EPPLER 559 AIRFOIL (e559-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 559 AIRFOIL (e559-il) Reynolds number: 500,000 Max Cl/Cd: 101.88 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e559-il-500000-n5.txt Download as CSV file: xf-e559-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 559 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
------ -------- --------- --------- -------- -------- --------
-15.750 -0.7389 0.08946 0.08562 -0.0585 1.0000 0.0131
-15.500 -0.7441 0.08543 0.08153 -0.0602 1.0000 0.0132
-15.250 -0.7495 0.08145 0.07749 -0.0618 1.0000 0.0134
-15.000 -0.7556 0.07749 0.07348 -0.0634 1.0000 0.0135
-14.750 -0.7612 0.07362 0.06954 -0.0649 1.0000 0.0137
-14.500 -0.7675 0.06983 0.06569 -0.0663 1.0000 0.0139
-14.250 -0.7751 0.06600 0.06180 -0.0677 1.0000 0.0139
-14.000 -0.7829 0.06232 0.05806 -0.0689 1.0000 0.0140
-13.750 -0.7936 0.05858 0.05427 -0.0700 1.0000 0.0141
-13.500 -0.8047 0.05495 0.05058 -0.0708 1.0000 0.0142
-13.250 -0.8183 0.05129 0.04685 -0.0715 1.0000 0.0142
-13.000 -0.8358 0.04747 0.04298 -0.0720 1.0000 0.0143
-12.750 -0.8508 0.04337 0.03882 -0.0736 0.9993 0.0144
-12.500 -0.8472 0.03836 0.03371 -0.0804 0.9953 0.0146
-12.250 -0.8438 0.03364 0.02888 -0.0867 0.9897 0.0149
-12.000 -0.8253 0.02884 0.02392 -0.0958 0.9844 0.0151
-11.750 -0.8030 0.02552 0.02046 -0.1023 0.9786 0.0155
-11.500 -0.7773 0.02385 0.01867 -0.1053 0.9740 0.0160
-11.250 -0.7475 0.02249 0.01722 -0.1082 0.9708 0.0166
-11.000 -0.7283 0.02142 0.01605 -0.1083 0.9630 0.0171
-10.500 -0.6789 0.01923 0.01372 -0.1103 0.9497 0.0183
-10.250 -0.6514 0.01831 0.01274 -0.1114 0.9436 0.0189
-10.000 -0.6253 0.01753 0.01189 -0.1119 0.9356 0.0196
-9.750 -0.5930 0.01679 0.01106 -0.1135 0.9306 0.0205
-9.500 -0.5624 0.01606 0.01027 -0.1147 0.9223 0.0215
-9.250 -0.5245 0.01526 0.00941 -0.1175 0.9170 0.0229
-9.000 -0.4862 0.01462 0.00870 -0.1201 0.9086 0.0245
-8.750 -0.4385 0.01391 0.00793 -0.1247 0.9015 0.0272
-8.500 -0.3919 0.01326 0.00723 -0.1291 0.8900 0.0324
-8.250 -0.3487 0.01261 0.00656 -0.1329 0.8744 0.0434
-8.000 -0.3124 0.01211 0.00601 -0.1350 0.8555 0.0562
-7.750 -0.2814 0.01172 0.00557 -0.1360 0.8353 0.0686
-7.500 -0.2538 0.01139 0.00518 -0.1362 0.8162 0.0818
-7.250 -0.2271 0.01111 0.00486 -0.1361 0.7975 0.0950
-7.000 -0.2008 0.01088 0.00458 -0.1359 0.7800 0.1077
-6.750 -0.1746 0.01068 0.00433 -0.1356 0.7635 0.1195
-6.500 -0.1484 0.01050 0.00409 -0.1354 0.7477 0.1327
-6.250 -0.1221 0.01032 0.00388 -0.1351 0.7329 0.1476
-6.000 -0.0956 0.01019 0.00371 -0.1348 0.7183 0.1601
-5.750 -0.0688 0.01008 0.00355 -0.1346 0.7044 0.1727
-5.500 -0.0420 0.00997 0.00340 -0.1344 0.6915 0.1841
-5.250 -0.0151 0.00989 0.00327 -0.1341 0.6787 0.1948
-4.750 0.0392 0.00977 0.00306 -0.1337 0.6543 0.2163
-4.500 0.0664 0.00972 0.00297 -0.1335 0.6427 0.2251
-4.250 0.0936 0.00971 0.00287 -0.1333 0.6311 0.2329
-4.000 0.1211 0.00967 0.00280 -0.1331 0.6202 0.2403
-3.750 0.1486 0.00966 0.00273 -0.1329 0.6100 0.2476
-3.250 0.2036 0.00964 0.00261 -0.1326 0.5889 0.2614
-3.000 0.2310 0.00965 0.00256 -0.1324 0.5798 0.2680
-2.750 0.2587 0.00964 0.00253 -0.1322 0.5699 0.2752
-2.500 0.2862 0.00967 0.00249 -0.1320 0.5607 0.2821
-2.250 0.3137 0.00967 0.00247 -0.1319 0.5510 0.2888
-2.000 0.3414 0.00969 0.00246 -0.1317 0.5427 0.2957
-1.750 0.3689 0.00972 0.00244 -0.1315 0.5339 0.3022
-1.500 0.3966 0.00974 0.00245 -0.1314 0.5254 0.3090
-1.250 0.4239 0.00980 0.00245 -0.1312 0.5166 0.3154
-1.000 0.4516 0.00982 0.00246 -0.1310 0.5091 0.3225
-0.750 0.4790 0.00987 0.00248 -0.1308 0.5012 0.3291
-0.500 0.5066 0.00992 0.00250 -0.1307 0.4939 0.3355
-0.250 0.5339 0.00996 0.00254 -0.1305 0.4856 0.3428
0.000 0.5612 0.01004 0.00257 -0.1303 0.4788 0.3495
0.250 0.5888 0.01007 0.00262 -0.1301 0.4719 0.3561
0.500 0.6157 0.01016 0.00267 -0.1299 0.4650 0.3638
0.750 0.6433 0.01021 0.00273 -0.1297 0.4581 0.3705
1.000 0.6703 0.01029 0.00279 -0.1295 0.4512 0.3777
1.250 0.6975 0.01037 0.00286 -0.1293 0.4455 0.3851
1.500 0.7248 0.01043 0.00294 -0.1291 0.4393 0.3930
1.750 0.7513 0.01054 0.00303 -0.1287 0.4329 0.4003
2.000 0.7786 0.01060 0.00312 -0.1286 0.4271 0.4081
2.250 0.8055 0.01069 0.00321 -0.1283 0.4212 0.4167
2.500 0.8318 0.01080 0.00332 -0.1280 0.4159 0.4251
2.750 0.8590 0.01088 0.00342 -0.1278 0.4108 0.4339
3.000 0.8856 0.01097 0.00355 -0.1275 0.4049 0.4434
3.500 0.9384 0.01118 0.00381 -0.1268 0.3950 0.4642
3.750 0.9648 0.01128 0.00394 -0.1265 0.3899 0.4754
4.250 1.0167 0.01152 0.00425 -0.1257 0.3799 0.5027
4.500 1.0429 0.01162 0.00441 -0.1254 0.3750 0.5177
4.750 1.0682 0.01176 0.00459 -0.1249 0.3700 0.5357
5.000 1.0936 0.01189 0.00478 -0.1244 0.3654 0.5555
5.250 1.1195 0.01199 0.00496 -0.1241 0.3604 0.5777
5.500 1.1444 0.01211 0.00516 -0.1235 0.3553 0.6047
5.750 1.1686 0.01226 0.00539 -0.1229 0.3503 0.6355
6.000 1.1939 0.01234 0.00561 -0.1224 0.3457 0.6722
6.250 1.2179 0.01244 0.00584 -0.1217 0.3405 0.7176
6.500 1.2397 0.01256 0.00610 -0.1205 0.3354 0.7756
7.000 1.2786 0.01255 0.00646 -0.1168 0.3259 1.0000
7.250 1.3004 0.01280 0.00670 -0.1158 0.3204 1.0000
7.500 1.3232 0.01302 0.00694 -0.1149 0.3154 1.0000
7.750 1.3453 0.01326 0.00718 -0.1138 0.3093 1.0000
8.000 1.3653 0.01357 0.00747 -0.1125 0.3036 1.0000
8.250 1.3875 0.01381 0.00774 -0.1115 0.2975 1.0000
8.500 1.4075 0.01412 0.00804 -0.1101 0.2907 1.0000
8.750 1.4278 0.01443 0.00836 -0.1089 0.2844 1.0000
9.000 1.4473 0.01476 0.00870 -0.1075 0.2768 1.0000
9.250 1.4657 0.01513 0.00907 -0.1060 0.2696 1.0000
9.500 1.4844 0.01550 0.00945 -0.1045 0.2617 1.0000
9.750 1.5015 0.01594 0.00988 -0.1029 0.2536 1.0000
10.000 1.5177 0.01642 0.01035 -0.1011 0.2443 1.0000
10.250 1.5340 0.01690 0.01084 -0.0994 0.2357 1.0000
10.500 1.5475 0.01751 0.01142 -0.0973 0.2260 1.0000
10.750 1.5608 0.01814 0.01204 -0.0953 0.2147 1.0000
11.000 1.5725 0.01887 0.01275 -0.0931 0.2032 1.0000
11.250 1.5819 0.01973 0.01358 -0.0907 0.1911 1.0000
11.500 1.5901 0.02068 0.01451 -0.0883 0.1799 1.0000
11.750 1.5965 0.02178 0.01558 -0.0859 0.1684 1.0000
12.000 1.6031 0.02292 0.01671 -0.0836 0.1577 1.0000
12.250 1.6074 0.02426 0.01803 -0.0812 0.1466 1.0000
12.500 1.6094 0.02582 0.01957 -0.0789 0.1353 1.0000
12.750 1.6109 0.02752 0.02126 -0.0767 0.1255 1.0000
13.000 1.6119 0.02937 0.02311 -0.0748 0.1163 1.0000
13.250 1.6114 0.03145 0.02519 -0.0730 0.1066 1.0000
13.500 1.6096 0.03376 0.02750 -0.0714 0.0980 1.0000
13.750 1.6049 0.03647 0.03020 -0.0700 0.0892 1.0000
14.000 1.6030 0.03907 0.03283 -0.0689 0.0821 1.0000
14.250 1.5991 0.04200 0.03579 -0.0681 0.0759 1.0000
14.500 1.5950 0.04508 0.03891 -0.0675 0.0702 1.0000
14.750 1.5896 0.04845 0.04232 -0.0671 0.0646 1.0000
15.000 1.5858 0.05175 0.04567 -0.0669 0.0607 1.0000
15.250 1.5798 0.05545 0.04943 -0.0669 0.0567 1.0000
15.500 1.5749 0.05914 0.05319 -0.0671 0.0531 1.0000
15.750 1.5679 0.06321 0.05731 -0.0675 0.0499 1.0000
16.000 1.5639 0.06699 0.06118 -0.0680 0.0474 1.0000
16.250 1.5581 0.07113 0.06539 -0.0687 0.0447 1.0000
16.500 1.5502 0.07565 0.06998 -0.0696 0.0422 1.0000
16.750 1.5454 0.07982 0.07423 -0.0706 0.0401 1.0000
17.000 1.5394 0.08425 0.07874 -0.0717 0.0379 1.0000
17.250 1.5316 0.08905 0.08361 -0.0730 0.0359 1.0000
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Polar data table (+)
Polar graphs
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