WORTMANN FX 74-080 (fx74080-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: WORTMANN FX 74-080 (fx74080-il) Reynolds number: 200,000 Max Cl/Cd: 80.33 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx74080-il-200000.txt Download as CSV file: xf-fx74080-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: WORTMANN FX 74-080
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.3320 0.12308 0.11965 -0.0431 1.0000 0.0169
-10.250 -0.3545 0.12402 0.12073 -0.0368 1.0000 0.0168
-10.000 -0.3588 0.12232 0.11906 -0.0357 0.9991 0.0173
-9.750 -0.3454 0.11825 0.11499 -0.0395 0.9963 0.0178
-9.500 -0.3328 0.11439 0.11112 -0.0431 0.9933 0.0185
-9.250 -0.3196 0.11053 0.10726 -0.0469 0.9904 0.0191
-9.000 -0.3064 0.10664 0.10336 -0.0508 0.9875 0.0200
-8.750 -0.2942 0.10303 0.09975 -0.0544 0.9835 0.0206
-8.500 -0.2798 0.09944 0.09616 -0.0592 0.9800 0.0217
-8.250 -0.2635 0.09606 0.09278 -0.0656 0.9771 0.0225
-8.000 -0.2535 0.09336 0.09010 -0.0707 0.9712 0.0229
-7.750 -0.2386 0.09002 0.08670 -0.0767 0.9666 0.0232
-7.500 -0.2178 0.08569 0.08236 -0.0841 0.9637 0.0233
-7.250 -0.2066 0.08232 0.07899 -0.0889 0.9570 0.0234
-7.000 -0.1848 0.07796 0.07458 -0.0957 0.9536 0.0234
-6.750 -0.1602 0.07220 0.06877 -0.1038 0.9513 0.0237
-6.500 -0.1624 0.06682 0.06344 -0.1022 0.9474 0.0252
-6.250 -0.1504 0.06368 0.06028 -0.1037 0.9427 0.0262
-6.000 -0.1271 0.05969 0.05622 -0.1087 0.9399 0.0287
-5.750 -0.0949 0.05515 0.05155 -0.1163 0.9377 0.0326
-5.500 -0.0778 0.05310 0.04929 -0.1187 0.9303 0.0354
-5.250 -0.0531 0.04779 0.04370 -0.1235 0.9266 0.0373
-5.000 -0.0315 0.04415 0.04007 -0.1256 0.9248 0.0394
-4.750 -0.0236 0.04228 0.03812 -0.1239 0.9187 0.0417
-4.500 0.0011 0.03955 0.03516 -0.1254 0.9150 0.0460
-4.250 0.0345 0.03598 0.03108 -0.1284 0.9124 0.0512
-4.000 0.0634 0.03312 0.02816 -0.1305 0.9108 0.0554
-3.500 0.0974 0.02966 0.02419 -0.1281 0.9010 0.0681
-3.250 0.1292 0.02756 0.02180 -0.1297 0.8991 0.0812
-3.000 0.1622 0.02573 0.01974 -0.1314 0.8975 0.0975
-2.750 0.1820 0.02290 0.01603 -0.1259 0.8914 0.0347
-2.500 0.2109 0.02073 0.01351 -0.1259 0.8886 0.0319
-2.250 0.2447 0.01976 0.01222 -0.1266 0.8866 0.0355
-2.000 0.2778 0.01815 0.01042 -0.1273 0.8850 0.0377
-1.750 0.2937 0.01755 0.00981 -0.1251 0.8800 0.0389
-1.500 0.3162 0.01694 0.00915 -0.1241 0.8757 0.0441
-1.250 0.3460 0.01602 0.00832 -0.1245 0.8733 0.0927
-1.000 0.3877 0.01340 0.00819 -0.1268 0.8732 1.0000
-0.750 0.4204 0.01343 0.00800 -0.1279 0.8712 1.0000
-0.500 0.4310 0.01391 0.00838 -0.1250 0.8641 1.0000
-0.250 0.4598 0.01400 0.00834 -0.1253 0.8609 1.0000
0.000 0.4927 0.01403 0.00823 -0.1265 0.8587 1.0000
0.250 0.5098 0.01443 0.00856 -0.1247 0.8528 1.0000
0.500 0.5347 0.01462 0.00869 -0.1244 0.8485 1.0000
0.750 0.5664 0.01467 0.00868 -0.1253 0.8460 1.0000
1.000 0.5999 0.01470 0.00866 -0.1264 0.8441 1.0000
1.250 0.6104 0.01527 0.00926 -0.1236 0.8358 1.0000
1.500 0.6415 0.01533 0.00930 -0.1243 0.8331 1.0000
1.750 0.6749 0.01534 0.00931 -0.1254 0.8311 1.0000
2.000 0.6866 0.01593 0.00992 -0.1228 0.8229 1.0000
2.250 0.7177 0.01597 0.01000 -0.1235 0.8200 1.0000
2.500 0.7513 0.01596 0.01003 -0.1246 0.8179 1.0000
2.750 0.7629 0.01658 0.01079 -0.1220 0.8094 1.0000
3.000 0.7948 0.01657 0.01086 -0.1228 0.8065 1.0000
3.250 0.8289 0.01652 0.01092 -0.1239 0.8044 1.0000
3.500 0.8413 0.01709 0.01160 -0.1214 0.7953 1.0000
3.750 0.8842 0.01571 0.01035 -0.1224 0.7849 1.0000
4.000 0.9342 0.01163 0.00629 -0.1212 0.7373 1.0000
4.250 0.9186 0.01156 0.00477 -0.1096 0.4651 1.0000
4.500 0.8891 0.01443 0.00607 -0.0996 0.1936 1.0000
4.750 0.8777 0.01670 0.00743 -0.0929 0.0383 1.0000
5.000 0.8892 0.01757 0.00846 -0.0898 0.0313 1.0000
5.250 0.8970 0.01868 0.00969 -0.0861 0.0277 1.0000
5.500 0.9009 0.02014 0.01123 -0.0820 0.0262 1.0000
5.750 0.9092 0.02186 0.01298 -0.0787 0.0251 1.0000
6.000 0.9290 0.02315 0.01433 -0.0773 0.0244 1.0000
6.250 0.9545 0.02447 0.01573 -0.0766 0.0208 1.0000
6.500 1.0153 0.02804 0.01947 -0.0815 0.0222 1.0000
10.250 1.0322 0.07189 0.06805 -0.0356 0.0356 1.0000
10.500 1.0091 0.07615 0.07247 -0.0336 0.0356 1.0000
10.750 0.9860 0.08097 0.07743 -0.0324 0.0358 1.0000
11.000 0.9635 0.08615 0.08273 -0.0320 0.0360 1.0000
11.250 0.9421 0.09155 0.08824 -0.0323 0.0363 1.0000
11.500 0.9202 0.09723 0.09402 -0.0332 0.0365 1.0000
11.750 0.8950 0.10255 0.09945 -0.0347 0.0368 1.0000
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Polar data table (+)
Polar graphs
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