Initially they added B to other countries because A wasn’t exported.
Why can’t Gaijin give APG-63/70 their real 2.5° beamwidth?
apologies, not really knowledgeable in radar info, what would that change exactly.
It will be a bit better in situations when two targets are near
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Angular resolution
Shouldn’t ingame F-15E have 229EEP engines? Their delivery started in 2010 and F-15E ingame is 2010+ version I suppose
Does EEP provide increased thrust over base line 229?
Nope
must have a lifetime of 5 minutes
Airflow would be problem too. At least for F-15 and F-16. Even GE-132 rated at 32000lbs chokes at low speed so thrust is limited until 0.4M
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F-14 had better intakes potential so probably theoretical 4.5 gen Tomcat would be fine.
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And IIRC that powerful F110 proposals are actually hybrids of CFM56 and YF120 named F110 to look like modification rather than new engine.
I could’ve sworn I read somewhere that it was proposed to use F110-GE-129 or the F110-GE-429 with thrust vectoring for the ASF-14 or the other one ST-21 (I pretty sure tho it was ASF-14 as that one focused on maneuverability)
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Than an F-15?
IIRC yes. It was initially built for TF-30 with bigger airflow than F100. And F-14 has reserve to almost 300lb/sec airflow.
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Don’t forget NASA’s F-15 STOL/MTD :)
I remembered a story from the 1970s.
At that time, the US Navy and Air Force were forced to use the F-100 engine as a common basis for the FX and VFAX. Pratt and Whitney asked the FX development office about the amount of airflow they would require for the F-15. They wanted an answer very quickly… because the Navy wanted the engine to have 256 lb/sec. It was clear to FX management that if they didn’t quickly provide the required airflow, they would lose the engine because it would be more suited to the Navy’s F-14. Fredd Rall, a very good engineer, was asked to estimate the required airflow. After a few minutes of thinking, he wrote the number 220 on a piece of paper. Pratt and Whitney was called and told that the airflow would be 220 lb/s. Pratt and Whitney built the engine according to this specification. Fredd Rall estimated the required amount of air very accurately; in the end, it was 224 lb/s. As a result, the Navy lost its engine for the F-14 and had to do with the TF-30 engine for a long time.
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I’m not sure what you mean by “despite being before F-15C production”. VTAS was tested on F-15A just like F-14A, it just wasn’t adopted
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