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hMaxEng=19.5, -- maximum operating altitude for the engine in km -- typically higher than service ceiling of the aircraft
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dcx_eng=0.0114, -- drag coefficient for the engine -- no correlation found -- most common values are 0.0085 and 0.0144
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cemax=0.13, -- kg / sec - fuel consumption for a single engine in dry configuration
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cefor=0.13, -- kg / sec - fuel consumption for a single engine in afterburner configuration
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cemax=0.097, -- kg / sec - fuel consumption for a single engine in dry configuration
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cefor=0.097, -- kg / sec - fuel consumption for a single engine in afterburner configuration
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dpdh_m=1800, -- altitude coefficient for max thrust -- altitude effects to thrust -- The best recommendation at this point is to start with these values between 2000 and 3000 and adjust as needed after initial flight testing
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dpdh_f=1800, -- altitude coefficient for AB thrust ???? or altitude effects to fuel rate -- The best recommendation at this point is to start with these values between 2000 and 3000 and adjust as needed after initial flight testing
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table_data= {
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-- Pmax - total thrust in Newtons (kN * 1000) for all engines
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-- Pfor - total thrust in Newtons (kN * 1000) for all engines
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