EPPLER 473 AIRFOIL (e473-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 473 AIRFOIL (e473-il) Reynolds number: 200,000 Max Cl/Cd: 53.76 at α=10° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e473-il-200000-n5.txt Download as CSV file: xf-e473-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 473 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-17.250 -1.0526 0.09379 0.08855 -0.0212 1.0000 0.0734
-17.000 -1.0673 0.08816 0.08279 -0.0238 1.0000 0.0758
-16.750 -1.0831 0.08265 0.07728 -0.0263 1.0000 0.0780
-16.500 -1.1017 0.07679 0.07136 -0.0290 1.0000 0.0803
-16.250 -1.1211 0.07102 0.06549 -0.0316 1.0000 0.0827
-16.000 -1.1388 0.06560 0.05995 -0.0339 1.0000 0.0849
-15.750 -1.1580 0.06008 0.05434 -0.0363 1.0000 0.0869
-15.500 -1.1784 0.05443 0.04862 -0.0388 1.0000 0.0890
-15.250 -1.1952 0.04934 0.04342 -0.0410 1.0000 0.0915
-15.000 -1.2072 0.04496 0.03891 -0.0428 1.0000 0.0942
-14.750 -1.2160 0.04117 0.03499 -0.0441 1.0000 0.0971
-14.500 -1.2264 0.03755 0.03130 -0.0451 1.0000 0.1000
-14.250 -1.2323 0.03473 0.02840 -0.0452 1.0000 0.1036
-14.000 -1.2329 0.03266 0.02619 -0.0446 1.0000 0.1073
-13.750 -1.2364 0.03069 0.02417 -0.0434 1.0000 0.1109
-13.500 -1.2367 0.02916 0.02258 -0.0416 1.0000 0.1152
-13.250 -1.2321 0.02801 0.02132 -0.0397 1.0000 0.1199
-13.000 -1.2314 0.02688 0.02018 -0.0371 1.0000 0.1242
-12.750 -1.2269 0.02600 0.01925 -0.0344 1.0000 0.1290
-12.500 -1.2205 0.02526 0.01842 -0.0316 1.0000 0.1338
-12.250 -1.2170 0.02458 0.01773 -0.0282 1.0000 0.1381
-12.000 -1.2095 0.02399 0.01708 -0.0252 1.0000 0.1429
-11.750 -1.1981 0.02341 0.01642 -0.0228 1.0000 0.1474
-11.500 -1.1869 0.02286 0.01587 -0.0203 1.0000 0.1518
-11.250 -1.1727 0.02237 0.01530 -0.0181 1.0000 0.1567
-11.000 -1.1576 0.02189 0.01474 -0.0161 1.0000 0.1612
-10.750 -1.1427 0.02146 0.01431 -0.0140 1.0000 0.1657
-10.500 -1.1258 0.02106 0.01383 -0.0122 1.0000 0.1706
-10.250 -1.1084 0.02065 0.01335 -0.0104 1.0000 0.1751
-10.000 -1.0913 0.02030 0.01301 -0.0086 1.0000 0.1794
-9.750 -1.0727 0.01996 0.01259 -0.0069 1.0000 0.1842
-9.500 -1.0534 0.01961 0.01214 -0.0054 1.0000 0.1886
-9.250 -1.0350 0.01929 0.01185 -0.0037 1.0000 0.1925
-9.000 -1.0155 0.01900 0.01152 -0.0021 1.0000 0.1966
-8.750 -0.9952 0.01871 0.01112 -0.0007 1.0000 0.2011
-8.500 -0.9752 0.01840 0.01077 0.0008 1.0000 0.2047
-8.250 -0.9552 0.01813 0.01051 0.0023 1.0000 0.2083
-8.000 -0.9347 0.01788 0.01021 0.0038 1.0000 0.2123
-7.750 -0.9137 0.01762 0.00987 0.0052 1.0000 0.2164
-7.500 -0.8930 0.01734 0.00956 0.0066 1.0000 0.2198
-7.250 -0.8723 0.01710 0.00934 0.0080 1.0000 0.2232
-7.000 -0.8514 0.01688 0.00910 0.0094 1.0000 0.2269
-6.750 -0.8302 0.01666 0.00882 0.0107 1.0000 0.2307
-6.500 -0.8089 0.01645 0.00853 0.0121 1.0000 0.2342
-6.250 -0.7766 0.01620 0.00833 0.0111 0.9967 0.2379
-6.000 -0.7355 0.01598 0.00811 0.0084 0.9897 0.2422
-5.750 -0.6953 0.01577 0.00784 0.0060 0.9818 0.2468
-5.500 -0.6607 0.01551 0.00753 0.0047 0.9703 0.2507
-5.000 -0.5976 0.01492 0.00700 0.0036 0.9351 0.2577
-4.750 -0.5550 0.01467 0.00671 0.0009 0.9117 0.2624
-4.500 -0.4975 0.01439 0.00633 -0.0049 0.8776 0.2673
-4.250 -0.4362 0.01408 0.00593 -0.0114 0.8146 0.2720
-4.000 -0.3998 0.01407 0.00565 -0.0126 0.7412 0.2764
-3.750 -0.3743 0.01414 0.00544 -0.0118 0.6802 0.2803
-3.500 -0.3504 0.01420 0.00525 -0.0107 0.6297 0.2838
-3.250 -0.3270 0.01418 0.00510 -0.0095 0.5878 0.2870
-3.000 -0.3032 0.01420 0.00498 -0.0085 0.5512 0.2908
-2.750 -0.2789 0.01422 0.00485 -0.0076 0.5186 0.2951
-2.500 -0.2541 0.01425 0.00472 -0.0068 0.4901 0.2992
-2.250 -0.2294 0.01422 0.00461 -0.0060 0.4654 0.3029
-2.000 -0.2046 0.01420 0.00452 -0.0052 0.4449 0.3069
-1.750 -0.1792 0.01419 0.00444 -0.0045 0.4277 0.3118
-1.500 -0.1534 0.01420 0.00436 -0.0039 0.4127 0.3169
-1.250 -0.1282 0.01416 0.00430 -0.0032 0.3993 0.3214
-1.000 -0.1030 0.01416 0.00425 -0.0025 0.3873 0.3263
-0.750 -0.0770 0.01415 0.00421 -0.0019 0.3761 0.3321
-0.500 -0.0514 0.01415 0.00418 -0.0012 0.3671 0.3380
-0.250 -0.0258 0.01412 0.00417 -0.0006 0.3587 0.3446
0.000 0.0000 0.01416 0.00416 0.0000 0.3517 0.3518
0.250 0.0258 0.01412 0.00417 0.0006 0.3446 0.3587
0.500 0.0514 0.01415 0.00418 0.0012 0.3379 0.3670
0.750 0.0770 0.01415 0.00421 0.0019 0.3321 0.3760
1.000 0.1030 0.01416 0.00425 0.0025 0.3263 0.3872
1.250 0.1282 0.01416 0.00430 0.0032 0.3214 0.3994
1.500 0.1534 0.01420 0.00436 0.0039 0.3169 0.4126
1.750 0.1792 0.01419 0.00444 0.0045 0.3119 0.4277
2.000 0.2046 0.01420 0.00452 0.0052 0.3070 0.4449
2.250 0.2294 0.01422 0.00461 0.0060 0.3028 0.4653
2.500 0.2541 0.01425 0.00472 0.0068 0.2992 0.4899
2.750 0.2789 0.01422 0.00485 0.0076 0.2950 0.5184
3.000 0.3032 0.01420 0.00498 0.0085 0.2908 0.5512
3.250 0.3270 0.01418 0.00510 0.0095 0.2870 0.5878
3.500 0.3504 0.01420 0.00525 0.0107 0.2838 0.6298
3.750 0.3743 0.01414 0.00544 0.0118 0.2804 0.6806
4.000 0.3999 0.01407 0.00565 0.0126 0.2763 0.7425
4.250 0.4364 0.01408 0.00593 0.0113 0.2720 0.8154
4.500 0.4974 0.01438 0.00633 0.0049 0.2674 0.8776
4.750 0.5550 0.01467 0.00671 -0.0009 0.2624 0.9117
5.000 0.5975 0.01492 0.00700 -0.0036 0.2577 0.9351
5.500 0.6609 0.01551 0.00753 -0.0048 0.2507 0.9704
5.750 0.6953 0.01576 0.00784 -0.0060 0.2467 0.9818
6.000 0.7356 0.01598 0.00811 -0.0085 0.2422 0.9897
6.250 0.7764 0.01619 0.00833 -0.0111 0.2379 0.9967
6.500 0.8089 0.01645 0.00853 -0.0121 0.2342 1.0000
6.750 0.8301 0.01666 0.00882 -0.0107 0.2307 1.0000
7.000 0.8513 0.01688 0.00909 -0.0094 0.2269 1.0000
7.250 0.8723 0.01709 0.00933 -0.0080 0.2231 1.0000
7.500 0.8929 0.01734 0.00956 -0.0066 0.2198 1.0000
7.750 0.9137 0.01762 0.00987 -0.0052 0.2164 1.0000
8.000 0.9346 0.01788 0.01021 -0.0038 0.2123 1.0000
8.250 0.9552 0.01813 0.01051 -0.0023 0.2083 1.0000
8.500 0.9752 0.01840 0.01077 -0.0008 0.2048 1.0000
8.750 0.9952 0.01871 0.01111 0.0007 0.2010 1.0000
9.000 1.0154 0.01900 0.01152 0.0021 0.1966 1.0000
9.250 1.0349 0.01929 0.01184 0.0037 0.1924 1.0000
9.500 1.0534 0.01961 0.01213 0.0054 0.1886 1.0000
9.750 1.0728 0.01996 0.01259 0.0069 0.1841 1.0000
10.000 1.0913 0.02030 0.01300 0.0086 0.1794 1.0000
10.250 1.1084 0.02065 0.01335 0.0104 0.1751 1.0000
10.500 1.1259 0.02105 0.01383 0.0122 0.1705 1.0000
10.750 1.1428 0.02145 0.01430 0.0140 0.1656 1.0000
11.000 1.1577 0.02189 0.01474 0.0161 0.1612 1.0000
11.250 1.1729 0.02237 0.01530 0.0181 0.1568 1.0000
11.500 1.1871 0.02286 0.01587 0.0202 0.1519 1.0000
11.750 1.1983 0.02340 0.01641 0.0227 0.1474 1.0000
12.000 1.2097 0.02399 0.01707 0.0251 0.1429 1.0000
12.250 1.2174 0.02457 0.01772 0.0282 0.1380 1.0000
12.500 1.2208 0.02526 0.01842 0.0316 0.1338 1.0000
12.750 1.2274 0.02600 0.01924 0.0343 0.1290 1.0000
13.000 1.2319 0.02687 0.02017 0.0370 0.1241 1.0000
13.250 1.2329 0.02800 0.02130 0.0396 0.1199 1.0000
13.500 1.2374 0.02914 0.02257 0.0415 0.1152 1.0000
13.750 1.2371 0.03067 0.02416 0.0433 0.1109 1.0000
14.000 1.2340 0.03263 0.02616 0.0445 0.1072 1.0000
14.250 1.2331 0.03473 0.02839 0.0451 0.1033 1.0000
14.500 1.2276 0.03750 0.03125 0.0450 0.0999 1.0000
14.750 1.2172 0.04113 0.03495 0.0440 0.0970 1.0000
15.000 1.2089 0.04488 0.03883 0.0427 0.0942 1.0000
15.250 1.1969 0.04926 0.04334 0.0409 0.0914 1.0000
15.500 1.1803 0.05436 0.04854 0.0387 0.0890 1.0000
15.750 1.1598 0.06002 0.05427 0.0361 0.0868 1.0000
16.000 1.1410 0.06549 0.05984 0.0337 0.0848 1.0000
16.250 1.1227 0.07101 0.06548 0.0313 0.0825 1.0000
16.500 1.1039 0.07671 0.07128 0.0288 0.0802 1.0000
16.750 1.0858 0.08249 0.07711 0.0261 0.0780 1.0000
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Polar data table (+)
Polar graphs
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