E62 (5.62%) (e62-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: E62 (5.62%) (e62-il) Reynolds number: 100,000 Max Cl/Cd: 74.44 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e62-il-100000-n5.txt Download as CSV file: xf-e62-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: E62 (5.62%)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.3560 0.11444 0.10970 -0.0272 1.0000 0.0324
-7.750 -0.3629 0.11335 0.10868 -0.0260 1.0000 0.0325
-7.500 -0.3707 0.11227 0.10769 -0.0245 1.0000 0.0326
-7.250 -0.3745 0.11066 0.10616 -0.0242 1.0000 0.0326
-7.000 -0.3755 0.10872 0.10428 -0.0247 1.0000 0.0327
-6.750 -0.3746 0.10495 0.10059 -0.0242 0.9997 0.0330
-6.500 -0.3677 0.09925 0.09487 -0.0186 0.9995 0.0347
-6.250 -0.3496 0.09552 0.09113 -0.0215 0.9958 0.0369
-6.000 -0.3298 0.09182 0.08744 -0.0264 0.9908 0.0392
-5.750 -0.3043 0.08786 0.08346 -0.0337 0.9854 0.0420
-5.500 -0.2685 0.08424 0.07980 -0.0471 0.9774 0.0443
-5.250 -0.2191 0.07968 0.07512 -0.0634 0.9722 0.0450
-5.000 -0.2089 0.07462 0.07011 -0.0636 0.9667 0.0458
-4.750 -0.1946 0.07080 0.06625 -0.0631 0.9629 0.0471
-4.500 -0.1693 0.06709 0.06252 -0.0669 0.9588 0.0491
-4.250 -0.1408 0.06334 0.05871 -0.0723 0.9528 0.0514
-4.000 -0.0591 0.05749 0.05244 -0.0946 0.9495 0.0581
-3.750 -0.0303 0.05259 0.04750 -0.0989 0.9455 0.0590
-3.500 -0.0018 0.04882 0.04368 -0.1021 0.9407 0.0599
-3.250 0.0509 0.04216 0.03669 -0.1103 0.9388 0.0300
-3.000 0.1182 0.03509 0.02892 -0.1216 0.9383 0.0241
-2.750 0.1646 0.03146 0.02491 -0.1275 0.9368 0.0232
-2.500 0.2141 0.02810 0.02088 -0.1331 0.9358 0.0235
-2.250 0.2544 0.02569 0.01786 -0.1362 0.9324 0.0249
-2.000 0.2921 0.02381 0.01554 -0.1386 0.9290 0.0253
-1.750 0.3305 0.02225 0.01362 -0.1408 0.9262 0.0255
-1.500 0.3686 0.02103 0.01217 -0.1428 0.9239 0.0264
-1.250 0.4024 0.02017 0.01115 -0.1441 0.9198 0.0278
-1.000 0.4345 0.01953 0.01037 -0.1449 0.9146 0.0300
-0.750 0.4711 0.01894 0.00970 -0.1467 0.9112 0.0379
-0.500 0.5083 0.01828 0.00907 -0.1485 0.9079 0.0701
-0.250 0.5408 0.01732 0.00913 -0.1503 0.9026 0.3992
0.000 0.5628 0.01600 0.00889 -0.1483 0.8977 1.0000
0.250 0.5937 0.01606 0.00871 -0.1489 0.8915 1.0000
0.500 0.6261 0.01607 0.00853 -0.1497 0.8857 1.0000
1.000 0.6903 0.01605 0.00824 -0.1512 0.8734 1.0000
1.250 0.7278 0.01589 0.00800 -0.1528 0.8691 1.0000
1.500 0.7561 0.01594 0.00800 -0.1528 0.8601 1.0000
1.750 0.7946 0.01576 0.00780 -0.1547 0.8551 1.0000
2.000 0.8233 0.01579 0.00783 -0.1547 0.8454 1.0000
2.250 0.8582 0.01567 0.00772 -0.1558 0.8377 1.0000
2.500 0.8921 0.01555 0.00766 -0.1566 0.8286 1.0000
2.750 0.9226 0.01553 0.00768 -0.1569 0.8174 1.0000
3.000 0.9548 0.01545 0.00766 -0.1574 0.8056 1.0000
3.250 0.9871 0.01538 0.00766 -0.1578 0.7924 1.0000
3.500 1.0187 0.01533 0.00774 -0.1581 0.7776 1.0000
3.750 1.0502 0.01530 0.00779 -0.1584 0.7610 1.0000
4.000 1.0812 0.01528 0.00785 -0.1585 0.7417 1.0000
4.250 1.1090 0.01536 0.00801 -0.1580 0.7184 1.0000
4.500 1.1360 0.01547 0.00826 -0.1574 0.6917 1.0000
4.750 1.1624 0.01563 0.00846 -0.1565 0.6593 1.0000
5.000 1.1844 0.01591 0.00862 -0.1546 0.5987 1.0000
5.250 1.1999 0.01671 0.00880 -0.1515 0.4857 1.0000
5.500 1.2131 0.01785 0.00943 -0.1486 0.3949 1.0000
5.750 1.2232 0.01931 0.01038 -0.1456 0.2964 1.0000
6.000 1.2313 0.02119 0.01149 -0.1426 0.1823 1.0000
6.250 1.2403 0.02327 0.01281 -0.1400 0.0800 1.0000
6.500 1.2513 0.02524 0.01436 -0.1374 0.0322 1.0000
6.750 1.2672 0.02660 0.01580 -0.1353 0.0238 1.0000
7.000 1.2820 0.02805 0.01740 -0.1330 0.0211 1.0000
7.250 1.2969 0.02940 0.01899 -0.1308 0.0197 1.0000
7.500 1.3102 0.03088 0.02076 -0.1284 0.0186 1.0000
7.750 1.3219 0.03247 0.02255 -0.1258 0.0178 1.0000
8.000 1.3331 0.03419 0.02444 -0.1232 0.0172 1.0000
8.250 1.3452 0.03609 0.02650 -0.1208 0.0167 1.0000
8.500 1.3596 0.03823 0.02879 -0.1189 0.0163 1.0000
8.750 1.3772 0.04074 0.03148 -0.1175 0.0159 1.0000
9.000 1.3984 0.04417 0.03508 -0.1170 0.0153 1.0000
9.250 1.4145 0.04659 0.03790 -0.1152 0.0148 1.0000
9.500 1.4267 0.04932 0.04106 -0.1131 0.0140 1.0000
9.750 1.4346 0.05241 0.04457 -0.1105 0.0136 1.0000
10.000 1.4373 0.05581 0.04839 -0.1074 0.0135 1.0000
10.250 1.4346 0.05933 0.05231 -0.1040 0.0135 1.0000
10.500 1.4276 0.06299 0.05635 -0.1005 0.0135 1.0000
10.750 1.4173 0.06682 0.06054 -0.0973 0.0135 1.0000
11.000 1.4038 0.07098 0.06512 -0.0944 0.0135 1.0000
11.250 1.3882 0.07545 0.06991 -0.0922 0.0136 1.0000
11.500 1.3711 0.08026 0.07502 -0.0909 0.0136 1.0000
11.750 1.3528 0.08552 0.08056 -0.0905 0.0137 1.0000
12.000 1.3333 0.09132 0.08662 -0.0912 0.0137 1.0000
12.250 1.3133 0.09772 0.09318 -0.0931 0.0138 1.0000
12.500 1.2931 0.10478 0.10045 -0.0962 0.0139 1.0000
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Polar data table (+)
Polar graphs
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