E178 (8.69%) (e178-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: E178 (8.69%) (e178-il) Reynolds number: 200,000 Max Cl/Cd: 77.22 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e178-il-200000.txt Download as CSV file: xf-e178-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: E178 (8.69%)
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
------ -------- --------- --------- -------- -------- --------
-8.250 -0.4401 0.08968 0.08651 -0.0141 1.0000 0.0419
-8.000 -0.4414 0.08597 0.08286 -0.0182 1.0000 0.0434
-7.750 -0.4458 0.08206 0.07904 -0.0243 1.0000 0.0442
-7.250 -0.4348 0.07185 0.06870 -0.0384 1.0000 0.0448
-7.000 -0.4345 0.06515 0.06210 -0.0392 1.0000 0.0461
-6.750 -0.4236 0.06290 0.05990 -0.0375 1.0000 0.0477
-6.500 -0.4120 0.05970 0.05669 -0.0388 1.0000 0.0499
-6.250 -0.4011 0.05570 0.05265 -0.0416 1.0000 0.0526
-6.000 -0.3800 0.04791 0.04432 -0.0507 0.9847 0.0590
-5.750 -0.3487 0.04549 0.04206 -0.0530 0.9717 0.0642
-5.500 -0.3163 0.03961 0.03559 -0.0589 0.9533 0.0731
-5.250 -0.2897 0.03685 0.03277 -0.0602 0.9359 0.0770
-5.000 -0.2637 0.02775 0.02231 -0.0592 0.9187 0.0436
-4.750 -0.2439 0.02379 0.01786 -0.0579 0.9033 0.0401
-4.500 -0.2213 0.02184 0.01546 -0.0565 0.8891 0.0415
-4.250 -0.1977 0.01985 0.01303 -0.0552 0.8762 0.0416
-4.000 -0.1730 0.01814 0.01095 -0.0540 0.8644 0.0415
-3.750 -0.1478 0.01685 0.00937 -0.0529 0.8535 0.0425
-3.500 -0.1225 0.01600 0.00831 -0.0519 0.8437 0.0443
-3.250 -0.0980 0.01474 0.00699 -0.0511 0.8335 0.0483
-3.000 -0.0726 0.01399 0.00620 -0.0504 0.8239 0.0517
-2.750 -0.0472 0.01343 0.00550 -0.0496 0.8155 0.0571
-2.500 -0.0220 0.01258 0.00470 -0.0489 0.8064 0.0788
-2.250 0.0011 0.01135 0.00427 -0.0485 0.7981 0.2584
-2.000 0.0235 0.01058 0.00412 -0.0476 0.7905 0.4400
-1.750 0.0420 0.00970 0.00412 -0.0456 0.7822 0.6736
-1.500 0.1044 0.00904 0.00398 -0.0508 0.7765 0.9801
-1.250 0.1468 0.00905 0.00378 -0.0539 0.7685 1.0000
-1.000 0.1711 0.00913 0.00366 -0.0532 0.7618 1.0000
-0.750 0.1966 0.00922 0.00361 -0.0528 0.7536 1.0000
-0.500 0.2214 0.00932 0.00354 -0.0521 0.7474 1.0000
-0.250 0.2472 0.00942 0.00355 -0.0518 0.7394 1.0000
0.000 0.2724 0.00954 0.00352 -0.0511 0.7335 1.0000
0.250 0.2985 0.00965 0.00357 -0.0509 0.7257 1.0000
0.500 0.3242 0.00978 0.00357 -0.0503 0.7200 1.0000
0.750 0.3505 0.00991 0.00366 -0.0501 0.7125 1.0000
1.000 0.3764 0.01004 0.00369 -0.0496 0.7067 1.0000
1.250 0.4029 0.01018 0.00382 -0.0494 0.6994 1.0000
1.500 0.4291 0.01031 0.00388 -0.0490 0.6934 1.0000
1.750 0.4556 0.01046 0.00403 -0.0487 0.6863 1.0000
2.000 0.4820 0.01059 0.00411 -0.0484 0.6799 1.0000
2.250 0.5084 0.01074 0.00426 -0.0481 0.6725 1.0000
2.500 0.5348 0.01085 0.00434 -0.0477 0.6653 1.0000
2.750 0.5612 0.01098 0.00449 -0.0474 0.6567 1.0000
3.000 0.5876 0.01109 0.00454 -0.0469 0.6500 1.0000
3.250 0.6140 0.01119 0.00471 -0.0466 0.6403 1.0000
3.500 0.6404 0.01129 0.00484 -0.0462 0.6315 1.0000
3.750 0.6668 0.01136 0.00489 -0.0457 0.6227 1.0000
4.000 0.6931 0.01143 0.00502 -0.0453 0.6118 1.0000
4.250 0.7194 0.01150 0.00514 -0.0448 0.6011 1.0000
4.500 0.7457 0.01155 0.00525 -0.0444 0.5903 1.0000
4.750 0.7719 0.01158 0.00533 -0.0439 0.5784 1.0000
5.000 0.7979 0.01160 0.00541 -0.0433 0.5645 1.0000
5.250 0.8238 0.01162 0.00551 -0.0428 0.5487 1.0000
5.500 0.8495 0.01165 0.00564 -0.0422 0.5307 1.0000
5.750 0.8750 0.01170 0.00574 -0.0416 0.5106 1.0000
6.000 0.9000 0.01180 0.00589 -0.0409 0.4843 1.0000
6.250 0.9243 0.01197 0.00610 -0.0402 0.4473 1.0000
6.500 0.9463 0.01239 0.00636 -0.0392 0.3872 1.0000
6.750 0.9618 0.01361 0.00697 -0.0378 0.2752 1.0000
7.000 0.9753 0.01525 0.00802 -0.0365 0.1749 1.0000
7.250 0.9913 0.01662 0.00904 -0.0354 0.1134 1.0000
7.500 1.0014 0.01873 0.01068 -0.0334 0.0491 1.0000
7.750 1.0109 0.02081 0.01265 -0.0312 0.0303 1.0000
8.000 1.0268 0.02205 0.01402 -0.0296 0.0257 1.0000
8.250 1.0401 0.02352 0.01555 -0.0278 0.0232 1.0000
8.500 1.0493 0.02570 0.01778 -0.0256 0.0215 1.0000
8.750 1.0640 0.02809 0.02026 -0.0239 0.0207 1.0000
9.000 1.0834 0.03006 0.02239 -0.0227 0.0202 1.0000
9.250 1.1034 0.03244 0.02501 -0.0216 0.0199 1.0000
9.500 1.1215 0.03491 0.02776 -0.0204 0.0196 1.0000
9.750 1.1358 0.03687 0.02999 -0.0190 0.0184 1.0000
10.000 1.1474 0.03937 0.03278 -0.0174 0.0178 1.0000
10.250 1.1546 0.04238 0.03613 -0.0156 0.0176 1.0000
10.500 1.1550 0.04596 0.04008 -0.0133 0.0178 1.0000
10.750 1.1484 0.04931 0.04376 -0.0106 0.0181 1.0000
11.000 1.1374 0.05286 0.04759 -0.0083 0.0185 1.0000
11.250 1.1235 0.05672 0.05171 -0.0068 0.0188 1.0000
11.500 1.1082 0.06083 0.05606 -0.0062 0.0190 1.0000
11.750 1.0913 0.06537 0.06081 -0.0065 0.0193 1.0000
12.000 1.0730 0.07038 0.06603 -0.0076 0.0195 1.0000
12.250 1.0540 0.07592 0.07173 -0.0095 0.0198 1.0000
12.500 1.0345 0.08187 0.07786 -0.0123 0.0199 1.0000
12.750 1.0144 0.08857 0.08469 -0.0158 0.0202 1.0000
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Polar data table (+)
Polar graphs
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