EPPLER 472 AIRFOIL (e472-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 472 AIRFOIL (e472-il) Reynolds number: 500,000 Max Cl/Cd: 69.49 at α=9.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e472-il-500000.txt Download as CSV file: xf-e472-il-500000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-17.750 -1.2089 0.08619 0.08243 -0.0227 1.0000 0.0395
-17.500 -1.2392 0.07839 0.07452 -0.0268 1.0000 0.0399
-17.250 -1.2722 0.07024 0.06624 -0.0311 1.0000 0.0402
-17.000 -1.3058 0.06194 0.05780 -0.0356 1.0000 0.0404
-16.750 -1.3374 0.05376 0.04945 -0.0404 1.0000 0.0404
-16.500 -1.3589 0.04693 0.04244 -0.0446 1.0000 0.0410
-16.250 -1.3714 0.04172 0.03706 -0.0478 1.0000 0.0420
-16.000 -1.3812 0.03745 0.03263 -0.0500 1.0000 0.0430
-15.750 -1.3938 0.03365 0.02873 -0.0509 1.0000 0.0443
-15.500 -1.3988 0.03117 0.02618 -0.0504 1.0000 0.0456
-15.250 -1.3989 0.02941 0.02432 -0.0491 1.0000 0.0472
-15.000 -1.3934 0.02820 0.02300 -0.0475 1.0000 0.0489
-14.750 -1.3931 0.02682 0.02154 -0.0451 1.0000 0.0507
-14.500 -1.3908 0.02569 0.02037 -0.0424 1.0000 0.0527
-14.250 -1.3838 0.02488 0.01949 -0.0398 1.0000 0.0547
-14.000 -1.3738 0.02427 0.01878 -0.0373 1.0000 0.0567
-13.750 -1.3704 0.02344 0.01790 -0.0338 1.0000 0.0586
-13.500 -1.3623 0.02267 0.01712 -0.0310 1.0000 0.0608
-13.250 -1.3484 0.02209 0.01649 -0.0289 1.0000 0.0631
-13.000 -1.3321 0.02162 0.01591 -0.0271 1.0000 0.0652
-12.750 -1.3196 0.02089 0.01514 -0.0248 1.0000 0.0677
-12.500 -1.3048 0.02029 0.01454 -0.0228 1.0000 0.0702
-12.250 -1.2868 0.01986 0.01405 -0.0211 1.0000 0.0728
-12.000 -1.2674 0.01950 0.01359 -0.0197 1.0000 0.0750
-11.750 -1.2524 0.01882 0.01289 -0.0176 1.0000 0.0778
-11.500 -1.2343 0.01835 0.01242 -0.0159 1.0000 0.0806
-11.250 -1.2142 0.01801 0.01203 -0.0145 1.0000 0.0835
-11.000 -1.1929 0.01773 0.01164 -0.0132 1.0000 0.0857
-10.750 -1.1760 0.01711 0.01105 -0.0114 1.0000 0.0892
-10.500 -1.1554 0.01678 0.01071 -0.0100 1.0000 0.0924
-10.250 -1.1334 0.01655 0.01042 -0.0088 1.0000 0.0956
-10.000 -1.1128 0.01617 0.00999 -0.0074 1.0000 0.0985
-9.750 -1.0930 0.01573 0.00958 -0.0058 1.0000 0.1019
-9.500 -1.0712 0.01546 0.00927 -0.0046 1.0000 0.1049
-9.250 -1.0487 0.01523 0.00898 -0.0034 1.0000 0.1078
-9.000 -1.0273 0.01488 0.00858 -0.0020 1.0000 0.1106
-8.750 -1.0065 0.01449 0.00822 -0.0006 1.0000 0.1141
-8.500 -0.9841 0.01424 0.00796 0.0006 1.0000 0.1172
-8.250 -0.9611 0.01405 0.00771 0.0018 1.0000 0.1202
-8.000 -0.9385 0.01379 0.00740 0.0030 1.0000 0.1231
-7.750 -0.9172 0.01341 0.00706 0.0044 1.0000 0.1267
-7.500 -0.8944 0.01320 0.00685 0.0055 1.0000 0.1300
-7.250 -0.8710 0.01303 0.00664 0.0066 1.0000 0.1332
-7.000 -0.8473 0.01290 0.00645 0.0077 1.0000 0.1357
-6.750 -0.8260 0.01248 0.00608 0.0091 1.0000 0.1398
-6.500 -0.8030 0.01230 0.00591 0.0103 1.0000 0.1433
-6.250 -0.7795 0.01215 0.00575 0.0114 1.0000 0.1467
-6.000 -0.7558 0.01204 0.00557 0.0125 1.0000 0.1493
-5.750 -0.7339 0.01170 0.00528 0.0138 1.0000 0.1533
-5.500 -0.7110 0.01152 0.00513 0.0150 1.0000 0.1570
-5.250 -0.6876 0.01139 0.00499 0.0161 1.0000 0.1605
-5.000 -0.6641 0.01128 0.00485 0.0172 1.0000 0.1635
-4.750 -0.6417 0.01106 0.00464 0.0185 1.0000 0.1671
-4.500 -0.6192 0.01087 0.00451 0.0197 1.0000 0.1711
-4.250 -0.5962 0.01077 0.00441 0.0209 1.0000 0.1748
-4.000 -0.5563 0.01070 0.00433 0.0186 0.9970 0.1790
-3.750 -0.5130 0.01049 0.00418 0.0154 0.9931 0.1847
-3.500 -0.4733 0.01030 0.00404 0.0132 0.9881 0.1899
-3.250 -0.4296 0.01018 0.00392 0.0101 0.9834 0.1947
-3.000 -0.3912 0.00988 0.00369 0.0082 0.9763 0.2007
-2.250 -0.2855 0.00911 0.00307 0.0047 0.9360 0.2186
-2.000 -0.2216 0.00883 0.00280 -0.0024 0.9071 0.2281
-1.750 -0.1572 0.00869 0.00247 -0.0097 0.8098 0.2402
-1.500 -0.1356 0.00893 0.00236 -0.0078 0.7122 0.2480
-1.250 -0.1155 0.00915 0.00230 -0.0059 0.6260 0.2577
-1.000 -0.0942 0.00933 0.00224 -0.0043 0.5504 0.2689
-0.750 -0.0713 0.00946 0.00220 -0.0030 0.4870 0.2825
-0.500 -0.0478 0.00956 0.00217 -0.0019 0.4343 0.2998
-0.250 -0.0239 0.00961 0.00215 -0.0010 0.3899 0.3226
0.000 0.0000 0.00963 0.00214 0.0000 0.3524 0.3524
0.250 0.0240 0.00961 0.00215 0.0010 0.3225 0.3897
0.500 0.0478 0.00955 0.00217 0.0019 0.2999 0.4344
0.750 0.0713 0.00946 0.00220 0.0030 0.2825 0.4870
1.000 0.0942 0.00933 0.00224 0.0043 0.2690 0.5508
1.250 0.1155 0.00915 0.00230 0.0059 0.2577 0.6258
1.500 0.1356 0.00893 0.00236 0.0078 0.2479 0.7126
1.750 0.1572 0.00869 0.00247 0.0097 0.2402 0.8095
2.000 0.2214 0.00883 0.00280 0.0024 0.2281 0.9070
2.250 0.2855 0.00911 0.00307 -0.0048 0.2186 0.9360
3.000 0.3908 0.00988 0.00369 -0.0081 0.2005 0.9760
3.250 0.4298 0.01018 0.00392 -0.0102 0.1947 0.9834
3.500 0.4732 0.01030 0.00404 -0.0132 0.1899 0.9881
3.750 0.5134 0.01049 0.00418 -0.0155 0.1847 0.9932
4.000 0.5566 0.01070 0.00433 -0.0186 0.1789 0.9970
4.250 0.5962 0.01077 0.00441 -0.0209 0.1749 1.0000
4.500 0.6192 0.01088 0.00451 -0.0197 0.1712 1.0000
4.750 0.6417 0.01106 0.00464 -0.0185 0.1671 1.0000
5.000 0.6641 0.01128 0.00485 -0.0172 0.1635 1.0000
5.250 0.6876 0.01139 0.00498 -0.0161 0.1605 1.0000
5.500 0.7110 0.01152 0.00513 -0.0150 0.1570 1.0000
5.750 0.7339 0.01170 0.00528 -0.0138 0.1533 1.0000
6.000 0.7558 0.01203 0.00557 -0.0125 0.1493 1.0000
6.250 0.7795 0.01215 0.00574 -0.0114 0.1467 1.0000
6.500 0.8030 0.01230 0.00592 -0.0103 0.1433 1.0000
6.750 0.8261 0.01248 0.00608 -0.0091 0.1398 1.0000
7.000 0.8473 0.01290 0.00645 -0.0077 0.1357 1.0000
7.250 0.8710 0.01303 0.00664 -0.0066 0.1332 1.0000
7.500 0.8944 0.01319 0.00684 -0.0055 0.1300 1.0000
7.750 0.9172 0.01341 0.00706 -0.0044 0.1267 1.0000
8.000 0.9385 0.01379 0.00740 -0.0030 0.1231 1.0000
8.250 0.9611 0.01405 0.00771 -0.0018 0.1202 1.0000
8.500 0.9841 0.01424 0.00796 -0.0006 0.1172 1.0000
8.750 1.0066 0.01449 0.00823 0.0006 0.1142 1.0000
9.000 1.0274 0.01487 0.00858 0.0020 0.1107 1.0000
9.250 1.0487 0.01523 0.00898 0.0034 0.1078 1.0000
9.500 1.0712 0.01547 0.00928 0.0046 0.1050 1.0000
9.750 1.0930 0.01573 0.00958 0.0058 0.1019 1.0000
10.000 1.1128 0.01617 0.00999 0.0074 0.0985 1.0000
10.250 1.1334 0.01655 0.01042 0.0088 0.0956 1.0000
10.500 1.1555 0.01678 0.01071 0.0100 0.0924 1.0000
10.750 1.1760 0.01711 0.01105 0.0113 0.0892 1.0000
11.000 1.1930 0.01773 0.01164 0.0132 0.0857 1.0000
11.250 1.2142 0.01801 0.01202 0.0145 0.0835 1.0000
11.500 1.2344 0.01834 0.01241 0.0159 0.0806 1.0000
11.750 1.2524 0.01882 0.01289 0.0176 0.0779 1.0000
12.000 1.2674 0.01950 0.01359 0.0197 0.0750 1.0000
12.250 1.2869 0.01986 0.01405 0.0211 0.0728 1.0000
12.500 1.3049 0.02029 0.01453 0.0228 0.0702 1.0000
12.750 1.3197 0.02089 0.01514 0.0248 0.0677 1.0000
13.000 1.3321 0.02162 0.01591 0.0271 0.0652 1.0000
13.250 1.3486 0.02209 0.01648 0.0289 0.0631 1.0000
13.500 1.3626 0.02266 0.01711 0.0309 0.0607 1.0000
13.750 1.3706 0.02344 0.01790 0.0337 0.0585 1.0000
14.000 1.3742 0.02426 0.01878 0.0373 0.0566 1.0000
14.250 1.3843 0.02487 0.01949 0.0397 0.0546 1.0000
14.500 1.3912 0.02569 0.02036 0.0423 0.0526 1.0000
14.750 1.3934 0.02683 0.02154 0.0450 0.0507 1.0000
15.000 1.3929 0.02825 0.02304 0.0475 0.0490 1.0000
15.250 1.3986 0.02946 0.02438 0.0491 0.0474 1.0000
15.500 1.3996 0.03115 0.02616 0.0503 0.0456 1.0000
15.750 1.3948 0.03362 0.02869 0.0508 0.0441 1.0000
16.000 1.3826 0.03738 0.03257 0.0499 0.0430 1.0000
16.250 1.3743 0.04145 0.03679 0.0478 0.0418 1.0000
16.500 1.3601 0.04691 0.04243 0.0445 0.0410 1.0000
16.750 1.3383 0.05379 0.04948 0.0401 0.0405 1.0000
17.000 1.3080 0.06184 0.05770 0.0354 0.0402 1.0000
17.250 1.2742 0.07023 0.06623 0.0308 0.0399 1.0000
17.500 1.2411 0.07838 0.07451 0.0265 0.0398 1.0000
17.750 1.2117 0.08601 0.08225 0.0225 0.0395 1.0000
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Polar data table (+)
Polar graphs
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