So you're saying the F119 engine's nozzle shape will reduce the engine's thrust by 15-20%? Again, any sources or studies (or even forum posts from other websites) to back it up?
Because I feel like that number is being pulled out of thin air.
From hazy memory it seems 14-17 percent is the value I heard from an Indian source, but that could be reference to Russian(soviet?) experimenting with their own square nozzle. Maybe for F-22 the loss has been lowered through better design.