lrn1007 (lrn1007-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: lrn1007 (lrn1007-il) Reynolds number: 50,000 Max Cl/Cd: 35.74 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-lrn1007-il-50000-n5.txt Download as CSV file: xf-lrn1007-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: lrn1007
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.2482 0.11420 0.10776 -0.0513 0.9665 0.0355
-8.000 -0.2489 0.11317 0.10677 -0.0518 0.9626 0.0360
-7.750 -0.2509 0.11261 0.10625 -0.0526 0.9584 0.0364
-7.500 -0.2448 0.11116 0.10483 -0.0555 0.9549 0.0367
-7.250 -0.2404 0.11067 0.10434 -0.0589 0.9507 0.0370
-7.000 -0.2345 0.10946 0.10314 -0.0617 0.9467 0.0371
-6.750 -0.2306 0.10232 0.09608 -0.0565 0.9460 0.0386
-6.500 -0.2234 0.09877 0.09253 -0.0562 0.9437 0.0405
-6.250 -0.2123 0.09586 0.08963 -0.0583 0.9412 0.0421
-6.000 -0.2112 0.09399 0.08778 -0.0582 0.9377 0.0435
-5.750 -0.2050 0.09187 0.08568 -0.0594 0.9343 0.0453
-5.500 -0.1911 0.08956 0.08335 -0.0628 0.9311 0.0475
-5.250 -0.1653 0.08802 0.08171 -0.0706 0.9278 0.0498
-5.000 -0.1474 0.08747 0.08103 -0.0758 0.9235 0.0504
-4.750 -0.1476 0.08250 0.07621 -0.0724 0.9212 0.0519
-4.500 -0.1379 0.07902 0.07273 -0.0720 0.9186 0.0549
-4.250 -0.1143 0.07598 0.06950 -0.0760 0.9160 0.0589
-4.000 -0.0795 0.07519 0.06843 -0.0838 0.9120 0.0637
-3.750 -0.0703 0.07123 0.06455 -0.0834 0.9089 0.0657
-3.500 -0.0533 0.06805 0.06134 -0.0844 0.9059 0.0712
-3.000 0.0047 0.06260 0.05562 -0.0924 0.8998 0.0872
-2.750 0.0282 0.05995 0.05287 -0.0948 0.8960 0.0959
-2.500 0.0580 0.05734 0.05010 -0.0982 0.8928 0.1129
-2.250 0.0909 0.05453 0.04714 -0.1023 0.8902 0.1413
-1.750 0.1265 0.04937 0.04204 -0.1035 0.8828 0.2482
-1.500 0.1559 0.04725 0.03982 -0.1055 0.8796 0.2856
-1.250 0.1950 0.04504 0.03744 -0.1088 0.8771 0.3030
-1.000 0.2362 0.04354 0.03554 -0.1126 0.8738 0.2933
-0.750 0.2743 0.04244 0.03392 -0.1152 0.8693 0.2628
-0.500 0.3230 0.04231 0.03301 -0.1177 0.8656 0.1824
-0.250 0.3668 0.04213 0.03230 -0.1188 0.8626 0.1244
0.000 0.3904 0.04231 0.03209 -0.1170 0.8564 0.0926
0.250 0.4241 0.04161 0.03114 -0.1173 0.8523 0.0689
0.500 0.4625 0.04166 0.03074 -0.1177 0.8489 0.0511
0.750 0.4825 0.04076 0.02978 -0.1168 0.8424 0.0455
1.000 0.5165 0.04076 0.02941 -0.1169 0.8379 0.0376
1.250 0.5462 0.03996 0.02844 -0.1171 0.8329 0.0354
1.500 0.5741 0.03968 0.02790 -0.1167 0.8269 0.0361
1.750 0.6110 0.03922 0.02722 -0.1178 0.8231 0.0377
2.000 0.6324 0.03905 0.02691 -0.1170 0.8154 0.0391
2.250 0.6684 0.03883 0.02645 -0.1182 0.8107 0.0386
2.500 0.6912 0.03899 0.02641 -0.1176 0.8026 0.0396
2.750 0.7270 0.03894 0.02609 -0.1188 0.7973 0.0490
3.000 0.7466 0.03764 0.02646 -0.1179 0.7889 1.0000
3.250 0.7804 0.03798 0.02627 -0.1185 0.7834 1.0000
3.500 0.7979 0.03858 0.02664 -0.1171 0.7731 1.0000
3.750 0.8204 0.03905 0.02698 -0.1165 0.7640 1.0000
4.000 0.8524 0.03926 0.02713 -0.1171 0.7571 1.0000
4.250 0.8702 0.03975 0.02763 -0.1158 0.7459 1.0000
4.500 0.8898 0.04017 0.02808 -0.1148 0.7349 1.0000
4.750 0.9115 0.04047 0.02847 -0.1140 0.7244 1.0000
5.000 0.9438 0.04034 0.02841 -0.1144 0.7166 1.0000
5.250 0.9618 0.04062 0.02878 -0.1131 0.7040 1.0000
5.500 0.9808 0.04080 0.02907 -0.1119 0.6910 1.0000
5.750 1.0013 0.04087 0.02929 -0.1107 0.6779 1.0000
6.000 1.0237 0.04081 0.02941 -0.1097 0.6649 1.0000
6.250 1.0473 0.04064 0.02946 -0.1086 0.6517 1.0000
6.500 1.0724 0.04031 0.02942 -0.1076 0.6383 1.0000
6.750 1.0984 0.03981 0.02930 -0.1063 0.6242 1.0000
7.000 1.1253 0.03914 0.02912 -0.1047 0.6094 1.0000
7.250 1.1589 0.03243 0.02122 -0.0946 0.3924 1.0000
7.500 1.1479 0.03515 0.02262 -0.0898 0.2431 1.0000
7.750 1.1421 0.03812 0.02478 -0.0867 0.1325 1.0000
8.000 1.1301 0.04234 0.02774 -0.0835 0.0172 1.0000
8.250 1.1369 0.04478 0.03033 -0.0813 0.0116 1.0000
8.500 1.1458 0.04695 0.03287 -0.0794 0.0093 1.0000
8.750 1.1524 0.04941 0.03567 -0.0775 0.0079 1.0000
9.000 1.1576 0.05200 0.03862 -0.0756 0.0076 1.0000
9.250 1.1615 0.05474 0.04172 -0.0737 0.0075 1.0000
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Polar data table (+)
Polar graphs
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