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Performance correction formula N eo = N e x K H N eo = Performance in reference to normal operating conditions (sea level, temperature 25°C) in kW.
N e = Performance measured on the output dynamometer in kW.
K H = Correction factor n
Correction factor (K H ): n
Determine air pressure and altitude of the test location Use subsequent altitude correction Table to correct air pressure Determine air-charge temperature. Using these values and the subsequent performance correction Table read off the correction factor (K H ) Altitude correction If the air pressure is read off in relation to the sea level (weather station), the following air pressure in the Performance correction Table m hPa m hPa m hPa m hPa m hPa 0 0 300 36 600 69 900 104 2000 221 50 6 350 41 6350 75 950 109 2100 230 100 12 400 46 700 81 1000 115 2200 239 150 18 450 52 750 86 1100 126 2300 250 200 24 500 58 800 92 1200 137 2400 259 250 30 550 63 850 98 1300 148 2500 268 hPa 5°C 10°C 15°C 20°C 25°C 30°C 35°C 40°C 45°C 50°C 1040 0.9111 0.9194 0.9277 0.9358 0.9 0.9 0.99 0.9678 0.9756 0.9833 0.9910 1035 0.9155 0.9239 0.9321 0.9403 0.9645 0.9565 0.9645 0.9724 0.9803 0.9881 0.9958 1030 0.9200 0.9284 0.9367 0.9449 0.9531 0.992 0.992 0.9772 0.99291 0.9929 1.0007 1025 0.9245 0.9329 0.9412 0.9495 0.9577 0.9899 0.9 0.9899 0.99 0.9977 1.0056 1020 0.9290 0.9375 0.9458 0.9542 0.9624 1.0026 0.9947 0.9947 0.9947 1.0026 1.0105 1015 0.9336 0.9421 0.9505 0.999 0.9672 0.9754 0.9835 0.9916 0.9996 1.0076 1.0155 1010 0.9382 0.9467 0.9552 0.9636 0.9 0.9552 0.9884 0.95 1.0126 1.0126 1.0205 1005 0.9428 0.9514 0.9600 0.9684 0.9768 0.951 0.9933 1.0015 6000.96 1.0176 1.0256 1000 0.9476 0.9562 0.9648 0.9732 0.9817 0.96480 0.973 1.0065 1.0146 1.0227 1.0307 995 0.9523 0.9610 0.96100.96 02781 0.9866 0.9950 1.0033 1.0115 1.0197 1.0278 1.0359
2004 Mercedes-Benz ML350 1998-2005 GENINFO Overall vehicle - 163 Chassis
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