What is the typical conversion factor between a commercial aircraft’s PWR setting and the N1 produced by it?
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None of this is correct. If you don’t know the answer, it helps to just let others who do know respond instead of adding confusion.
N1 refers to the low speed spool/rotational speed of the low pressure compressor and turbine, as well as the fan. Think of it as an RPM gauge in your car, in the most bare bones terms. For IF purposes, power is how much power, or thrust, is being generated on a scale of 0-100% of the engine’s maximum output.
N1 ranges from mid-70s to high-90s for your average takeoff, with some widebodies occasionally requiring over 100% N1. Aircraft weight, airport environments (including temp. and altitude primarily), and other factors influence how much N1, and subsequently how much thrust is needed for takeoff.
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sorry, i didn’t know
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Thanks for this information appreciate it
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i thought i read somewhere that the minimum legal thrust for takeoff is 80 n1
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It differs by engine, aircraft weight, airport elevation, ambient temperature etc. But here I have a chart of engine thrust vs %N1 of CFM-7B27, a typical engine in narrow-bodies, that suggests that the relationship is exponential (source).
There is no single guide nor equation for all variables I mentioned above (engine, aircraft weight, airport elevation, temperature) especially for IF purposes, but the good news is you just gave me a thread idea.
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In IF it operates on approximately a doubling in throttle is a 4x in thrust, it’s fit somewhat around y=2^x with some variance between aircraft.
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