is with 2000kg fuel
Their figure is taken when Su-27 is at 50% fuel IMHO
i concluded that from their ITR value
Lift = 1/2*V^2*reference wing area*air density *CL
Take for example when speed is mach 0.5 ( about 164 meters/sec) => CL is 1.85
air density at sea level is about 1.2kg/m3
Su-27 wing area is about 62m2
so total amount of lift is 1.85 * 1/2 * 1.2 * 164.8^2 * 62 = 1879085N
Su-27 empty weight is 16380 kg, max internal fuel is 9400 kg, Su-27 with 50% fuel will weight about 21080 kg
max G it can pull based on lift generated is 1879085/9.81/21080 =about 9G. That seem to fit with value in the graph