EPPLER 472 AIRFOIL (e472-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 472 AIRFOIL (e472-il) Reynolds number: 200,000 Max Cl/Cd: 41.37 at α=8° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e472-il-200000.txt Download as CSV file: xf-e472-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.750 -1.0500 0.08283 0.07842 -0.0288 1.0000 0.0746
-15.500 -1.1423 0.06419 0.05942 -0.0420 1.0000 0.0732
-15.250 -1.1819 0.05556 0.05052 -0.0479 1.0000 0.0736
-15.000 -1.2088 0.04979 0.04448 -0.0509 1.0000 0.0743
-14.750 -1.2309 0.04554 0.03994 -0.0519 1.0000 0.0751
-14.500 -1.2296 0.04345 0.03788 -0.0513 1.0000 0.0772
-14.250 -1.2197 0.04265 0.03714 -0.0504 1.0000 0.0793
-14.000 -1.2217 0.04101 0.03541 -0.0490 1.0000 0.0812
-13.750 -1.2293 0.03923 0.03346 -0.0466 1.0000 0.0830
-13.500 -1.2402 0.03757 0.03155 -0.0430 1.0000 0.0847
-13.250 -1.2469 0.03602 0.02981 -0.0392 1.0000 0.0864
-13.000 -1.2320 0.03537 0.02929 -0.0376 1.0000 0.0889
-12.750 -1.2198 0.03497 0.02889 -0.0356 1.0000 0.0915
-12.500 -1.2138 0.03406 0.02783 -0.0329 1.0000 0.0943
-12.250 -1.2105 0.03303 0.02647 -0.0298 1.0000 0.0968
-12.000 -1.1952 0.03197 0.02548 -0.0284 1.0000 0.0997
-11.750 -1.1767 0.03179 0.02537 -0.0269 1.0000 0.1025
-11.500 -1.1635 0.03115 0.02461 -0.0248 1.0000 0.1057
-11.250 -1.1538 0.03024 0.02340 -0.0222 1.0000 0.1086
-11.000 -1.1373 0.02912 0.02226 -0.0207 1.0000 0.1115
-10.750 -1.1169 0.02886 0.02207 -0.0195 1.0000 0.1144
-10.500 -1.0998 0.02830 0.02142 -0.0177 1.0000 0.1177
-10.250 -1.0855 0.02755 0.02041 -0.0156 1.0000 0.1211
-10.000 -1.0678 0.02649 0.01929 -0.0141 1.0000 0.1242
-9.750 -1.0464 0.02612 0.01897 -0.0129 1.0000 0.1271
-9.500 -1.0270 0.02565 0.01844 -0.0114 1.0000 0.1305
-9.250 -1.0094 0.02503 0.01760 -0.0096 1.0000 0.1341
-9.000 -0.9905 0.02409 0.01656 -0.0081 1.0000 0.1374
-8.750 -0.9684 0.02367 0.01620 -0.0070 1.0000 0.1405
-8.500 -0.9475 0.02325 0.01574 -0.0056 1.0000 0.1441
-8.250 -0.9280 0.02277 0.01507 -0.0040 1.0000 0.1481
-8.000 -0.9076 0.02194 0.01415 -0.0026 1.0000 0.1517
-7.750 -0.8851 0.02148 0.01376 -0.0016 1.0000 0.1549
-7.500 -0.8633 0.02112 0.01336 -0.0003 1.0000 0.1589
-7.250 -0.8424 0.02071 0.01278 0.0012 1.0000 0.1630
-7.000 -0.8208 0.01995 0.01196 0.0024 1.0000 0.1668
-6.750 -0.7980 0.01952 0.01160 0.0035 1.0000 0.1704
-6.500 -0.7757 0.01918 0.01122 0.0047 1.0000 0.1747
-6.250 -0.7540 0.01884 0.01073 0.0061 1.0000 0.1790
-6.000 -0.7313 0.01813 0.01003 0.0072 1.0000 0.1828
-5.750 -0.7084 0.01775 0.00971 0.0083 1.0000 0.1869
-5.500 -0.6858 0.01744 0.00936 0.0095 1.0000 0.1916
-5.250 -0.6636 0.01720 0.00896 0.0109 1.0000 0.1958
-5.000 -0.6403 0.01652 0.00840 0.0118 1.0000 0.2001
-4.750 -0.6174 0.01622 0.00813 0.0130 1.0000 0.2047
-4.500 -0.5948 0.01596 0.00781 0.0142 1.0000 0.2098
-4.250 -0.5719 0.01551 0.00737 0.0153 1.0000 0.2144
-4.000 -0.5491 0.01517 0.00710 0.0164 1.0000 0.2189
-3.750 -0.5264 0.01493 0.00686 0.0176 1.0000 0.2243
-3.500 -0.5039 0.01465 0.00655 0.0188 1.0000 0.2296
-3.250 -0.4815 0.01432 0.00633 0.0200 1.0000 0.2350
-3.000 -0.4591 0.01411 0.00615 0.0212 1.0000 0.2407
-2.750 -0.4369 0.01387 0.00593 0.0224 1.0000 0.2466
-2.500 -0.4153 0.01364 0.00581 0.0236 1.0000 0.2528
-2.250 -0.3938 0.01352 0.00570 0.0249 1.0000 0.2599
-2.000 -0.3462 0.01326 0.00561 0.0209 0.9925 0.2697
-1.750 -0.2929 0.01296 0.00542 0.0159 0.9815 0.2824
-1.500 -0.2458 0.01256 0.00515 0.0123 0.9655 0.2965
-1.250 -0.2031 0.01210 0.00484 0.0098 0.9449 0.3122
-1.000 -0.1619 0.01157 0.00451 0.0077 0.9175 0.3316
-0.750 -0.0959 0.01094 0.00412 0.0005 0.8678 0.3679
-0.500 -0.0349 0.01058 0.00373 -0.0054 0.7485 0.4236
-0.250 -0.0151 0.01064 0.00361 -0.0031 0.6416 0.4799
0.000 0.0000 0.01068 0.00358 0.0000 0.5521 0.5522
0.250 0.0151 0.01064 0.00361 0.0031 0.4800 0.6416
0.500 0.0349 0.01058 0.00373 0.0054 0.4236 0.7486
0.750 0.0958 0.01095 0.00412 -0.0005 0.3677 0.8677
1.000 0.1618 0.01157 0.00451 -0.0077 0.3318 0.9174
1.250 0.2032 0.01210 0.00484 -0.0098 0.3122 0.9449
1.500 0.2457 0.01256 0.00515 -0.0123 0.2965 0.9654
1.750 0.2930 0.01296 0.00543 -0.0159 0.2825 0.9816
2.000 0.3463 0.01326 0.00561 -0.0209 0.2697 0.9926
2.250 0.3938 0.01353 0.00570 -0.0249 0.2599 1.0000
2.500 0.4153 0.01364 0.00581 -0.0236 0.2529 1.0000
2.750 0.4369 0.01388 0.00593 -0.0224 0.2466 1.0000
3.000 0.4591 0.01411 0.00615 -0.0212 0.2407 1.0000
3.250 0.4815 0.01431 0.00633 -0.0200 0.2350 1.0000
3.500 0.5038 0.01464 0.00655 -0.0188 0.2296 1.0000
3.750 0.5264 0.01492 0.00685 -0.0176 0.2243 1.0000
4.000 0.5491 0.01517 0.00710 -0.0164 0.2190 1.0000
4.250 0.5719 0.01551 0.00737 -0.0153 0.2144 1.0000
4.500 0.5948 0.01596 0.00781 -0.0142 0.2099 1.0000
4.750 0.6174 0.01622 0.00813 -0.0130 0.2047 1.0000
5.000 0.6403 0.01652 0.00840 -0.0118 0.2001 1.0000
5.250 0.6635 0.01719 0.00896 -0.0109 0.1958 1.0000
5.500 0.6858 0.01744 0.00936 -0.0095 0.1916 1.0000
5.750 0.7084 0.01775 0.00971 -0.0083 0.1869 1.0000
6.000 0.7313 0.01813 0.01003 -0.0072 0.1828 1.0000
6.250 0.7540 0.01883 0.01073 -0.0061 0.1790 1.0000
6.500 0.7757 0.01917 0.01122 -0.0047 0.1747 1.0000
6.750 0.7980 0.01953 0.01161 -0.0035 0.1704 1.0000
7.000 0.8208 0.01995 0.01197 -0.0024 0.1668 1.0000
7.250 0.8425 0.02071 0.01278 -0.0012 0.1631 1.0000
7.500 0.8634 0.02112 0.01336 0.0003 0.1590 1.0000
7.750 0.8851 0.02149 0.01376 0.0016 0.1550 1.0000
8.000 0.9076 0.02194 0.01415 0.0026 0.1517 1.0000
8.250 0.9280 0.02277 0.01507 0.0040 0.1481 1.0000
8.500 0.9476 0.02325 0.01573 0.0056 0.1441 1.0000
8.750 0.9685 0.02366 0.01620 0.0070 0.1405 1.0000
9.000 0.9905 0.02410 0.01657 0.0081 0.1375 1.0000
9.250 1.0095 0.02504 0.01760 0.0096 0.1341 1.0000
9.500 1.0270 0.02566 0.01844 0.0114 0.1305 1.0000
9.750 1.0464 0.02613 0.01899 0.0129 0.1271 1.0000
10.000 1.0679 0.02647 0.01927 0.0141 0.1241 1.0000
10.250 1.0855 0.02755 0.02041 0.0156 0.1210 1.0000
10.500 1.0999 0.02830 0.02141 0.0177 0.1177 1.0000
10.750 1.1170 0.02885 0.02206 0.0195 0.1144 1.0000
11.000 1.1373 0.02912 0.02227 0.0207 0.1116 1.0000
11.250 1.1538 0.03024 0.02339 0.0222 0.1086 1.0000
11.500 1.1636 0.03113 0.02458 0.0248 0.1057 1.0000
11.750 1.1769 0.03178 0.02535 0.0269 0.1025 1.0000
12.000 1.1953 0.03197 0.02549 0.0283 0.0997 1.0000
12.250 1.2107 0.03301 0.02645 0.0298 0.0968 1.0000
12.500 1.2138 0.03408 0.02784 0.0329 0.0943 1.0000
12.750 1.2202 0.03493 0.02885 0.0355 0.0915 1.0000
13.000 1.2325 0.03533 0.02924 0.0376 0.0889 1.0000
13.250 1.2474 0.03602 0.02981 0.0391 0.0864 1.0000
13.500 1.2406 0.03757 0.03156 0.0429 0.0847 1.0000
13.750 1.2297 0.03923 0.03346 0.0466 0.0830 1.0000
14.000 1.2222 0.04100 0.03540 0.0489 0.0811 1.0000
14.250 1.2215 0.04251 0.03699 0.0503 0.0792 1.0000
14.500 1.2313 0.04336 0.03778 0.0512 0.0771 1.0000
14.750 1.2315 0.04558 0.03998 0.0519 0.0751 1.0000
15.000 1.2092 0.04981 0.04450 0.0508 0.0743 1.0000
15.250 1.1826 0.05559 0.05055 0.0477 0.0736 1.0000
15.500 1.1437 0.06413 0.05937 0.0419 0.0733 1.0000
15.750 1.0004 0.09204 0.08774 0.0222 0.0755 1.0000
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