EPPLER 479 AIRFOIL (e479-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 479 AIRFOIL (e479-il) Reynolds number: 500,000 Max Cl/Cd: 74.14 at α=8.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e479-il-500000-n5.txt Download as CSV file: xf-e479-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 479 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-18.250 -1.1777 0.08978 0.08514 -0.0153 1.0000 0.0345
-18.000 -1.1893 0.08466 0.07995 -0.0176 1.0000 0.0357
-17.750 -1.1992 0.07990 0.07511 -0.0197 1.0000 0.0366
-17.500 -1.2082 0.07534 0.07047 -0.0216 1.0000 0.0381
-17.250 -1.2173 0.07085 0.06589 -0.0234 1.0000 0.0391
-17.000 -1.2287 0.06616 0.06113 -0.0253 1.0000 0.0401
-16.750 -1.2400 0.06157 0.05646 -0.0271 1.0000 0.0413
-16.500 -1.2495 0.05735 0.05217 -0.0286 1.0000 0.0424
-16.250 -1.2576 0.05343 0.04816 -0.0300 1.0000 0.0439
-16.000 -1.2650 0.04967 0.04431 -0.0311 1.0000 0.0453
-15.750 -1.2731 0.04587 0.04044 -0.0323 1.0000 0.0465
-15.500 -1.2791 0.04239 0.03688 -0.0333 1.0000 0.0480
-15.250 -1.2820 0.03931 0.03373 -0.0340 1.0000 0.0496
-15.000 -1.2825 0.03658 0.03091 -0.0345 1.0000 0.0514
-14.750 -1.2847 0.03375 0.02803 -0.0350 1.0000 0.0532
-14.500 -1.2849 0.03127 0.02549 -0.0351 1.0000 0.0556
-14.250 -1.2817 0.02923 0.02339 -0.0350 1.0000 0.0576
-13.750 -1.2746 0.02565 0.01970 -0.0339 1.0000 0.0620
-13.500 -1.2695 0.02421 0.01821 -0.0328 1.0000 0.0646
-13.250 -1.2621 0.02306 0.01701 -0.0316 1.0000 0.0672
-13.000 -1.2559 0.02196 0.01587 -0.0299 1.0000 0.0697
-12.750 -1.2494 0.02099 0.01488 -0.0279 1.0000 0.0732
-12.500 -1.2396 0.02027 0.01412 -0.0259 1.0000 0.0762
-12.250 -1.2308 0.01957 0.01339 -0.0235 1.0000 0.0792
-12.000 -1.2222 0.01892 0.01274 -0.0209 1.0000 0.0827
-11.750 -1.2105 0.01841 0.01219 -0.0185 1.0000 0.0866
-11.500 -1.1967 0.01783 0.01162 -0.0166 1.0000 0.0909
-11.250 -1.1811 0.01730 0.01109 -0.0149 1.0000 0.0961
-11.000 -1.1642 0.01681 0.01059 -0.0133 1.0000 0.1012
-10.750 -1.1469 0.01631 0.01011 -0.0117 1.0000 0.1068
-10.250 -1.1094 0.01546 0.00926 -0.0089 1.0000 0.1164
-10.000 -1.0897 0.01508 0.00887 -0.0076 1.0000 0.1217
-9.750 -1.0701 0.01470 0.00849 -0.0062 1.0000 0.1266
-9.500 -1.0504 0.01432 0.00812 -0.0049 1.0000 0.1325
-9.250 -1.0296 0.01402 0.00780 -0.0036 1.0000 0.1374
-9.000 -1.0099 0.01364 0.00746 -0.0022 1.0000 0.1436
-8.750 -0.9889 0.01334 0.00716 -0.0010 1.0000 0.1496
-8.500 -0.9636 0.01300 0.00684 -0.0007 0.9980 0.1558
-8.250 -0.9288 0.01267 0.00652 -0.0022 0.9887 0.1638
-8.000 -0.8932 0.01230 0.00619 -0.0040 0.9759 0.1717
-7.500 -0.8092 0.01164 0.00552 -0.0100 0.9172 0.1902
-7.250 -0.7777 0.01146 0.00523 -0.0106 0.8724 0.1975
-7.000 -0.7535 0.01132 0.00500 -0.0097 0.8354 0.2054
-6.750 -0.7291 0.01122 0.00478 -0.0088 0.8040 0.2123
-6.500 -0.7047 0.01109 0.00458 -0.0080 0.7768 0.2202
-6.250 -0.6794 0.01099 0.00438 -0.0074 0.7511 0.2274
-6.000 -0.6542 0.01086 0.00420 -0.0068 0.7285 0.2351
-5.750 -0.6281 0.01078 0.00403 -0.0063 0.7071 0.2421
-5.500 -0.6023 0.01066 0.00387 -0.0058 0.6867 0.2498
-5.250 -0.5757 0.01059 0.00372 -0.0054 0.6674 0.2565
-5.000 -0.5495 0.01048 0.00357 -0.0049 0.6497 0.2639
-4.750 -0.5226 0.01042 0.00344 -0.0046 0.6319 0.2710
-4.500 -0.4959 0.01034 0.00331 -0.0042 0.6145 0.2773
-4.250 -0.4690 0.01027 0.00320 -0.0039 0.5986 0.2846
-3.750 -0.4147 0.01015 0.00298 -0.0033 0.5676 0.2975
-3.500 -0.3872 0.01011 0.00289 -0.0030 0.5523 0.3039
-3.250 -0.3599 0.01005 0.00280 -0.0028 0.5389 0.3099
-3.000 -0.3325 0.01000 0.00272 -0.0025 0.5259 0.3168
-2.500 -0.2775 0.00993 0.00257 -0.0020 0.4994 0.3290
-2.250 -0.2498 0.00990 0.00251 -0.0018 0.4881 0.3356
-2.000 -0.2221 0.00989 0.00245 -0.0016 0.4770 0.3413
-1.750 -0.1945 0.00985 0.00241 -0.0014 0.4656 0.3483
-1.250 -0.1390 0.00982 0.00232 -0.0010 0.4447 0.3612
-1.000 -0.1112 0.00979 0.00230 -0.0008 0.4353 0.3686
-0.500 -0.0556 0.00977 0.00226 -0.0004 0.4164 0.3830
0.000 0.0000 0.00977 0.00224 0.0000 0.3991 0.3991
0.500 0.0556 0.00977 0.00226 0.0004 0.3830 0.4164
1.000 0.1112 0.00979 0.00230 0.0008 0.3687 0.4353
1.250 0.1390 0.00982 0.00232 0.0010 0.3612 0.4447
1.500 0.1666 0.00984 0.00236 0.0012 0.3548 0.4549
1.750 0.1945 0.00985 0.00241 0.0014 0.3482 0.4656
2.000 0.2221 0.00989 0.00245 0.0016 0.3413 0.4771
2.250 0.2498 0.00990 0.00251 0.0018 0.3356 0.4881
2.500 0.2775 0.00993 0.00257 0.0020 0.3289 0.4995
3.000 0.3325 0.01000 0.00272 0.0025 0.3167 0.5260
3.250 0.3599 0.01005 0.00280 0.0028 0.3099 0.5389
3.500 0.3872 0.01011 0.00289 0.0030 0.3039 0.5523
3.750 0.4147 0.01015 0.00298 0.0033 0.2973 0.5676
4.250 0.4690 0.01027 0.00320 0.0039 0.2847 0.5986
4.500 0.4959 0.01034 0.00331 0.0042 0.2775 0.6143
4.750 0.5226 0.01042 0.00344 0.0046 0.2709 0.6318
5.000 0.5495 0.01048 0.00357 0.0049 0.2638 0.6497
5.250 0.5757 0.01059 0.00372 0.0054 0.2565 0.6674
5.500 0.6024 0.01066 0.00387 0.0058 0.2497 0.6866
5.750 0.6282 0.01078 0.00403 0.0063 0.2421 0.7072
6.000 0.6542 0.01086 0.00420 0.0068 0.2351 0.7285
6.250 0.6795 0.01098 0.00438 0.0074 0.2275 0.7512
6.500 0.7047 0.01109 0.00458 0.0080 0.2201 0.7768
6.750 0.7291 0.01122 0.00478 0.0088 0.2123 0.8043
7.000 0.7535 0.01132 0.00500 0.0097 0.2053 0.8359
7.250 0.7778 0.01146 0.00523 0.0105 0.1975 0.8728
7.500 0.8093 0.01164 0.00552 0.0100 0.1901 0.9174
8.000 0.8932 0.01230 0.00618 0.0040 0.1720 0.9759
8.250 0.9289 0.01267 0.00652 0.0022 0.1636 0.9887
8.500 0.9638 0.01300 0.00684 0.0006 0.1558 0.9981
8.750 0.9889 0.01334 0.00716 0.0010 0.1495 1.0000
9.000 1.0099 0.01364 0.00745 0.0022 0.1436 1.0000
9.250 1.0296 0.01401 0.00780 0.0036 0.1375 1.0000
9.500 1.0504 0.01432 0.00812 0.0049 0.1325 1.0000
9.750 1.0701 0.01470 0.00848 0.0062 0.1267 1.0000
10.000 1.0897 0.01508 0.00887 0.0076 0.1216 1.0000
10.250 1.1096 0.01545 0.00925 0.0089 0.1166 1.0000
10.500 1.1277 0.01592 0.00970 0.0104 0.1113 1.0000
10.750 1.1471 0.01631 0.01011 0.0117 0.1068 1.0000
11.000 1.1644 0.01681 0.01059 0.0133 0.1012 1.0000
11.250 1.1813 0.01730 0.01109 0.0148 0.0960 1.0000
11.500 1.1969 0.01784 0.01162 0.0165 0.0907 1.0000
11.750 1.2108 0.01841 0.01219 0.0185 0.0863 1.0000
12.000 1.2226 0.01892 0.01274 0.0208 0.0827 1.0000
12.250 1.2313 0.01956 0.01339 0.0234 0.0791 1.0000
12.500 1.2402 0.02026 0.01411 0.0258 0.0762 1.0000
12.750 1.2499 0.02099 0.01488 0.0278 0.0730 1.0000
13.000 1.2568 0.02194 0.01585 0.0298 0.0698 1.0000
13.250 1.2629 0.02305 0.01699 0.0314 0.0673 1.0000
13.500 1.2703 0.02420 0.01820 0.0327 0.0645 1.0000
13.750 1.2754 0.02563 0.01967 0.0338 0.0619 1.0000
14.000 1.2781 0.02742 0.02151 0.0345 0.0597 1.0000
14.250 1.2828 0.02920 0.02335 0.0349 0.0575 1.0000
14.500 1.2860 0.03125 0.02547 0.0350 0.0554 1.0000
14.750 1.2856 0.03375 0.02802 0.0348 0.0530 1.0000
15.000 1.2841 0.03652 0.03085 0.0344 0.0513 1.0000
15.250 1.2839 0.03922 0.03364 0.0338 0.0496 1.0000
15.500 1.2811 0.04230 0.03679 0.0331 0.0481 1.0000
15.750 1.2751 0.04580 0.04036 0.0321 0.0464 1.0000
16.000 1.2661 0.04971 0.04434 0.0309 0.0450 1.0000
16.250 1.2599 0.05334 0.04807 0.0297 0.0438 1.0000
16.500 1.2520 0.05725 0.05206 0.0284 0.0424 1.0000
16.750 1.2422 0.06151 0.05641 0.0269 0.0412 1.0000
17.000 1.2315 0.06602 0.06099 0.0251 0.0401 1.0000
17.250 1.2196 0.07080 0.06584 0.0232 0.0391 1.0000
17.500 1.2109 0.07521 0.07034 0.0214 0.0380 1.0000
17.750 1.2022 0.07975 0.07496 0.0195 0.0371 1.0000
18.000 1.1920 0.08456 0.07984 0.0174 0.0356 1.0000
18.250 1.1808 0.08961 0.08497 0.0151 0.0346 1.0000
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Polar data table (+)
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