EPPLER 472 AIRFOIL (e472-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 472 AIRFOIL (e472-il) Reynolds number: 500,000 Max Cl/Cd: 72.64 at α=9.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e472-il-500000-n5.txt Download as CSV file: xf-e472-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 472 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
------ -------- --------- --------- -------- -------- --------
-17.500 -1.1811 0.08823 0.08424 -0.0202 1.0000 0.0314
-17.250 -1.2246 0.07833 0.07420 -0.0255 1.0000 0.0311
-17.000 -1.2797 0.06667 0.06235 -0.0319 1.0000 0.0304
-16.750 -1.3267 0.05594 0.05140 -0.0381 1.0000 0.0297
-16.500 -1.3595 0.04710 0.04233 -0.0439 1.0000 0.0297
-16.250 -1.3784 0.04091 0.03597 -0.0479 1.0000 0.0303
-16.000 -1.3893 0.03667 0.03156 -0.0499 1.0000 0.0310
-15.750 -1.3983 0.03337 0.02814 -0.0505 1.0000 0.0321
-15.500 -1.4029 0.03101 0.02568 -0.0497 1.0000 0.0331
-15.250 -1.4042 0.02923 0.02380 -0.0482 1.0000 0.0342
-15.000 -1.4023 0.02785 0.02234 -0.0462 1.0000 0.0357
-14.750 -1.3996 0.02665 0.02106 -0.0438 1.0000 0.0373
-14.500 -1.3968 0.02556 0.01991 -0.0410 1.0000 0.0390
-14.250 -1.3917 0.02469 0.01897 -0.0381 1.0000 0.0407
-14.000 -1.3852 0.02397 0.01818 -0.0351 1.0000 0.0424
-13.750 -1.3793 0.02317 0.01734 -0.0319 1.0000 0.0442
-13.500 -1.3681 0.02243 0.01655 -0.0296 1.0000 0.0462
-13.250 -1.3546 0.02180 0.01586 -0.0274 1.0000 0.0483
-13.000 -1.3402 0.02119 0.01519 -0.0254 1.0000 0.0501
-12.750 -1.3261 0.02053 0.01450 -0.0234 1.0000 0.0525
-12.500 -1.3099 0.01997 0.01389 -0.0215 1.0000 0.0549
-12.250 -1.2923 0.01949 0.01335 -0.0198 1.0000 0.0570
-12.000 -1.2756 0.01892 0.01275 -0.0180 1.0000 0.0594
-11.750 -1.2578 0.01841 0.01222 -0.0163 1.0000 0.0619
-11.500 -1.2388 0.01797 0.01172 -0.0148 1.0000 0.0645
-11.250 -1.2197 0.01753 0.01124 -0.0132 1.0000 0.0669
-11.000 -1.2007 0.01706 0.01076 -0.0117 1.0000 0.0697
-10.750 -1.1806 0.01666 0.01033 -0.0102 1.0000 0.0728
-10.500 -1.1598 0.01632 0.00993 -0.0089 1.0000 0.0756
-10.250 -1.1400 0.01587 0.00950 -0.0074 1.0000 0.0792
-10.000 -1.1190 0.01552 0.00913 -0.0060 1.0000 0.0825
-9.750 -1.0973 0.01522 0.00878 -0.0048 1.0000 0.0851
-9.500 -1.0762 0.01486 0.00840 -0.0034 1.0000 0.0877
-9.250 -1.0548 0.01452 0.00806 -0.0021 1.0000 0.0909
-9.000 -1.0329 0.01423 0.00774 -0.0008 1.0000 0.0938
-8.750 -1.0104 0.01397 0.00744 0.0004 1.0000 0.0964
-8.500 -0.9885 0.01366 0.00712 0.0017 1.0000 0.0991
-8.250 -0.9663 0.01338 0.00684 0.0029 1.0000 0.1024
-8.000 -0.9437 0.01313 0.00658 0.0041 1.0000 0.1056
-7.750 -0.9207 0.01291 0.00632 0.0052 1.0000 0.1081
-7.500 -0.8981 0.01266 0.00606 0.0064 1.0000 0.1110
-7.250 -0.8754 0.01241 0.00583 0.0076 1.0000 0.1145
-7.000 -0.8524 0.01220 0.00561 0.0088 1.0000 0.1177
-6.750 -0.8292 0.01202 0.00540 0.0099 1.0000 0.1206
-6.500 -0.8061 0.01182 0.00519 0.0111 1.0000 0.1235
-6.250 -0.7832 0.01161 0.00500 0.0122 1.0000 0.1269
-6.000 -0.7600 0.01143 0.00483 0.0134 1.0000 0.1301
-5.750 -0.7366 0.01128 0.00467 0.0145 1.0000 0.1334
-5.500 -0.6998 0.01113 0.00451 0.0128 0.9976 0.1367
-5.250 -0.6544 0.01095 0.00438 0.0092 0.9932 0.1412
-5.000 -0.6118 0.01075 0.00419 0.0063 0.9868 0.1458
-4.750 -0.5686 0.01058 0.00401 0.0033 0.9801 0.1494
-4.500 -0.5372 0.01034 0.00380 0.0028 0.9717 0.1531
-4.250 -0.5101 0.01014 0.00364 0.0033 0.9605 0.1571
-4.000 -0.4814 0.00995 0.00346 0.0034 0.9455 0.1610
-3.750 -0.4423 0.00977 0.00326 0.0014 0.9284 0.1644
-3.500 -0.3582 0.00943 0.00292 -0.0103 0.8800 0.1717
-3.250 -0.3217 0.00959 0.00271 -0.0116 0.7736 0.1767
-3.000 -0.2998 0.00979 0.00261 -0.0100 0.6960 0.1796
-2.750 -0.2777 0.00992 0.00252 -0.0085 0.6288 0.1835
-2.500 -0.2548 0.01004 0.00244 -0.0072 0.5655 0.1880
-2.250 -0.2310 0.01018 0.00237 -0.0062 0.5053 0.1928
-2.000 -0.2062 0.01027 0.00230 -0.0053 0.4581 0.1971
-1.750 -0.1811 0.01032 0.00224 -0.0045 0.4192 0.2023
-1.500 -0.1556 0.01037 0.00219 -0.0038 0.3850 0.2079
-1.250 -0.1299 0.01043 0.00215 -0.0031 0.3539 0.2140
-1.000 -0.1043 0.01046 0.00212 -0.0024 0.3264 0.2215
-0.750 -0.0782 0.01050 0.00209 -0.0018 0.3044 0.2282
-0.500 -0.0522 0.01050 0.00207 -0.0012 0.2871 0.2367
-0.250 -0.0260 0.01052 0.00206 -0.0006 0.2722 0.2461
0.000 0.0000 0.01052 0.00206 0.0000 0.2587 0.2585
0.250 0.0260 0.01052 0.00206 0.0006 0.2460 0.2722
0.500 0.0522 0.01050 0.00207 0.0012 0.2368 0.2871
0.750 0.0782 0.01050 0.00209 0.0018 0.2282 0.3044
1.000 0.1043 0.01046 0.00212 0.0024 0.2215 0.3267
1.250 0.1299 0.01043 0.00215 0.0031 0.2139 0.3539
1.500 0.1556 0.01037 0.00219 0.0038 0.2079 0.3851
1.750 0.1811 0.01032 0.00224 0.0045 0.2023 0.4189
2.000 0.2062 0.01028 0.00230 0.0053 0.1971 0.4580
2.250 0.2310 0.01018 0.00237 0.0062 0.1929 0.5053
2.500 0.2548 0.01004 0.00244 0.0072 0.1881 0.5653
2.750 0.2777 0.00992 0.00252 0.0085 0.1835 0.6291
3.000 0.2999 0.00979 0.00261 0.0100 0.1796 0.6956
3.250 0.3216 0.00959 0.00271 0.0116 0.1767 0.7740
3.500 0.3598 0.00943 0.00293 0.0100 0.1716 0.8827
3.750 0.4424 0.00977 0.00326 -0.0015 0.1644 0.9284
4.000 0.4816 0.00995 0.00346 -0.0035 0.1610 0.9458
4.250 0.5101 0.01014 0.00363 -0.0033 0.1570 0.9604
4.500 0.5371 0.01034 0.00380 -0.0028 0.1531 0.9716
4.750 0.5687 0.01058 0.00401 -0.0033 0.1495 0.9803
5.000 0.6121 0.01075 0.00419 -0.0064 0.1458 0.9869
5.250 0.6546 0.01095 0.00438 -0.0092 0.1412 0.9933
5.500 0.6998 0.01113 0.00451 -0.0128 0.1367 0.9976
5.750 0.7366 0.01128 0.00467 -0.0145 0.1334 1.0000
6.000 0.7600 0.01143 0.00483 -0.0134 0.1301 1.0000
6.250 0.7832 0.01161 0.00500 -0.0122 0.1269 1.0000
6.500 0.8061 0.01182 0.00519 -0.0111 0.1235 1.0000
6.750 0.8292 0.01202 0.00540 -0.0099 0.1206 1.0000
7.000 0.8524 0.01220 0.00561 -0.0088 0.1177 1.0000
7.250 0.8754 0.01241 0.00583 -0.0076 0.1144 1.0000
7.500 0.8981 0.01266 0.00605 -0.0065 0.1109 1.0000
7.750 0.9208 0.01291 0.00632 -0.0053 0.1082 1.0000
8.000 0.9437 0.01313 0.00658 -0.0041 0.1056 1.0000
8.250 0.9663 0.01338 0.00684 -0.0029 0.1024 1.0000
8.500 0.9885 0.01366 0.00712 -0.0017 0.0991 1.0000
8.750 1.0104 0.01397 0.00744 -0.0004 0.0964 1.0000
9.000 1.0329 0.01423 0.00774 0.0008 0.0939 1.0000
9.250 1.0548 0.01452 0.00806 0.0021 0.0909 1.0000
9.500 1.0762 0.01486 0.00840 0.0034 0.0878 1.0000
9.750 1.0973 0.01522 0.00878 0.0047 0.0851 1.0000
10.000 1.1190 0.01552 0.00913 0.0060 0.0825 1.0000
10.250 1.1400 0.01587 0.00950 0.0074 0.0792 1.0000
10.500 1.1598 0.01632 0.00993 0.0088 0.0756 1.0000
10.750 1.1807 0.01666 0.01033 0.0102 0.0728 1.0000
11.000 1.2007 0.01706 0.01076 0.0117 0.0697 1.0000
11.250 1.2196 0.01753 0.01124 0.0132 0.0669 1.0000
11.500 1.2389 0.01797 0.01172 0.0148 0.0644 1.0000
11.750 1.2578 0.01841 0.01221 0.0163 0.0620 1.0000
12.000 1.2757 0.01891 0.01275 0.0180 0.0594 1.0000
12.250 1.2923 0.01949 0.01335 0.0198 0.0570 1.0000
12.500 1.3099 0.01997 0.01389 0.0215 0.0549 1.0000
12.750 1.3261 0.02053 0.01449 0.0233 0.0525 1.0000
13.000 1.3404 0.02119 0.01519 0.0254 0.0502 1.0000
13.250 1.3547 0.02180 0.01586 0.0274 0.0482 1.0000
13.500 1.3682 0.02243 0.01655 0.0295 0.0462 1.0000
13.750 1.3793 0.02318 0.01734 0.0319 0.0441 1.0000
14.000 1.3856 0.02397 0.01818 0.0350 0.0424 1.0000
14.250 1.3920 0.02469 0.01897 0.0381 0.0406 1.0000
14.500 1.3971 0.02556 0.01991 0.0410 0.0389 1.0000
14.750 1.4001 0.02665 0.02106 0.0437 0.0373 1.0000
15.000 1.4029 0.02784 0.02233 0.0461 0.0360 1.0000
15.250 1.4051 0.02919 0.02377 0.0481 0.0346 1.0000
15.500 1.4040 0.03097 0.02564 0.0496 0.0331 1.0000
15.750 1.3983 0.03343 0.02820 0.0503 0.0319 1.0000
16.000 1.3906 0.03661 0.03150 0.0498 0.0311 1.0000
16.250 1.3799 0.04084 0.03589 0.0478 0.0300 1.0000
16.500 1.3611 0.04703 0.04226 0.0438 0.0297 1.0000
16.750 1.3296 0.05566 0.05112 0.0381 0.0298 1.0000
17.000 1.2815 0.06663 0.06231 0.0317 0.0302 1.0000
17.250 1.2278 0.07808 0.07395 0.0254 0.0308 1.0000
17.500 1.1839 0.08805 0.08407 0.0201 0.0314 1.0000
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Polar data table (+)
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