EPPLER 472 AIRFOIL (e472-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 472 AIRFOIL (e472-il) Reynolds number: 1,000,000 Max Cl/Cd: 90.8 at α=9° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e472-il-1000000-n5.txt Download as CSV file: xf-e472-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-18.000 -1.2971 0.07780 0.07408 -0.0264 1.0000 0.0179
-17.750 -1.3802 0.06187 0.05785 -0.0353 1.0000 0.0170
-17.500 -1.4317 0.05017 0.04588 -0.0425 1.0000 0.0165
-17.250 -1.4625 0.04187 0.03736 -0.0481 1.0000 0.0167
-17.000 -1.4784 0.03664 0.03198 -0.0511 1.0000 0.0170
-16.750 -1.4875 0.03308 0.02830 -0.0521 1.0000 0.0175
-16.500 -1.4925 0.03050 0.02561 -0.0519 1.0000 0.0181
-16.250 -1.4936 0.02861 0.02363 -0.0507 1.0000 0.0187
-16.000 -1.4945 0.02697 0.02191 -0.0489 1.0000 0.0194
-15.750 -1.4932 0.02565 0.02051 -0.0467 1.0000 0.0202
-15.500 -1.4900 0.02456 0.01936 -0.0441 1.0000 0.0211
-15.250 -1.4850 0.02366 0.01840 -0.0414 1.0000 0.0221
-15.000 -1.4808 0.02281 0.01750 -0.0382 1.0000 0.0232
-14.750 -1.4771 0.02206 0.01671 -0.0347 1.0000 0.0244
-14.500 -1.4705 0.02138 0.01599 -0.0314 1.0000 0.0258
-14.250 -1.4595 0.02068 0.01525 -0.0289 1.0000 0.0273
-14.000 -1.4476 0.02000 0.01454 -0.0266 1.0000 0.0291
-13.750 -1.4333 0.01943 0.01392 -0.0244 1.0000 0.0308
-13.500 -1.4193 0.01879 0.01326 -0.0223 1.0000 0.0328
-13.250 -1.4038 0.01822 0.01267 -0.0203 1.0000 0.0351
-13.000 -1.3874 0.01770 0.01212 -0.0184 1.0000 0.0374
-12.750 -1.3710 0.01713 0.01155 -0.0165 1.0000 0.0400
-12.500 -1.3528 0.01668 0.01107 -0.0148 1.0000 0.0422
-12.250 -1.3345 0.01621 0.01058 -0.0132 1.0000 0.0442
-12.000 -1.3159 0.01574 0.01010 -0.0115 1.0000 0.0469
-11.750 -1.2960 0.01536 0.00970 -0.0101 1.0000 0.0489
-11.500 -1.2763 0.01495 0.00927 -0.0085 1.0000 0.0512
-11.250 -1.2564 0.01454 0.00885 -0.0071 1.0000 0.0538
-11.000 -1.2356 0.01420 0.00849 -0.0057 1.0000 0.0562
-10.750 -1.2146 0.01386 0.00814 -0.0043 1.0000 0.0585
-10.500 -1.1938 0.01349 0.00777 -0.0029 1.0000 0.0613
-10.250 -1.1723 0.01318 0.00744 -0.0016 1.0000 0.0639
-10.000 -1.1502 0.01290 0.00715 -0.0003 1.0000 0.0662
-9.750 -1.1289 0.01256 0.00682 0.0010 1.0000 0.0697
-9.500 -1.1069 0.01226 0.00653 0.0022 1.0000 0.0736
-9.250 -1.0844 0.01200 0.00625 0.0034 1.0000 0.0765
-9.000 -1.0623 0.01171 0.00598 0.0047 1.0000 0.0800
-8.750 -1.0397 0.01146 0.00573 0.0059 1.0000 0.0830
-8.500 -1.0166 0.01125 0.00551 0.0070 1.0000 0.0851
-8.250 -0.9937 0.01102 0.00527 0.0082 1.0000 0.0881
-8.000 -0.9709 0.01078 0.00505 0.0094 1.0000 0.0913
-7.750 -0.9477 0.01058 0.00485 0.0105 1.0000 0.0941
-7.500 -0.9242 0.01041 0.00466 0.0116 1.0000 0.0964
-7.250 -0.8930 0.01022 0.00448 0.0110 0.9991 0.0998
-7.000 -0.8575 0.01002 0.00431 0.0095 0.9973 0.1038
-6.750 -0.8192 0.00986 0.00416 0.0074 0.9952 0.1073
-6.500 -0.7776 0.00971 0.00401 0.0047 0.9931 0.1107
-6.250 -0.7421 0.00948 0.00381 0.0033 0.9895 0.1150
-6.000 -0.7022 0.00928 0.00364 0.0009 0.9854 0.1190
-5.750 -0.6584 0.00909 0.00345 -0.0023 0.9808 0.1219
-5.500 -0.6297 0.00887 0.00325 -0.0022 0.9711 0.1258
-5.250 -0.6059 0.00869 0.00310 -0.0010 0.9597 0.1297
-5.000 -0.5743 0.00851 0.00293 -0.0015 0.9452 0.1329
-4.750 -0.4956 0.00824 0.00262 -0.0122 0.9110 0.1376
-4.500 -0.4612 0.00833 0.00243 -0.0132 0.8170 0.1422
-4.250 -0.4407 0.00852 0.00234 -0.0113 0.7315 0.1451
-4.000 -0.4180 0.00867 0.00225 -0.0100 0.6622 0.1478
-3.750 -0.3937 0.00877 0.00217 -0.0090 0.6052 0.1500
-3.500 -0.3690 0.00882 0.00208 -0.0081 0.5544 0.1544
-3.250 -0.3441 0.00890 0.00201 -0.0072 0.5023 0.1579
-3.000 -0.3186 0.00897 0.00195 -0.0065 0.4560 0.1610
-2.750 -0.2926 0.00904 0.00188 -0.0059 0.4173 0.1638
-2.500 -0.2665 0.00906 0.00182 -0.0052 0.3860 0.1677
-2.250 -0.2404 0.00908 0.00177 -0.0046 0.3580 0.1720
-2.000 -0.2140 0.00912 0.00173 -0.0041 0.3310 0.1757
-1.750 -0.1875 0.00916 0.00169 -0.0035 0.3064 0.1789
-1.500 -0.1609 0.00917 0.00165 -0.0030 0.2875 0.1837
-1.250 -0.1343 0.00917 0.00162 -0.0025 0.2721 0.1889
-1.000 -0.1074 0.00919 0.00160 -0.0020 0.2587 0.1932
-0.500 -0.0538 0.00920 0.00157 -0.0010 0.2344 0.2047
-0.250 -0.0269 0.00921 0.00156 -0.0005 0.2253 0.2109
0.000 0.0000 0.00920 0.00156 0.0000 0.2179 0.2178
0.250 0.0269 0.00921 0.00156 0.0005 0.2108 0.2253
0.500 0.0539 0.00920 0.00157 0.0010 0.2046 0.2342
1.000 0.1074 0.00919 0.00160 0.0020 0.1932 0.2586
1.250 0.1343 0.00917 0.00162 0.0025 0.1889 0.2722
1.500 0.1609 0.00917 0.00165 0.0030 0.1838 0.2875
1.750 0.1875 0.00916 0.00169 0.0035 0.1790 0.3068
2.000 0.2140 0.00911 0.00173 0.0041 0.1757 0.3318
2.250 0.2403 0.00908 0.00177 0.0046 0.1720 0.3585
2.500 0.2665 0.00906 0.00182 0.0052 0.1678 0.3860
2.750 0.2926 0.00904 0.00188 0.0059 0.1637 0.4172
3.000 0.3185 0.00897 0.00195 0.0065 0.1609 0.4570
3.250 0.3440 0.00889 0.00201 0.0072 0.1579 0.5039
3.500 0.3691 0.00882 0.00208 0.0080 0.1544 0.5541
3.750 0.3937 0.00877 0.00217 0.0089 0.1502 0.6054
4.000 0.4180 0.00867 0.00225 0.0100 0.1478 0.6619
4.250 0.4407 0.00852 0.00234 0.0113 0.1452 0.7315
4.500 0.4611 0.00832 0.00243 0.0133 0.1422 0.8193
4.750 0.4955 0.00824 0.00262 0.0122 0.1376 0.9108
5.000 0.5749 0.00851 0.00293 0.0013 0.1328 0.9458
5.250 0.6058 0.00869 0.00310 0.0010 0.1297 0.9600
5.750 0.6586 0.00909 0.00345 0.0022 0.1219 0.9807
6.000 0.7023 0.00928 0.00364 -0.0009 0.1193 0.9854
6.250 0.7421 0.00947 0.00381 -0.0032 0.1149 0.9895
6.500 0.7777 0.00971 0.00401 -0.0047 0.1107 0.9931
6.750 0.8192 0.00986 0.00416 -0.0074 0.1073 0.9952
7.000 0.8575 0.01002 0.00431 -0.0095 0.1039 0.9973
7.250 0.8931 0.01021 0.00448 -0.0110 0.1000 0.9991
7.500 0.9242 0.01041 0.00466 -0.0116 0.0964 1.0000
7.750 0.9477 0.01058 0.00485 -0.0105 0.0941 1.0000
8.000 0.9709 0.01078 0.00505 -0.0094 0.0914 1.0000
8.250 0.9937 0.01102 0.00527 -0.0082 0.0881 1.0000
8.500 1.0166 0.01125 0.00551 -0.0070 0.0852 1.0000
8.750 1.0397 0.01146 0.00573 -0.0059 0.0830 1.0000
9.000 1.0624 0.01170 0.00598 -0.0047 0.0803 1.0000
9.250 1.0844 0.01200 0.00625 -0.0035 0.0765 1.0000
9.500 1.1069 0.01226 0.00653 -0.0022 0.0733 1.0000
9.750 1.1289 0.01256 0.00682 -0.0010 0.0696 1.0000
10.000 1.1503 0.01290 0.00714 0.0003 0.0662 1.0000
10.250 1.1723 0.01318 0.00744 0.0016 0.0638 1.0000
10.500 1.1939 0.01349 0.00777 0.0029 0.0613 1.0000
10.750 1.2146 0.01386 0.00814 0.0043 0.0585 1.0000
11.000 1.2356 0.01420 0.00849 0.0057 0.0562 1.0000
11.250 1.2565 0.01454 0.00885 0.0070 0.0540 1.0000
11.500 1.2763 0.01495 0.00927 0.0085 0.0513 1.0000
11.750 1.2960 0.01536 0.00969 0.0101 0.0489 1.0000
12.000 1.3159 0.01574 0.01010 0.0115 0.0469 1.0000
12.250 1.3345 0.01621 0.01058 0.0132 0.0443 1.0000
12.500 1.3528 0.01668 0.01107 0.0149 0.0421 1.0000
12.750 1.3710 0.01713 0.01155 0.0165 0.0399 1.0000
13.000 1.3873 0.01770 0.01213 0.0184 0.0373 1.0000
13.250 1.4039 0.01822 0.01267 0.0203 0.0351 1.0000
13.500 1.4197 0.01877 0.01324 0.0222 0.0331 1.0000
13.750 1.4334 0.01942 0.01392 0.0244 0.0308 1.0000
14.000 1.4479 0.01999 0.01452 0.0265 0.0293 1.0000
14.250 1.4593 0.02070 0.01526 0.0290 0.0272 1.0000
14.500 1.4707 0.02138 0.01599 0.0314 0.0258 1.0000
14.750 1.4776 0.02205 0.01670 0.0346 0.0244 1.0000
15.000 1.4811 0.02282 0.01751 0.0382 0.0232 1.0000
15.250 1.4858 0.02364 0.01838 0.0413 0.0222 1.0000
15.500 1.4907 0.02454 0.01934 0.0440 0.0212 1.0000
15.750 1.4940 0.02563 0.02050 0.0466 0.0202 1.0000
16.000 1.4947 0.02699 0.02193 0.0489 0.0193 1.0000
16.250 1.4946 0.02858 0.02360 0.0506 0.0186 1.0000
16.500 1.4923 0.03058 0.02568 0.0518 0.0177 1.0000
16.750 1.4887 0.03304 0.02826 0.0520 0.0174 1.0000
17.000 1.4788 0.03672 0.03205 0.0509 0.0168 1.0000
17.250 1.4645 0.04174 0.03723 0.0480 0.0167 1.0000
17.500 1.4385 0.04930 0.04500 0.0429 0.0168 1.0000
17.750 1.3803 0.06209 0.05807 0.0349 0.0168 1.0000
18.000 1.3044 0.07696 0.07323 0.0266 0.0181 1.0000
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