E178 (8.69%) (e178-il) Xfoil prediction polar at RE=100,000 Ncrit=5
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Airfoil: E178 (8.69%) (e178-il) Reynolds number: 100,000 Max Cl/Cd: 55.81 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e178-il-100000-n5.txt Download as CSV file: xf-e178-il-100000-n5.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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.3799 0.07709 0.07293 -0.0228 1.0000 0.0300
-8.000 -0.4552 0.08207 0.07773 -0.0250 1.0000 0.0308
-7.750 -0.4483 0.07900 0.07466 -0.0243 1.0000 0.0291
-7.500 -0.4453 0.07459 0.07029 -0.0275 1.0000 0.0285
-7.250 -0.4410 0.06966 0.06539 -0.0316 1.0000 0.0278
-7.000 -0.4351 0.06444 0.06015 -0.0358 1.0000 0.0272
-6.750 -0.4278 0.05888 0.05452 -0.0397 1.0000 0.0267
-6.500 -0.4193 0.05327 0.04877 -0.0429 1.0000 0.0261
-6.250 -0.4106 0.04793 0.04323 -0.0450 1.0000 0.0258
-6.000 -0.3896 0.04177 0.03664 -0.0488 0.9785 0.0257
-5.750 -0.3603 0.03617 0.03042 -0.0526 0.9569 0.0265
-5.500 -0.3301 0.03213 0.02559 -0.0547 0.9387 0.0294
-5.250 -0.3017 0.02886 0.02165 -0.0556 0.9220 0.0299
-5.000 -0.2742 0.02629 0.01848 -0.0558 0.9065 0.0303
-4.750 -0.2485 0.02369 0.01546 -0.0556 0.8922 0.0312
-4.500 -0.2230 0.02192 0.01342 -0.0552 0.8788 0.0326
-4.250 -0.1974 0.02072 0.01195 -0.0546 0.8660 0.0346
-4.000 -0.1718 0.01995 0.01096 -0.0541 0.8540 0.0394
-3.750 -0.1462 0.01897 0.00975 -0.0532 0.8432 0.0415
-3.500 -0.1214 0.01803 0.00866 -0.0524 0.8328 0.0430
-3.250 -0.0968 0.01718 0.00772 -0.0517 0.8222 0.0461
-3.000 -0.0714 0.01657 0.00697 -0.0510 0.8125 0.0517
-2.750 -0.0461 0.01592 0.00625 -0.0503 0.8040 0.0654
-2.500 -0.0209 0.01523 0.00569 -0.0498 0.7945 0.1137
-2.250 0.0032 0.01441 0.00544 -0.0495 0.7861 0.2439
-2.000 0.0253 0.01335 0.00531 -0.0487 0.7784 0.4728
-1.750 0.0462 0.01261 0.00524 -0.0467 0.7700 0.6705
-1.500 0.0934 0.01203 0.00502 -0.0488 0.7640 0.9152
-1.250 0.1475 0.01195 0.00468 -0.0541 0.7561 1.0000
-1.000 0.1719 0.01203 0.00452 -0.0534 0.7492 1.0000
-0.750 0.1971 0.01213 0.00444 -0.0530 0.7409 1.0000
-0.500 0.2220 0.01224 0.00434 -0.0524 0.7341 1.0000
-0.250 0.2474 0.01235 0.00431 -0.0519 0.7265 1.0000
0.000 0.2728 0.01247 0.00428 -0.0514 0.7199 1.0000
0.250 0.2985 0.01260 0.00430 -0.0510 0.7126 1.0000
0.500 0.3242 0.01274 0.00431 -0.0506 0.7063 1.0000
0.750 0.3501 0.01289 0.00438 -0.0502 0.6991 1.0000
1.000 0.3760 0.01303 0.00444 -0.0498 0.6931 1.0000
1.250 0.4021 0.01320 0.00457 -0.0495 0.6859 1.0000
1.500 0.4281 0.01335 0.00464 -0.0491 0.6801 1.0000
1.750 0.4543 0.01353 0.00482 -0.0489 0.6727 1.0000
2.000 0.4805 0.01368 0.00492 -0.0484 0.6672 1.0000
2.250 0.5067 0.01389 0.00517 -0.0482 0.6594 1.0000
2.500 0.5329 0.01405 0.00530 -0.0478 0.6536 1.0000
2.750 0.5590 0.01426 0.00556 -0.0476 0.6454 1.0000
3.000 0.5852 0.01441 0.00572 -0.0471 0.6387 1.0000
3.250 0.6111 0.01459 0.00599 -0.0468 0.6295 1.0000
3.500 0.6370 0.01476 0.00621 -0.0463 0.6205 1.0000
3.750 0.6631 0.01488 0.00635 -0.0458 0.6122 1.0000
4.000 0.6887 0.01504 0.00660 -0.0453 0.6011 1.0000
4.250 0.7144 0.01517 0.00682 -0.0448 0.5895 1.0000
4.500 0.7399 0.01529 0.00708 -0.0443 0.5770 1.0000
4.750 0.7653 0.01539 0.00728 -0.0436 0.5634 1.0000
5.000 0.7906 0.01549 0.00748 -0.0430 0.5483 1.0000
5.250 0.8158 0.01558 0.00767 -0.0423 0.5317 1.0000
5.500 0.8405 0.01571 0.00792 -0.0416 0.5112 1.0000
5.750 0.8649 0.01584 0.00813 -0.0407 0.4872 1.0000
6.000 0.8886 0.01603 0.00849 -0.0399 0.4564 1.0000
6.250 0.9113 0.01633 0.00879 -0.0389 0.4149 1.0000
6.500 0.9320 0.01685 0.00916 -0.0377 0.3566 1.0000
6.750 0.9490 0.01782 0.00979 -0.0363 0.2845 1.0000
7.000 0.9643 0.01912 0.01076 -0.0350 0.2181 1.0000
7.250 0.9791 0.02050 0.01186 -0.0337 0.1623 1.0000
7.500 0.9924 0.02202 0.01306 -0.0324 0.1109 1.0000
7.750 1.0047 0.02361 0.01429 -0.0310 0.0645 1.0000
8.000 1.0165 0.02527 0.01576 -0.0294 0.0390 1.0000
8.250 1.0275 0.02698 0.01751 -0.0275 0.0287 1.0000
8.500 1.0365 0.02880 0.01954 -0.0254 0.0241 1.0000
8.750 1.0478 0.03029 0.02117 -0.0237 0.0206 1.0000
9.000 1.0548 0.03210 0.02305 -0.0218 0.0180 1.0000
9.250 1.0620 0.03383 0.02494 -0.0197 0.0166 1.0000
9.500 1.0696 0.03568 0.02696 -0.0177 0.0158 1.0000
9.750 1.0783 0.03768 0.02914 -0.0160 0.0150 1.0000
10.000 1.0879 0.03984 0.03149 -0.0144 0.0144 1.0000
10.250 1.0973 0.04217 0.03403 -0.0130 0.0139 1.0000
10.500 1.1052 0.04469 0.03678 -0.0117 0.0135 1.0000
10.750 1.1105 0.04744 0.03978 -0.0105 0.0132 1.0000
11.000 1.1131 0.05036 0.04295 -0.0095 0.0130 1.0000
11.250 1.1117 0.05362 0.04647 -0.0086 0.0127 1.0000
11.500 1.1081 0.05708 0.05020 -0.0082 0.0127 1.0000
11.750 1.1013 0.06093 0.05431 -0.0081 0.0126 1.0000
12.000 1.0917 0.06517 0.05881 -0.0086 0.0126 1.0000
12.250 1.0797 0.06987 0.06383 -0.0097 0.0126 1.0000
12.500 1.0655 0.07513 0.06933 -0.0114 0.0126 1.0000
12.750 1.0497 0.08092 0.07536 -0.0139 0.0127 1.0000
13.000 1.0313 0.08755 0.08214 -0.0173 0.0127 1.0000
13.250 1.0111 0.09514 0.08995 -0.0217 0.0129 1.0000
13.500 0.9891 0.10391 0.09891 -0.0272 0.0131 1.0000
13.750 0.9636 0.11495 0.11013 -0.0345 0.0134 1.0000
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Polar data table (+)
Polar graphs
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