EJ200 thrust vs. altitude

Hi folks,

I’m once again looking for some guidance/advice on a project I’m doing. Assuming a dry thrust of 17,500lbf and afterburning thrust of 27,000lbf for the EJ200, how would I be able to calculate (or estimate) the thrust output of the engine for all altitudes (sea level to say 50,000ft)? Essentially I am looking for T/T0 as a function of altitude. Are there any formulas or estimators that can be used to approximate thrust vs. altitude? I realize there are lots of factors (such as density, etc.) that come into play, but an estimator will do.

In addition, I am looking for a model for SFC as a function of power, speed & altitude for the same engine.

I would appreciate any and all the help I can get. Thanks in advance!