EPPLER E662 AIRFOIL (e662-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER E662 AIRFOIL (e662-il) Reynolds number: 1,000,000 Max Cl/Cd: 138.7 at α=2.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e662-il-1000000-n5.txt Download as CSV file: xf-e662-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER E662 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.750 -0.5139 0.04780 0.04444 -0.1561 0.8121 0.0075
-14.250 -0.5511 0.03707 0.03338 -0.1625 0.8085 0.0075
-14.000 -0.5681 0.03341 0.02955 -0.1628 0.8070 0.0076
-13.750 -0.5642 0.03183 0.02789 -0.1625 0.8057 0.0077
-13.500 -0.5686 0.02973 0.02565 -0.1615 0.8042 0.0078
-13.250 -0.5662 0.02825 0.02405 -0.1604 0.8028 0.0079
-13.000 -0.5693 0.02644 0.02210 -0.1586 0.8013 0.0080
-12.750 -0.5610 0.02546 0.02102 -0.1574 0.8000 0.0082
-12.500 -0.5582 0.02413 0.01956 -0.1555 0.7987 0.0082
-12.250 -0.5515 0.02308 0.01838 -0.1538 0.7974 0.0083
-12.000 -0.5444 0.02207 0.01725 -0.1519 0.7960 0.0084
-11.500 -0.5250 0.02052 0.01551 -0.1481 0.7936 0.0085
-11.250 -0.5167 0.01984 0.01474 -0.1458 0.7926 0.0086
-11.000 -0.5073 0.01890 0.01370 -0.1437 0.7916 0.0088
-10.750 -0.4918 0.01820 0.01292 -0.1425 0.7907 0.0090
-10.500 -0.4730 0.01771 0.01238 -0.1416 0.7898 0.0092
-10.250 -0.4520 0.01736 0.01200 -0.1410 0.7890 0.0094
-10.000 -0.4314 0.01690 0.01149 -0.1403 0.7881 0.0095
-9.750 -0.4098 0.01650 0.01105 -0.1398 0.7872 0.0097
-9.500 -0.3884 0.01602 0.01049 -0.1392 0.7862 0.0100
-9.250 -0.3664 0.01556 0.00998 -0.1387 0.7852 0.0102
-9.000 -0.3441 0.01509 0.00944 -0.1382 0.7843 0.0104
-8.750 -0.3213 0.01464 0.00893 -0.1378 0.7834 0.0106
-8.500 -0.2981 0.01420 0.00842 -0.1374 0.7826 0.0109
-8.250 -0.2742 0.01382 0.00796 -0.1371 0.7818 0.0111
-8.000 -0.2497 0.01348 0.00757 -0.1369 0.7809 0.0113
-7.750 -0.2251 0.01314 0.00717 -0.1367 0.7798 0.0115
-7.500 -0.1999 0.01284 0.00683 -0.1366 0.7789 0.0116
-7.250 -0.1774 0.01225 0.00620 -0.1361 0.7783 0.0122
-7.000 -0.1523 0.01191 0.00585 -0.1360 0.7776 0.0125
-6.750 -0.1268 0.01162 0.00554 -0.1359 0.7768 0.0129
-6.500 -0.1010 0.01134 0.00524 -0.1358 0.7759 0.0132
-6.250 -0.0751 0.01106 0.00494 -0.1358 0.7750 0.0135
-6.000 -0.0489 0.01080 0.00466 -0.1358 0.7741 0.0139
-5.750 -0.0225 0.01056 0.00439 -0.1358 0.7731 0.0142
-5.500 0.0043 0.01034 0.00416 -0.1359 0.7721 0.0146
-5.250 0.0313 0.01014 0.00393 -0.1360 0.7711 0.0149
-5.000 0.0585 0.00996 0.00373 -0.1362 0.7701 0.0153
-4.750 0.0853 0.00969 0.00345 -0.1363 0.7691 0.0162
-4.500 0.1127 0.00951 0.00326 -0.1364 0.7681 0.0171
-4.250 0.1404 0.00935 0.00308 -0.1367 0.7670 0.0178
-4.000 0.1683 0.00921 0.00293 -0.1370 0.7659 0.0187
-3.750 0.1966 0.00911 0.00280 -0.1373 0.7647 0.0196
-3.500 0.2245 0.00896 0.00267 -0.1376 0.7636 0.0223
-3.250 0.2520 0.00878 0.00254 -0.1378 0.7625 0.0308
-3.000 0.2793 0.00855 0.00243 -0.1380 0.7610 0.0561
-2.750 0.3069 0.00834 0.00233 -0.1383 0.7593 0.0829
-2.500 0.3347 0.00813 0.00223 -0.1386 0.7575 0.1159
-2.250 0.3627 0.00793 0.00214 -0.1390 0.7557 0.1515
-2.000 0.3908 0.00767 0.00206 -0.1395 0.7541 0.2071
-1.750 0.4192 0.00739 0.00197 -0.1401 0.7523 0.2733
-1.500 0.4481 0.00707 0.00189 -0.1408 0.7503 0.3603
-1.250 0.4775 0.00648 0.00178 -0.1420 0.7482 0.5192
-1.000 0.5072 0.00595 0.00181 -0.1430 0.7460 0.6901
-0.750 0.5358 0.00595 0.00187 -0.1433 0.7436 0.7237
-0.500 0.5645 0.00596 0.00189 -0.1436 0.7411 0.7358
-0.250 0.5932 0.00598 0.00191 -0.1438 0.7385 0.7452
0.000 0.6221 0.00602 0.00190 -0.1442 0.7358 0.7541
0.250 0.6501 0.00605 0.00197 -0.1443 0.7326 0.7615
0.500 0.6785 0.00610 0.00201 -0.1446 0.7286 0.7693
0.750 0.7061 0.00613 0.00206 -0.1446 0.7245 0.7749
1.000 0.7337 0.00618 0.00209 -0.1446 0.7204 0.7792
1.250 0.7618 0.00620 0.00213 -0.1449 0.7151 0.7821
1.500 0.7894 0.00622 0.00213 -0.1450 0.7088 0.7840
1.750 0.8169 0.00625 0.00214 -0.1451 0.7014 0.7854
2.000 0.8433 0.00629 0.00214 -0.1449 0.6918 0.7867
2.250 0.8686 0.00635 0.00216 -0.1446 0.6794 0.7880
2.750 0.9154 0.00660 0.00229 -0.1431 0.6463 0.7904
3.000 0.9366 0.00680 0.00240 -0.1419 0.6256 0.7916
3.250 0.9559 0.00705 0.00256 -0.1403 0.6033 0.7929
3.500 0.9744 0.00732 0.00274 -0.1386 0.5794 0.7941
3.750 0.9915 0.00762 0.00293 -0.1366 0.5560 0.7954
4.000 1.0068 0.00794 0.00315 -0.1343 0.5322 0.7968
4.250 1.0198 0.00824 0.00335 -0.1314 0.5100 0.7983
4.500 1.0315 0.00860 0.00362 -0.1284 0.4861 0.7997
4.750 1.0440 0.00900 0.00391 -0.1256 0.4621 0.8009
5.000 1.0574 0.00939 0.00421 -0.1231 0.4411 0.8019
5.250 1.0711 0.00978 0.00453 -0.1206 0.4215 0.8031
5.500 1.0837 0.01022 0.00489 -0.1180 0.3993 0.8045
5.750 1.0960 0.01069 0.00528 -0.1154 0.3785 0.8058
6.000 1.1084 0.01119 0.00570 -0.1129 0.3575 0.8071
6.250 1.1200 0.01174 0.00617 -0.1104 0.3354 0.8083
6.500 1.1316 0.01233 0.00667 -0.1079 0.3147 0.8096
6.750 1.1453 0.01288 0.00716 -0.1059 0.2972 0.8108
7.000 1.1581 0.01349 0.00770 -0.1038 0.2779 0.8121
7.250 1.1713 0.01413 0.00826 -0.1018 0.2600 0.8134
7.500 1.1835 0.01483 0.00888 -0.0997 0.2409 0.8146
7.750 1.1964 0.01553 0.00951 -0.0978 0.2216 0.8158
8.000 1.2087 0.01629 0.01017 -0.0959 0.2021 0.8171
8.250 1.2203 0.01710 0.01089 -0.0940 0.1825 0.8184
8.500 1.2322 0.01791 0.01162 -0.0921 0.1628 0.8197
8.750 1.2422 0.01885 0.01245 -0.0900 0.1410 0.8209
9.000 1.2556 0.01963 0.01318 -0.0884 0.1275 0.8221
9.500 1.2825 0.02123 0.01469 -0.0854 0.1026 0.8246
9.750 1.2943 0.02216 0.01556 -0.0837 0.0887 0.8259
10.000 1.3077 0.02301 0.01637 -0.0824 0.0783 0.8271
10.250 1.3203 0.02392 0.01725 -0.0809 0.0681 0.8284
10.500 1.3339 0.02479 0.01810 -0.0796 0.0602 0.8297
10.750 1.3458 0.02579 0.01906 -0.0782 0.0511 0.8309
11.000 1.3572 0.02685 0.02008 -0.0767 0.0431 0.8321
11.250 1.3693 0.02787 0.02108 -0.0754 0.0366 0.8333
11.500 1.3819 0.02886 0.02208 -0.0741 0.0317 0.8348
11.750 1.3928 0.02999 0.02322 -0.0727 0.0262 0.8363
12.000 1.4048 0.03107 0.02431 -0.0715 0.0228 0.8378
12.250 1.4164 0.03221 0.02547 -0.0703 0.0192 0.8393
12.500 1.4264 0.03350 0.02675 -0.0690 0.0151 0.8408
12.750 1.4363 0.03482 0.02809 -0.0678 0.0114 0.8423
13.250 1.4541 0.03775 0.03106 -0.0654 0.0065 0.8452
13.500 1.4637 0.03919 0.03255 -0.0643 0.0057 0.8466
14.000 1.4833 0.04212 0.03560 -0.0624 0.0048 0.8496
14.250 1.4919 0.04375 0.03728 -0.0614 0.0044 0.8513
14.500 1.5001 0.04545 0.03905 -0.0605 0.0042 0.8530
14.750 1.5077 0.04724 0.04092 -0.0597 0.0039 0.8548
15.000 1.5160 0.04901 0.04276 -0.0589 0.0037 0.8567
15.250 1.5235 0.05088 0.04471 -0.0583 0.0036 0.8586
15.500 1.5306 0.05285 0.04676 -0.0577 0.0035 0.8605
15.750 1.5370 0.05494 0.04893 -0.0571 0.0034 0.8623
16.000 1.5424 0.05718 0.05126 -0.0566 0.0033 0.8645
16.250 1.5472 0.05953 0.05369 -0.0562 0.0032 0.8668
16.500 1.5511 0.06203 0.05628 -0.0558 0.0031 0.8693
16.750 1.5540 0.06472 0.05906 -0.0556 0.0030 0.8718
17.000 1.5554 0.06767 0.06210 -0.0555 0.0029 0.8741
17.250 1.5567 0.07072 0.06524 -0.0555 0.0028 0.8763
17.500 1.5567 0.07399 0.06863 -0.0556 0.0027 0.8787
17.750 1.5541 0.07768 0.07244 -0.0559 0.0026 0.8812
18.000 1.5512 0.08150 0.07638 -0.0564 0.0026 0.8838
18.250 1.5474 0.08557 0.08056 -0.0571 0.0025 0.8865
18.500 1.5461 0.08934 0.08444 -0.0579 0.0025 0.8895
19.000 1.5391 0.09771 0.09304 -0.0601 0.0025 0.8958
19.250 1.5348 0.10210 0.09756 -0.0615 0.0024 0.8995
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Polar data table (+)
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