E385 (8.41%) (e385-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: E385 (8.41%) (e385-il) Reynolds number: 200,000 Max Cl/Cd: 96.82 at α=6.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e385-il-200000.txt Download as CSV file: xf-e385-il-200000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.2628 0.10928 0.10599 -0.0353 1.0000 0.0272
-8.500 -0.2719 0.10838 0.10517 -0.0330 1.0000 0.0277
-8.250 -0.2791 0.10762 0.10449 -0.0326 0.9989 0.0282
-8.000 -0.2582 0.10443 0.10130 -0.0417 0.9929 0.0286
-7.750 -0.2361 0.10090 0.09777 -0.0503 0.9860 0.0288
-7.500 -0.2181 0.09590 0.09280 -0.0565 0.9780 0.0291
-7.250 -0.1970 0.09017 0.08704 -0.0557 0.9768 0.0302
-7.000 -0.1724 0.08612 0.08298 -0.0593 0.9731 0.0317
-6.750 -0.1526 0.08258 0.07943 -0.0638 0.9639 0.0331
-6.500 -0.1231 0.07820 0.07503 -0.0716 0.9586 0.0351
-6.250 -0.0860 0.07395 0.07075 -0.0865 0.9468 0.0382
-6.000 -0.0551 0.06763 0.06441 -0.0981 0.9380 0.0397
-5.750 -0.0347 0.06429 0.06107 -0.0975 0.9340 0.0413
-5.500 -0.0053 0.06061 0.05735 -0.1028 0.9274 0.0434
-5.250 0.0293 0.05635 0.05303 -0.1111 0.9192 0.0466
-5.000 0.0975 0.05041 0.04666 -0.1330 0.9077 0.0510
-4.750 0.1144 0.04524 0.04158 -0.1339 0.9020 0.0528
-4.500 0.1365 0.04287 0.03918 -0.1349 0.8914 0.0552
-4.250 0.1911 0.03942 0.03510 -0.1458 0.8816 0.0642
-4.000 0.2147 0.03443 0.03016 -0.1483 0.8743 0.0666
-3.750 0.2396 0.03238 0.02806 -0.1492 0.8640 0.0701
-3.500 0.2785 0.02902 0.02424 -0.1540 0.8559 0.0809
-3.250 0.3071 0.02706 0.02217 -0.1551 0.8473 0.0858
-3.000 0.3399 0.02479 0.01959 -0.1574 0.8387 0.0976
-2.500 0.4236 0.01661 0.00950 -0.1604 0.8245 0.0384
-2.250 0.4544 0.01528 0.00789 -0.1607 0.8174 0.0384
-2.000 0.4834 0.01417 0.00664 -0.1608 0.8094 0.0396
-1.750 0.5135 0.01331 0.00573 -0.1612 0.8026 0.0443
-1.500 0.5427 0.01282 0.00523 -0.1615 0.7947 0.0591
-1.250 0.5750 0.01184 0.00471 -0.1626 0.7883 0.2076
-1.000 0.6031 0.01104 0.00489 -0.1633 0.7808 0.5196
-0.750 0.6193 0.01039 0.00495 -0.1601 0.7744 0.8109
-0.500 0.6414 0.01023 0.00478 -0.1584 0.7673 1.0000
-0.250 0.6704 0.01036 0.00470 -0.1586 0.7607 1.0000
0.000 0.6989 0.01053 0.00469 -0.1587 0.7543 1.0000
0.250 0.7271 0.01068 0.00471 -0.1588 0.7476 1.0000
0.500 0.7559 0.01084 0.00472 -0.1589 0.7419 1.0000
0.750 0.7833 0.01102 0.00482 -0.1589 0.7348 1.0000
1.000 0.8122 0.01118 0.00484 -0.1591 0.7295 1.0000
1.250 0.8393 0.01138 0.00500 -0.1590 0.7225 1.0000
1.500 0.8676 0.01154 0.00509 -0.1591 0.7167 1.0000
1.750 0.8952 0.01175 0.00525 -0.1591 0.7106 1.0000
2.000 0.9227 0.01193 0.00540 -0.1590 0.7041 1.0000
2.250 0.9512 0.01213 0.00551 -0.1591 0.6990 1.0000
2.500 0.9776 0.01233 0.00576 -0.1590 0.6917 1.0000
2.750 1.0059 0.01250 0.00587 -0.1590 0.6861 1.0000
3.000 1.0322 0.01272 0.00612 -0.1588 0.6788 1.0000
3.250 1.0600 0.01287 0.00623 -0.1587 0.6723 1.0000
3.500 1.0863 0.01307 0.00649 -0.1585 0.6646 1.0000
3.750 1.1140 0.01321 0.00661 -0.1583 0.6577 1.0000
4.000 1.1399 0.01340 0.00686 -0.1580 0.6495 1.0000
4.250 1.1677 0.01353 0.00695 -0.1579 0.6423 1.0000
4.500 1.1929 0.01369 0.00720 -0.1574 0.6329 1.0000
4.750 1.2199 0.01382 0.00737 -0.1571 0.6248 1.0000
5.000 1.2457 0.01395 0.00756 -0.1567 0.6155 1.0000
5.250 1.2711 0.01409 0.00779 -0.1562 0.6058 1.0000
5.500 1.2973 0.01420 0.00794 -0.1557 0.5960 1.0000
5.750 1.3226 0.01428 0.00809 -0.1551 0.5847 1.0000
6.000 1.3469 0.01440 0.00831 -0.1544 0.5724 1.0000
6.250 1.3711 0.01450 0.00851 -0.1536 0.5589 1.0000
6.500 1.3942 0.01454 0.00857 -0.1524 0.5402 1.0000
6.750 1.4145 0.01461 0.00867 -0.1508 0.5123 1.0000
7.000 1.4343 0.01484 0.00890 -0.1492 0.4812 1.0000
7.250 1.4529 0.01523 0.00925 -0.1475 0.4439 1.0000
7.500 1.4653 0.01603 0.00978 -0.1449 0.3816 1.0000
7.750 1.4720 0.01735 0.01067 -0.1416 0.3077 1.0000
8.000 1.4765 0.01893 0.01186 -0.1382 0.2431 1.0000
8.250 1.4796 0.02060 0.01318 -0.1347 0.1845 1.0000
8.500 1.4773 0.02248 0.01468 -0.1305 0.1255 1.0000
8.750 1.4648 0.02499 0.01669 -0.1250 0.0638 1.0000
9.000 1.4556 0.02749 0.01897 -0.1201 0.0390 1.0000
9.250 1.4556 0.02944 0.02100 -0.1168 0.0328 1.0000
9.500 1.4563 0.03144 0.02307 -0.1139 0.0292 1.0000
9.750 1.4537 0.03385 0.02561 -0.1111 0.0271 1.0000
10.000 1.4570 0.03588 0.02779 -0.1089 0.0257 1.0000
10.250 1.4589 0.03817 0.03021 -0.1069 0.0246 1.0000
10.500 1.4609 0.04057 0.03272 -0.1051 0.0237 1.0000
10.750 1.4633 0.04305 0.03530 -0.1034 0.0229 1.0000
11.000 1.4664 0.04557 0.03792 -0.1018 0.0222 1.0000
11.250 1.4710 0.04813 0.04055 -0.1002 0.0216 1.0000
11.500 1.4796 0.05065 0.04313 -0.0986 0.0210 1.0000
11.750 1.4984 0.05304 0.04561 -0.0969 0.0206 1.0000
12.000 1.5249 0.05590 0.04868 -0.0957 0.0202 1.0000
12.250 1.5310 0.05842 0.05146 -0.0944 0.0199 1.0000
12.500 1.5361 0.06124 0.05454 -0.0932 0.0195 1.0000
12.750 1.5399 0.06449 0.05807 -0.0921 0.0192 1.0000
13.000 1.5418 0.06842 0.06231 -0.0909 0.0192 1.0000
13.250 1.5392 0.07280 0.06700 -0.0900 0.0193 1.0000
13.500 1.5321 0.07758 0.07208 -0.0893 0.0194 1.0000
13.750 1.5215 0.08277 0.07757 -0.0890 0.0195 1.0000
14.000 1.5084 0.08843 0.08350 -0.0892 0.0197 1.0000
14.250 1.4932 0.09437 0.08971 -0.0899 0.0198 1.0000
14.500 1.4764 0.10107 0.09666 -0.0911 0.0200 1.0000
14.750 1.4700 0.10651 0.10229 -0.0920 0.0204 1.0000
15.000 1.4581 0.11136 0.10735 -0.0940 0.0206 1.0000
15.250 1.4415 0.11750 0.11373 -0.0968 0.0209 1.0000
15.500 1.4214 0.12483 0.12134 -0.1009 0.0212 1.0000
15.750 1.3894 0.13553 0.13238 -0.1078 0.0219 1.0000
16.000 1.3537 0.14869 0.14585 -0.1172 0.0224 1.0000
|
Polar data table (+)
Polar graphs
<< Back to E385 (8.41%) (e385-il)