EPPLER E662 AIRFOIL (e662-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER E662 AIRFOIL (e662-il) Reynolds number: 500,000 Max Cl/Cd: 111.09 at α=4° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e662-il-500000-n5.txt Download as CSV file: xf-e662-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.250 -0.2847 0.04985 0.04621 -0.1572 0.8278 0.0104
-12.000 -0.3360 0.04066 0.03669 -0.1624 0.8251 0.0102
-11.750 -0.3522 0.03732 0.03318 -0.1622 0.8233 0.0104
-11.500 -0.3692 0.03427 0.02993 -0.1608 0.8213 0.0104
-11.250 -0.3862 0.03140 0.02681 -0.1583 0.8190 0.0105
-11.000 -0.3904 0.02965 0.02487 -0.1559 0.8170 0.0109
-10.750 -0.3933 0.02808 0.02310 -0.1532 0.8152 0.0110
-10.500 -0.3964 0.02675 0.02153 -0.1499 0.8136 0.0113
-10.250 -0.3894 0.02561 0.02017 -0.1478 0.8123 0.0115
-10.000 -0.3794 0.02443 0.01876 -0.1461 0.8111 0.0116
-9.500 -0.3542 0.02184 0.01588 -0.1433 0.8088 0.0121
-9.250 -0.3367 0.02103 0.01499 -0.1424 0.8076 0.0123
-9.000 -0.3178 0.02030 0.01417 -0.1415 0.8063 0.0126
-8.750 -0.2979 0.01959 0.01336 -0.1408 0.8053 0.0128
-8.500 -0.2772 0.01888 0.01255 -0.1402 0.8042 0.0131
-8.250 -0.2557 0.01822 0.01179 -0.1396 0.8031 0.0135
-8.000 -0.2334 0.01765 0.01113 -0.1391 0.8021 0.0140
-7.750 -0.2106 0.01709 0.01047 -0.1387 0.8009 0.0144
-7.500 -0.1873 0.01657 0.00985 -0.1383 0.7998 0.0148
-7.250 -0.1635 0.01610 0.00928 -0.1379 0.7987 0.0151
-7.000 -0.1407 0.01547 0.00858 -0.1374 0.7978 0.0154
-6.750 -0.1182 0.01483 0.00791 -0.1369 0.7968 0.0159
-6.500 -0.0943 0.01438 0.00742 -0.1366 0.7959 0.0163
-6.250 -0.0697 0.01400 0.00699 -0.1365 0.7948 0.0168
-6.000 -0.0456 0.01365 0.00662 -0.1361 0.7938 0.0173
-5.750 -0.0213 0.01332 0.00627 -0.1358 0.7928 0.0178
-5.500 0.0036 0.01305 0.00598 -0.1356 0.7916 0.0186
-5.250 0.0287 0.01279 0.00568 -0.1354 0.7904 0.0193
-5.000 0.0538 0.01249 0.00536 -0.1352 0.7891 0.0200
-4.750 0.0792 0.01220 0.00505 -0.1351 0.7878 0.0210
-4.500 0.1053 0.01197 0.00481 -0.1350 0.7865 0.0221
-4.250 0.1319 0.01177 0.00459 -0.1351 0.7852 0.0236
-4.000 0.1588 0.01160 0.00439 -0.1352 0.7840 0.0255
-3.750 0.1858 0.01138 0.00420 -0.1353 0.7828 0.0316
-3.500 0.2127 0.01111 0.00403 -0.1355 0.7816 0.0533
-3.250 0.2401 0.01089 0.00389 -0.1358 0.7805 0.0791
-3.000 0.2678 0.01068 0.00378 -0.1362 0.7793 0.1118
-2.750 0.2933 0.01043 0.00370 -0.1361 0.7778 0.1560
-2.500 0.3191 0.01014 0.00362 -0.1362 0.7760 0.2126
-2.250 0.3451 0.00964 0.00352 -0.1366 0.7740 0.3249
-2.000 0.3724 0.00906 0.00339 -0.1374 0.7720 0.4610
-1.750 0.4005 0.00843 0.00333 -0.1381 0.7701 0.6270
-1.500 0.4269 0.00843 0.00359 -0.1377 0.7683 0.7179
-1.250 0.4558 0.00851 0.00365 -0.1379 0.7666 0.7423
-1.000 0.4855 0.00857 0.00366 -0.1384 0.7650 0.7535
-0.750 0.5125 0.00865 0.00375 -0.1382 0.7628 0.7617
-0.500 0.5396 0.00872 0.00380 -0.1382 0.7599 0.7713
-0.250 0.5652 0.00883 0.00393 -0.1377 0.7571 0.7793
0.000 0.5930 0.00891 0.00400 -0.1377 0.7545 0.7881
0.250 0.6197 0.00899 0.00408 -0.1374 0.7522 0.7935
0.500 0.6487 0.00901 0.00407 -0.1377 0.7500 0.7977
0.750 0.6757 0.00903 0.00409 -0.1377 0.7467 0.8010
1.000 0.7022 0.00902 0.00409 -0.1376 0.7428 0.8030
1.250 0.7292 0.00900 0.00407 -0.1376 0.7391 0.8043
1.500 0.7574 0.00896 0.00401 -0.1378 0.7359 0.8057
1.750 0.7830 0.00897 0.00405 -0.1375 0.7313 0.8071
2.000 0.8089 0.00896 0.00407 -0.1373 0.7262 0.8087
2.250 0.8366 0.00893 0.00402 -0.1374 0.7217 0.8101
2.500 0.8620 0.00894 0.00407 -0.1371 0.7153 0.8117
2.750 0.8883 0.00891 0.00404 -0.1369 0.7084 0.8133
3.000 0.9138 0.00892 0.00405 -0.1367 0.7002 0.8147
3.250 0.9395 0.00891 0.00401 -0.1364 0.6908 0.8163
3.500 0.9641 0.00892 0.00401 -0.1359 0.6790 0.8177
3.750 0.9866 0.00897 0.00401 -0.1350 0.6644 0.8186
4.000 1.0076 0.00907 0.00406 -0.1337 0.6472 0.8196
4.250 1.0264 0.00924 0.00416 -0.1320 0.6272 0.8209
4.500 1.0423 0.00948 0.00431 -0.1297 0.6059 0.8224
4.750 1.0547 0.00974 0.00449 -0.1268 0.5832 0.8239
5.000 1.0643 0.01009 0.00473 -0.1233 0.5606 0.8255
5.250 1.0743 0.01050 0.00505 -0.1200 0.5364 0.8272
5.500 1.0835 0.01099 0.00544 -0.1167 0.5133 0.8289
5.750 1.0938 0.01148 0.00585 -0.1137 0.4906 0.8308
6.000 1.1028 0.01204 0.00631 -0.1106 0.4684 0.8326
6.250 1.1124 0.01260 0.00680 -0.1077 0.4467 0.8339
6.500 1.1207 0.01324 0.00737 -0.1046 0.4248 0.8353
6.750 1.1297 0.01391 0.00798 -0.1018 0.4027 0.8367
7.000 1.1396 0.01461 0.00861 -0.0993 0.3816 0.8382
7.250 1.1489 0.01540 0.00931 -0.0967 0.3595 0.8398
7.500 1.1596 0.01616 0.01000 -0.0945 0.3381 0.8413
7.750 1.1705 0.01697 0.01073 -0.0924 0.3179 0.8431
8.000 1.1823 0.01777 0.01147 -0.0905 0.2981 0.8449
8.250 1.1936 0.01863 0.01225 -0.0886 0.2766 0.8465
8.500 1.2049 0.01951 0.01304 -0.0867 0.2567 0.8479
8.750 1.2162 0.02039 0.01385 -0.0848 0.2358 0.8492
9.000 1.2263 0.02136 0.01473 -0.0829 0.2141 0.8506
9.250 1.2380 0.02227 0.01559 -0.0812 0.1965 0.8520
9.500 1.2504 0.02316 0.01644 -0.0797 0.1799 0.8535
9.750 1.2620 0.02413 0.01735 -0.0781 0.1627 0.8551
10.000 1.2730 0.02516 0.01831 -0.0765 0.1453 0.8567
10.500 1.2945 0.02735 0.02038 -0.0735 0.1144 0.8600
10.750 1.3058 0.02845 0.02143 -0.0721 0.1010 0.8618
11.000 1.3157 0.02964 0.02258 -0.0706 0.0869 0.8634
11.250 1.3265 0.03079 0.02370 -0.0692 0.0768 0.8651
11.500 1.3370 0.03198 0.02488 -0.0679 0.0665 0.8668
11.750 1.3463 0.03330 0.02618 -0.0665 0.0564 0.8686
12.000 1.3571 0.03453 0.02742 -0.0653 0.0493 0.8704
12.250 1.3670 0.03588 0.02877 -0.0641 0.0434 0.8723
12.500 1.3775 0.03721 0.03012 -0.0630 0.0381 0.8743
12.750 1.3878 0.03859 0.03153 -0.0620 0.0339 0.8762
13.000 1.3963 0.04013 0.03309 -0.0609 0.0291 0.8781
13.250 1.4053 0.04163 0.03463 -0.0598 0.0250 0.8800
13.500 1.4128 0.04332 0.03636 -0.0588 0.0214 0.8822
13.750 1.4195 0.04513 0.03821 -0.0577 0.0171 0.8846
14.000 1.4252 0.04709 0.04021 -0.0567 0.0133 0.8871
14.250 1.4307 0.04914 0.04229 -0.0558 0.0106 0.8896
14.750 1.4408 0.05340 0.04670 -0.0542 0.0079 0.8954
15.000 1.4462 0.05556 0.04897 -0.0535 0.0072 0.8990
15.250 1.4509 0.05788 0.05139 -0.0530 0.0067 0.9027
15.750 1.4568 0.06306 0.05678 -0.0521 0.0060 0.9110
16.000 1.4585 0.06588 0.05971 -0.0518 0.0057 0.9164
16.250 1.4608 0.06862 0.06258 -0.0515 0.0056 0.9233
16.750 1.4600 0.07449 0.06874 -0.0510 0.0052 1.0000
17.000 1.4600 0.07795 0.07231 -0.0514 0.0050 1.0000
17.250 1.4599 0.08147 0.07594 -0.0520 0.0049 1.0000
17.500 1.4586 0.08525 0.07984 -0.0527 0.0047 1.0000
17.750 1.4561 0.08928 0.08398 -0.0536 0.0046 1.0000
18.000 1.4526 0.09353 0.08835 -0.0548 0.0045 1.0000
18.250 1.4480 0.09803 0.09297 -0.0561 0.0044 1.0000
18.500 1.4416 0.10289 0.09795 -0.0577 0.0042 1.0000
18.750 1.4345 0.10796 0.10316 -0.0595 0.0041 1.0000
19.000 1.4264 0.11331 0.10863 -0.0616 0.0041 1.0000
19.250 1.4166 0.11902 0.11448 -0.0641 0.0040 1.0000
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