E385 (8.41%) (e385-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: E385 (8.41%) (e385-il) Reynolds number: 200,000 Max Cl/Cd: 96.79 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e385-il-200000-n5.txt Download as CSV file: xf-e385-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: E385 (8.41%)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.2598 0.11630 0.11276 -0.0384 1.0000 0.0172
-9.500 -0.2581 0.11400 0.11051 -0.0381 1.0000 0.0176
-9.250 -0.2575 0.11185 0.10840 -0.0375 1.0000 0.0178
-9.000 -0.2447 0.10840 0.10496 -0.0405 0.9975 0.0184
-8.750 -0.2284 0.10452 0.10108 -0.0446 0.9930 0.0192
-8.500 -0.2120 0.10076 0.09733 -0.0499 0.9872 0.0204
-8.250 -0.1972 0.09730 0.09388 -0.0551 0.9800 0.0207
-8.000 -0.1820 0.09368 0.09027 -0.0614 0.9716 0.0208
-7.500 -0.1522 0.08601 0.08262 -0.0653 0.9544 0.0218
-7.250 -0.1327 0.08282 0.07941 -0.0682 0.9464 0.0236
-7.000 -0.1148 0.07935 0.07594 -0.0726 0.9347 0.0243
-6.750 -0.0948 0.07559 0.07215 -0.0789 0.9212 0.0261
-6.500 -0.0639 0.07096 0.06747 -0.0919 0.9059 0.0270
-6.250 -0.0342 0.06624 0.06268 -0.1015 0.8923 0.0272
-6.000 -0.0102 0.06138 0.05777 -0.1079 0.8794 0.0274
-5.750 0.0059 0.05811 0.05446 -0.1087 0.8677 0.0281
-5.500 0.0275 0.05496 0.05124 -0.1120 0.8553 0.0287
-5.250 0.0516 0.05151 0.04769 -0.1167 0.8430 0.0294
-5.000 0.0789 0.04760 0.04365 -0.1224 0.8309 0.0297
-4.500 0.1556 0.03244 0.02779 -0.1404 0.8100 0.0152
-4.000 0.2246 0.02388 0.01831 -0.1487 0.7924 0.0142
-3.750 0.2602 0.02031 0.01408 -0.1515 0.7847 0.0140
-3.500 0.2933 0.01792 0.01109 -0.1530 0.7765 0.0143
-3.250 0.3246 0.01652 0.00917 -0.1538 0.7689 0.0158
-3.000 0.3541 0.01536 0.00777 -0.1544 0.7611 0.0167
-2.750 0.3836 0.01443 0.00663 -0.1547 0.7539 0.0172
-2.500 0.4128 0.01372 0.00576 -0.1549 0.7465 0.0178
-2.250 0.4420 0.01316 0.00507 -0.1552 0.7397 0.0188
-2.000 0.4712 0.01274 0.00449 -0.1555 0.7327 0.0202
-1.750 0.5004 0.01240 0.00406 -0.1558 0.7265 0.0235
-1.500 0.5294 0.01213 0.00375 -0.1560 0.7195 0.0316
-1.250 0.5590 0.01179 0.00345 -0.1564 0.7138 0.0719
-1.000 0.5880 0.01143 0.00340 -0.1570 0.7072 0.1668
-0.750 0.6170 0.01107 0.00340 -0.1576 0.7012 0.3074
-0.500 0.6453 0.01081 0.00343 -0.1579 0.6953 0.4364
-0.250 0.6718 0.01044 0.00352 -0.1577 0.6893 0.6184
0.250 0.7128 0.00989 0.00341 -0.1536 0.6780 1.0000
0.500 0.7411 0.01002 0.00340 -0.1538 0.6725 1.0000
0.750 0.7694 0.01015 0.00342 -0.1538 0.6672 1.0000
1.000 0.7974 0.01027 0.00347 -0.1539 0.6612 1.0000
1.250 0.8255 0.01042 0.00350 -0.1540 0.6562 1.0000
1.500 0.8534 0.01056 0.00359 -0.1540 0.6504 1.0000
1.750 0.8812 0.01070 0.00369 -0.1540 0.6447 1.0000
2.000 0.9091 0.01086 0.00377 -0.1541 0.6399 1.0000
2.250 0.9365 0.01100 0.00392 -0.1541 0.6336 1.0000
2.500 0.9641 0.01116 0.00405 -0.1540 0.6281 1.0000
2.750 0.9915 0.01132 0.00420 -0.1540 0.6223 1.0000
3.000 1.0187 0.01148 0.00436 -0.1539 0.6158 1.0000
3.250 1.0459 0.01164 0.00450 -0.1538 0.6095 1.0000
3.500 1.0726 0.01179 0.00470 -0.1537 0.6014 1.0000
3.750 1.0994 0.01196 0.00487 -0.1535 0.5939 1.0000
4.000 1.1259 0.01212 0.00506 -0.1533 0.5855 1.0000
4.250 1.1522 0.01229 0.00526 -0.1530 0.5768 1.0000
4.500 1.1784 0.01247 0.00546 -0.1527 0.5677 1.0000
4.750 1.2042 0.01264 0.00570 -0.1524 0.5570 1.0000
5.000 1.2299 0.01283 0.00594 -0.1520 0.5466 1.0000
5.250 1.2552 0.01304 0.00620 -0.1516 0.5356 1.0000
5.500 1.2802 0.01325 0.00646 -0.1510 0.5227 1.0000
5.750 1.3047 0.01348 0.00674 -0.1505 0.5078 1.0000
6.000 1.3286 0.01374 0.00704 -0.1498 0.4903 1.0000
6.250 1.3506 0.01408 0.00737 -0.1487 0.4627 1.0000
6.500 1.3697 0.01459 0.00774 -0.1472 0.4207 1.0000
6.750 1.3847 0.01543 0.00828 -0.1452 0.3615 1.0000
7.000 1.3938 0.01676 0.00916 -0.1424 0.2874 1.0000
7.250 1.4024 0.01821 0.01022 -0.1397 0.2236 1.0000
7.500 1.4127 0.01951 0.01126 -0.1373 0.1747 1.0000
7.750 1.4208 0.02094 0.01242 -0.1347 0.1283 1.0000
8.000 1.4285 0.02230 0.01356 -0.1319 0.0917 1.0000
8.250 1.4343 0.02360 0.01472 -0.1288 0.0636 1.0000
8.500 1.4385 0.02501 0.01602 -0.1256 0.0402 1.0000
8.750 1.4424 0.02651 0.01746 -0.1225 0.0254 1.0000
9.000 1.4483 0.02794 0.01892 -0.1198 0.0192 1.0000
9.250 1.4555 0.02933 0.02041 -0.1175 0.0166 1.0000
9.750 1.4682 0.03246 0.02378 -0.1131 0.0139 1.0000
10.000 1.4746 0.03412 0.02557 -0.1112 0.0129 1.0000
10.250 1.4800 0.03594 0.02752 -0.1094 0.0122 1.0000
10.500 1.4840 0.03799 0.02971 -0.1077 0.0117 1.0000
10.750 1.4861 0.04030 0.03215 -0.1061 0.0113 1.0000
11.000 1.4862 0.04292 0.03492 -0.1045 0.0110 1.0000
11.250 1.4861 0.04567 0.03780 -0.1032 0.0108 1.0000
11.500 1.4876 0.04834 0.04062 -0.1020 0.0106 1.0000
11.750 1.4886 0.05115 0.04360 -0.1010 0.0105 1.0000
12.000 1.4893 0.05408 0.04668 -0.1001 0.0103 1.0000
12.250 1.4899 0.05709 0.04984 -0.0993 0.0102 1.0000
12.500 1.4907 0.06017 0.05307 -0.0986 0.0100 1.0000
12.750 1.4917 0.06330 0.05635 -0.0979 0.0099 1.0000
13.000 1.4932 0.06646 0.05966 -0.0974 0.0097 1.0000
13.250 1.4949 0.06966 0.06302 -0.0968 0.0096 1.0000
13.500 1.4966 0.07294 0.06647 -0.0964 0.0095 1.0000
13.750 1.4980 0.07633 0.07003 -0.0962 0.0093 1.0000
14.000 1.4987 0.07989 0.07377 -0.0961 0.0090 1.0000
14.250 1.4981 0.08366 0.07773 -0.0964 0.0087 1.0000
14.500 1.4971 0.08760 0.08185 -0.0967 0.0086 1.0000
14.750 1.4946 0.09179 0.08622 -0.0975 0.0084 1.0000
15.000 1.4913 0.09622 0.09082 -0.0984 0.0082 1.0000
15.250 1.4872 0.10090 0.09568 -0.0995 0.0081 1.0000
15.500 1.4820 0.10586 0.10084 -0.1009 0.0080 1.0000
15.750 1.4757 0.11113 0.10633 -0.1027 0.0080 1.0000
16.000 1.4680 0.11682 0.11223 -0.1049 0.0079 1.0000
16.250 1.4596 0.12278 0.11839 -0.1075 0.0079 1.0000
16.500 1.4502 0.12918 0.12501 -0.1107 0.0078 1.0000
16.750 1.4395 0.13597 0.13201 -0.1143 0.0078 1.0000
17.000 1.4288 0.14316 0.13942 -0.1186 0.0078 1.0000
17.250 1.4172 0.15080 0.14727 -0.1234 0.0078 1.0000
17.500 1.4047 0.15907 0.15573 -0.1289 0.0078 1.0000
17.750 1.3916 0.16798 0.16485 -0.1351 0.0078 1.0000
18.000 1.3756 0.17856 0.17567 -0.1426 0.0079 1.0000
18.250 1.3550 0.19169 0.18904 -0.1520 0.0081 1.0000
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Polar data table (+)
Polar graphs
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