E176 (8.83%) (e176-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: E176 (8.83%) (e176-il) Reynolds number: 100,000 Max Cl/Cd: 58.89 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e176-il-100000-n5.txt Download as CSV file: xf-e176-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: E176 (8.83%)
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 -0.3861 0.09238 0.08774 -0.0239 1.0000 0.0560
-8.000 -0.3845 0.08898 0.08440 -0.0259 1.0000 0.0566
-7.750 -0.3976 0.08599 0.08158 -0.0340 1.0000 0.0594
-7.500 -0.3941 0.08170 0.07732 -0.0396 1.0000 0.0597
-7.000 -0.3817 0.06964 0.06529 -0.0407 1.0000 0.0330
-6.750 -0.3773 0.06577 0.06146 -0.0426 1.0000 0.0319
-6.500 -0.3755 0.06177 0.05748 -0.0444 1.0000 0.0309
-6.250 -0.3489 0.05453 0.05005 -0.0533 0.9787 0.0290
-6.000 -0.3189 0.04298 0.03772 -0.0636 0.9578 0.0259
-5.750 -0.2886 0.03837 0.03255 -0.0674 0.9423 0.0253
-5.500 -0.2612 0.03427 0.02791 -0.0698 0.9270 0.0252
-5.250 -0.2338 0.03084 0.02394 -0.0713 0.9123 0.0251
-5.000 -0.2078 0.02795 0.02061 -0.0721 0.8983 0.0264
-4.750 -0.1814 0.02640 0.01881 -0.0725 0.8851 0.0283
-4.500 -0.1550 0.02453 0.01652 -0.0724 0.8723 0.0293
-4.250 -0.1287 0.02271 0.01429 -0.0719 0.8600 0.0296
-4.000 -0.1023 0.02122 0.01247 -0.0714 0.8484 0.0301
-3.750 -0.0761 0.01996 0.01092 -0.0708 0.8376 0.0309
-3.500 -0.0501 0.01891 0.00967 -0.0701 0.8277 0.0320
-3.250 -0.0243 0.01804 0.00864 -0.0695 0.8175 0.0334
-3.000 0.0013 0.01726 0.00771 -0.0689 0.8077 0.0356
-2.750 0.0274 0.01666 0.00701 -0.0685 0.7989 0.0415
-2.500 0.0537 0.01606 0.00634 -0.0680 0.7899 0.0545
-2.250 0.0796 0.01528 0.00573 -0.0676 0.7814 0.1033
-2.000 0.1044 0.01445 0.00547 -0.0674 0.7737 0.2439
-1.750 0.1275 0.01351 0.00539 -0.0668 0.7652 0.4692
-1.500 0.1468 0.01269 0.00531 -0.0642 0.7587 0.7037
-1.250 0.1991 0.01212 0.00501 -0.0678 0.7509 0.9770
-1.000 0.2302 0.01218 0.00478 -0.0685 0.7443 1.0000
-0.750 0.2561 0.01229 0.00468 -0.0681 0.7361 1.0000
-0.500 0.2820 0.01241 0.00457 -0.0677 0.7297 1.0000
-0.250 0.3082 0.01254 0.00455 -0.0674 0.7219 1.0000
0.000 0.3344 0.01266 0.00449 -0.0670 0.7158 1.0000
0.250 0.3607 0.01281 0.00453 -0.0668 0.7082 1.0000
0.500 0.3871 0.01295 0.00451 -0.0664 0.7025 1.0000
0.750 0.4135 0.01311 0.00461 -0.0662 0.6950 1.0000
1.000 0.4400 0.01326 0.00465 -0.0659 0.6892 1.0000
1.250 0.4665 0.01344 0.00478 -0.0657 0.6822 1.0000
1.500 0.4930 0.01361 0.00487 -0.0654 0.6761 1.0000
1.750 0.5195 0.01380 0.00503 -0.0652 0.6696 1.0000
2.000 0.5461 0.01398 0.00519 -0.0649 0.6631 1.0000
2.250 0.5726 0.01417 0.00536 -0.0646 0.6570 1.0000
2.500 0.5990 0.01437 0.00557 -0.0644 0.6500 1.0000
2.750 0.6256 0.01456 0.00575 -0.0641 0.6440 1.0000
3.000 0.6519 0.01478 0.00603 -0.0639 0.6364 1.0000
3.250 0.6784 0.01496 0.00623 -0.0636 0.6298 1.0000
3.500 0.7044 0.01516 0.00649 -0.0632 0.6213 1.0000
3.750 0.7305 0.01535 0.00673 -0.0629 0.6130 1.0000
4.000 0.7568 0.01550 0.00694 -0.0624 0.6045 1.0000
4.250 0.7824 0.01568 0.00722 -0.0620 0.5939 1.0000
4.500 0.8081 0.01583 0.00745 -0.0615 0.5832 1.0000
4.750 0.8338 0.01595 0.00765 -0.0609 0.5720 1.0000
5.000 0.8593 0.01607 0.00790 -0.0603 0.5600 1.0000
5.250 0.8846 0.01620 0.00813 -0.0597 0.5463 1.0000
5.500 0.9094 0.01633 0.00841 -0.0590 0.5302 1.0000
5.750 0.9339 0.01646 0.00867 -0.0583 0.5118 1.0000
6.000 0.9582 0.01659 0.00888 -0.0574 0.4915 1.0000
6.250 0.9817 0.01679 0.00924 -0.0566 0.4659 1.0000
6.500 1.0040 0.01705 0.00956 -0.0555 0.4299 1.0000
6.750 1.0222 0.01757 0.00982 -0.0538 0.3602 1.0000
7.000 1.0344 0.01883 0.01050 -0.0518 0.2683 1.0000
7.250 1.0448 0.02047 0.01162 -0.0500 0.1884 1.0000
7.500 1.0552 0.02214 0.01285 -0.0483 0.1221 1.0000
7.750 1.0648 0.02389 0.01418 -0.0466 0.0663 1.0000
8.000 1.0740 0.02565 0.01573 -0.0446 0.0360 1.0000
8.250 1.0854 0.02714 0.01727 -0.0427 0.0274 1.0000
8.500 1.0955 0.02868 0.01892 -0.0406 0.0239 1.0000
8.750 1.1052 0.03014 0.02055 -0.0387 0.0218 1.0000
9.000 1.1118 0.03165 0.02220 -0.0364 0.0204 1.0000
9.250 1.1169 0.03327 0.02394 -0.0342 0.0195 1.0000
9.500 1.1199 0.03519 0.02598 -0.0321 0.0188 1.0000
9.750 1.1238 0.03723 0.02812 -0.0302 0.0181 1.0000
10.000 1.1316 0.03909 0.03017 -0.0287 0.0173 1.0000
10.250 1.1400 0.04098 0.03223 -0.0275 0.0163 1.0000
10.750 1.1553 0.04513 0.03674 -0.0253 0.0147 1.0000
11.000 1.1626 0.04746 0.03923 -0.0243 0.0143 1.0000
11.250 1.1691 0.05003 0.04197 -0.0234 0.0140 1.0000
11.500 1.1744 0.05276 0.04490 -0.0226 0.0138 1.0000
11.750 1.1778 0.05578 0.04813 -0.0219 0.0136 1.0000
12.000 1.1789 0.05907 0.05164 -0.0214 0.0135 1.0000
12.250 1.1769 0.06272 0.05552 -0.0212 0.0134 1.0000
12.500 1.1721 0.06674 0.05980 -0.0214 0.0133 1.0000
12.750 1.1645 0.07108 0.06439 -0.0220 0.0133 1.0000
13.000 1.1547 0.07581 0.06938 -0.0231 0.0133 1.0000
13.250 1.1428 0.08092 0.07474 -0.0247 0.0133 1.0000
13.500 1.1294 0.08647 0.08054 -0.0269 0.0133 1.0000
13.750 1.1132 0.09279 0.08709 -0.0299 0.0133 1.0000
14.000 1.0959 0.09975 0.09429 -0.0337 0.0135 1.0000
14.250 1.0765 0.10784 0.10262 -0.0385 0.0136 1.0000
14.500 1.0535 0.11770 0.11272 -0.0448 0.0138 1.0000
14.750 1.0248 0.13068 0.12592 -0.0534 0.0141 1.0000
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Polar data table (+)
Polar graphs
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