EPPLER 398 AIRFOIL (e398-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 398 AIRFOIL (e398-il) Reynolds number: 200,000 Max Cl/Cd: 86.68 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e398-il-200000-n5.txt Download as CSV file: xf-e398-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 398 AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-12.000 -0.3982 0.08445 0.08083 -0.0748 0.9909 0.0122
-11.750 -0.4420 0.06906 0.06521 -0.0871 0.9832 0.0116
-11.250 -0.4740 0.05173 0.04749 -0.1040 0.9571 0.0114
-11.000 -0.4753 0.04488 0.04043 -0.1128 0.9443 0.0114
-10.750 -0.4687 0.03869 0.03400 -0.1225 0.9312 0.0118
-10.500 -0.4558 0.03357 0.02858 -0.1319 0.9171 0.0121
-10.250 -0.4364 0.03018 0.02482 -0.1382 0.9050 0.0131
-10.000 -0.4145 0.02786 0.02227 -0.1418 0.8947 0.0137
-9.750 -0.3911 0.02610 0.02032 -0.1444 0.8846 0.0145
-9.500 -0.3694 0.02458 0.01860 -0.1457 0.8741 0.0154
-9.250 -0.3454 0.02313 0.01690 -0.1471 0.8653 0.0166
-9.000 -0.3229 0.02197 0.01560 -0.1478 0.8556 0.0179
-8.750 -0.2985 0.02093 0.01436 -0.1484 0.8470 0.0198
-8.500 -0.2737 0.02006 0.01335 -0.1490 0.8384 0.0227
-8.250 -0.2488 0.01926 0.01242 -0.1494 0.8303 0.0262
-8.000 -0.2231 0.01853 0.01156 -0.1497 0.8226 0.0305
-7.750 -0.1971 0.01794 0.01084 -0.1500 0.8153 0.0356
-7.500 -0.1711 0.01737 0.01016 -0.1503 0.8076 0.0411
-7.250 -0.1444 0.01684 0.00955 -0.1506 0.8008 0.0474
-7.000 -0.1181 0.01636 0.00900 -0.1507 0.7934 0.0543
-6.500 -0.0640 0.01557 0.00799 -0.1511 0.7804 0.0702
-6.250 -0.0365 0.01517 0.00754 -0.1514 0.7741 0.0793
-6.000 -0.0092 0.01482 0.00713 -0.1516 0.7679 0.0891
-5.750 0.0182 0.01451 0.00676 -0.1518 0.7616 0.1000
-5.500 0.0465 0.01424 0.00640 -0.1521 0.7565 0.1120
-5.250 0.0738 0.01399 0.00612 -0.1522 0.7503 0.1252
-5.000 0.1017 0.01376 0.00585 -0.1524 0.7444 0.1398
-4.750 0.1301 0.01356 0.00559 -0.1527 0.7396 0.1554
-4.500 0.1576 0.01338 0.00540 -0.1528 0.7337 0.1714
-4.250 0.1857 0.01321 0.00521 -0.1530 0.7285 0.1882
-4.000 0.2144 0.01308 0.00502 -0.1533 0.7240 0.2058
-3.750 0.2419 0.01295 0.00491 -0.1534 0.7182 0.2236
-3.500 0.2701 0.01285 0.00478 -0.1535 0.7132 0.2418
-3.250 0.2988 0.01277 0.00466 -0.1538 0.7090 0.2599
-3.000 0.3266 0.01270 0.00459 -0.1539 0.7040 0.2778
-2.750 0.3546 0.01265 0.00451 -0.1540 0.6989 0.2956
-2.500 0.3831 0.01260 0.00444 -0.1541 0.6946 0.3135
-2.250 0.4114 0.01257 0.00440 -0.1543 0.6904 0.3310
-2.000 0.4391 0.01253 0.00438 -0.1544 0.6855 0.3484
-1.750 0.4673 0.01251 0.00436 -0.1545 0.6810 0.3667
-1.500 0.4960 0.01250 0.00432 -0.1547 0.6773 0.3847
-1.250 0.5236 0.01250 0.00436 -0.1547 0.6727 0.4030
-1.000 0.5513 0.01250 0.00439 -0.1548 0.6681 0.4219
-0.750 0.5795 0.01250 0.00439 -0.1549 0.6640 0.4414
-0.500 0.6080 0.01253 0.00441 -0.1550 0.6604 0.4615
-0.250 0.6351 0.01254 0.00450 -0.1550 0.6558 0.4815
0.000 0.6626 0.01256 0.00457 -0.1550 0.6514 0.5030
0.250 0.6907 0.01259 0.00462 -0.1550 0.6476 0.5257
0.500 0.7185 0.01263 0.00470 -0.1551 0.6439 0.5489
0.750 0.7453 0.01267 0.00484 -0.1549 0.6393 0.5731
1.000 0.7723 0.01271 0.00494 -0.1548 0.6350 0.5979
1.250 0.7999 0.01276 0.00503 -0.1547 0.6314 0.6244
1.500 0.8265 0.01281 0.00516 -0.1545 0.6274 0.6509
1.750 0.8522 0.01286 0.00533 -0.1541 0.6228 0.6790
2.000 0.8781 0.01291 0.00546 -0.1537 0.6187 0.7086
2.250 0.9043 0.01297 0.00556 -0.1532 0.6151 0.7402
2.500 0.9284 0.01302 0.00574 -0.1524 0.6108 0.7735
2.750 0.9511 0.01306 0.00590 -0.1513 0.6062 0.8107
3.000 0.9728 0.01307 0.00600 -0.1498 0.6020 0.8553
3.250 0.9948 0.01302 0.00601 -0.1484 0.5984 0.9268
3.500 1.0226 0.01312 0.00617 -0.1486 0.5933 1.0000
3.750 1.0497 0.01329 0.00635 -0.1486 0.5884 1.0000
4.000 1.0778 0.01345 0.00648 -0.1488 0.5841 1.0000
4.250 1.1042 0.01364 0.00669 -0.1487 0.5792 1.0000
4.500 1.1300 0.01382 0.00691 -0.1485 0.5736 1.0000
4.750 1.1572 0.01398 0.00707 -0.1484 0.5686 1.0000
5.000 1.1825 0.01418 0.00731 -0.1481 0.5628 1.0000
5.250 1.2075 0.01436 0.00754 -0.1477 0.5566 1.0000
5.500 1.2339 0.01454 0.00770 -0.1475 0.5509 1.0000
5.750 1.2569 0.01475 0.00800 -0.1468 0.5433 1.0000
6.000 1.2821 0.01493 0.00817 -0.1464 0.5366 1.0000
6.250 1.3045 0.01515 0.00849 -0.1455 0.5285 1.0000
6.500 1.3285 0.01535 0.00869 -0.1449 0.5211 1.0000
6.750 1.3498 0.01559 0.00902 -0.1439 0.5117 1.0000
7.000 1.3713 0.01582 0.00927 -0.1428 0.5023 1.0000
7.250 1.3914 0.01608 0.00958 -0.1415 0.4917 1.0000
7.500 1.4104 0.01636 0.00992 -0.1400 0.4804 1.0000
7.750 1.4284 0.01668 0.01027 -0.1384 0.4684 1.0000
8.000 1.4442 0.01703 0.01064 -0.1364 0.4551 1.0000
8.250 1.4570 0.01743 0.01105 -0.1338 0.4406 1.0000
8.500 1.4683 0.01791 0.01153 -0.1311 0.4246 1.0000
8.750 1.4778 0.01849 0.01210 -0.1282 0.4068 1.0000
9.000 1.4852 0.01919 0.01277 -0.1250 0.3875 1.0000
9.250 1.4896 0.02008 0.01359 -0.1216 0.3669 1.0000
9.500 1.4926 0.02112 0.01458 -0.1182 0.3441 1.0000
9.750 1.4922 0.02242 0.01580 -0.1147 0.3211 1.0000
10.000 1.4912 0.02390 0.01720 -0.1113 0.2971 1.0000
10.250 1.4886 0.02562 0.01883 -0.1081 0.2746 1.0000
10.500 1.4863 0.02748 0.02062 -0.1052 0.2521 1.0000
10.750 1.4826 0.02957 0.02263 -0.1025 0.2312 1.0000
11.000 1.4804 0.03172 0.02472 -0.1002 0.2107 1.0000
11.250 1.4777 0.03402 0.02698 -0.0980 0.1918 1.0000
11.500 1.4749 0.03646 0.02937 -0.0961 0.1744 1.0000
11.750 1.4733 0.03891 0.03178 -0.0945 0.1582 1.0000
12.000 1.4723 0.04140 0.03425 -0.0930 0.1432 1.0000
12.250 1.4714 0.04399 0.03682 -0.0918 0.1293 1.0000
12.500 1.4706 0.04667 0.03949 -0.0906 0.1166 1.0000
13.000 1.4703 0.05214 0.04496 -0.0889 0.0939 1.0000
13.250 1.4706 0.05495 0.04780 -0.0882 0.0839 1.0000
13.500 1.4707 0.05787 0.05074 -0.0876 0.0749 1.0000
13.750 1.4702 0.06093 0.05381 -0.0871 0.0669 1.0000
14.000 1.4699 0.06405 0.05696 -0.0868 0.0595 1.0000
14.250 1.4707 0.06711 0.06007 -0.0866 0.0529 1.0000
14.500 1.4699 0.07043 0.06342 -0.0864 0.0474 1.0000
14.750 1.4698 0.07373 0.06678 -0.0864 0.0425 1.0000
15.000 1.4697 0.07711 0.07023 -0.0865 0.0384 1.0000
15.250 1.4687 0.08068 0.07387 -0.0867 0.0347 1.0000
15.500 1.4681 0.08424 0.07752 -0.0871 0.0316 1.0000
15.750 1.4671 0.08794 0.08129 -0.0875 0.0288 1.0000
16.000 1.4653 0.09181 0.08525 -0.0881 0.0266 1.0000
16.250 1.4646 0.09559 0.08914 -0.0888 0.0245 1.0000
16.500 1.4613 0.09980 0.09342 -0.0897 0.0228 1.0000
16.750 1.4601 0.10375 0.09749 -0.0905 0.0211 1.0000
17.000 1.4583 0.10783 0.10169 -0.0916 0.0196 1.0000
17.250 1.4542 0.11234 0.10628 -0.0930 0.0185 1.0000
17.500 1.4520 0.11660 0.11067 -0.0943 0.0173 1.0000
17.750 1.4500 0.12083 0.11503 -0.0957 0.0161 1.0000
18.000 1.4466 0.12536 0.11966 -0.0975 0.0152 1.0000
18.250 1.4421 0.13013 0.12452 -0.0994 0.0144 1.0000
18.500 1.4399 0.13452 0.12906 -0.1012 0.0135 1.0000
18.750 1.4370 0.13907 0.13374 -0.1033 0.0128 1.0000
19.000 1.4334 0.14379 0.13856 -0.1056 0.0122 1.0000
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Polar data table (+)
Polar graphs
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