Originally Posted by
ASRAAMTOO
essentially Rate of turn is proportional to VSquared/load factor and Radius of turn is proportional to load factor/V.
Thanks A, Isn't it radius that has the squared relationship to velocity?
Could it be due to compressabiilty at the Mach numbers involved? ie. Compressibility = heat = greater kinematic viscosity = lower Reynolds number than expected for the increased velocity = lower C/L max at lower AoA for the airfoil?
ie If we assume the the F16 is at a Critical Angle Cat 1 at 198kt below doing 2.6G for min radius then 8/2.6 = 3.07 times increase in load factor at max rate/load factor so multiply by 1.61 to get the 8G Critical Cat 1 AoA velocity and we get 347kt where as the sea level plot shows it is tilted way back at 398knt doing 8G at its Cat 1 AoA.
Is Cat 1 not a fixed AoA but varies with velocity?
Why does the dog house tilt back like that? It seems to get more tilted at higher altitude Turn Performance plots as well. See 30,000ft below.
On to something here or still missing the bull?
30,000 ft