EPPLER 580 AIRFOIL (e580-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 580 AIRFOIL (e580-il) Reynolds number: 100,000 Max Cl/Cd: 54.39 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e580-il-100000-n5.txt Download as CSV file: xf-e580-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 580 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.4090 0.08185 0.07700 -0.0707 0.9912 0.0303
-9.750 -0.4128 0.07528 0.07035 -0.0775 0.9854 0.0301
-9.500 -0.4216 0.06923 0.06418 -0.0837 0.9773 0.0298
-9.250 -0.4316 0.06406 0.05885 -0.0890 0.9677 0.0296
-9.000 -0.4415 0.05960 0.05419 -0.0931 0.9563 0.0294
-8.750 -0.4401 0.05477 0.04906 -0.0978 0.9461 0.0292
-8.500 -0.4385 0.05083 0.04481 -0.0996 0.9350 0.0291
-8.250 -0.4302 0.04720 0.04083 -0.1012 0.9256 0.0290
-8.000 -0.4115 0.04346 0.03666 -0.1038 0.9196 0.0290
-7.750 -0.3966 0.04057 0.03338 -0.1043 0.9108 0.0291
-7.500 -0.3703 0.03768 0.03007 -0.1063 0.9059 0.0292
-7.250 -0.3471 0.03536 0.02739 -0.1069 0.8992 0.0295
-7.000 -0.3203 0.03334 0.02503 -0.1077 0.8933 0.0299
-6.750 -0.2877 0.03142 0.02289 -0.1094 0.8899 0.0311
-6.500 -0.2652 0.03025 0.02167 -0.1092 0.8821 0.0323
-6.250 -0.2345 0.02892 0.02022 -0.1102 0.8774 0.0336
-6.000 -0.2002 0.02752 0.01868 -0.1114 0.8744 0.0345
-5.750 -0.1783 0.02657 0.01766 -0.1105 0.8660 0.0353
-5.500 -0.1464 0.02549 0.01650 -0.1113 0.8616 0.0364
-5.250 -0.1102 0.02444 0.01536 -0.1130 0.8586 0.0377
-5.000 -0.0894 0.02366 0.01459 -0.1123 0.8492 0.0393
-4.750 -0.0530 0.02280 0.01369 -0.1144 0.8451 0.0431
-4.500 -0.0236 0.02212 0.01293 -0.1153 0.8381 0.0481
-4.250 0.0103 0.02133 0.01207 -0.1171 0.8321 0.0552
-4.000 0.0516 0.02016 0.01100 -0.1205 0.8283 0.0845
-3.750 0.0862 0.01787 0.01007 -0.1253 0.8204 0.3481
-3.500 0.1190 0.01833 0.01096 -0.1253 0.8147 0.5163
-3.250 0.1434 0.01941 0.01204 -0.1230 0.8069 0.5653
-3.000 0.1690 0.02029 0.01287 -0.1209 0.8000 0.5946
-2.750 0.1966 0.02060 0.01306 -0.1199 0.7933 0.6072
-2.500 0.2270 0.02047 0.01277 -0.1205 0.7858 0.6119
-2.250 0.2622 0.02029 0.01242 -0.1218 0.7803 0.6156
-2.000 0.2899 0.02019 0.01217 -0.1221 0.7716 0.6201
-1.750 0.3307 0.01986 0.01161 -0.1251 0.7662 0.6253
-1.500 0.3546 0.01986 0.01154 -0.1244 0.7573 0.6278
-1.250 0.3890 0.01971 0.01125 -0.1257 0.7513 0.6308
-1.000 0.4157 0.01967 0.01113 -0.1258 0.7427 0.6342
-0.750 0.4509 0.01952 0.01082 -0.1275 0.7364 0.6384
-0.500 0.4797 0.01947 0.01067 -0.1281 0.7283 0.6418
-0.250 0.5103 0.01941 0.01053 -0.1287 0.7215 0.6442
0.000 0.5375 0.01942 0.01049 -0.1287 0.7139 0.6471
0.250 0.5678 0.01940 0.01039 -0.1294 0.7068 0.6505
0.500 0.5981 0.01938 0.01029 -0.1303 0.6997 0.6540
0.750 0.6279 0.01938 0.01022 -0.1310 0.6921 0.6574
1.000 0.6566 0.01941 0.01020 -0.1312 0.6856 0.6599
1.250 0.6823 0.01949 0.01028 -0.1310 0.6777 0.6629
1.500 0.7139 0.01949 0.01021 -0.1318 0.6716 0.6660
1.750 0.7392 0.01960 0.01032 -0.1318 0.6633 0.6695
2.000 0.7719 0.01961 0.01025 -0.1329 0.6572 0.6731
2.250 0.7941 0.01977 0.01047 -0.1320 0.6490 0.6758
2.500 0.8235 0.01982 0.01049 -0.1324 0.6425 0.6789
2.750 0.8481 0.01998 0.01069 -0.1321 0.6347 0.6822
3.000 0.8778 0.02006 0.01073 -0.1327 0.6278 0.6859
3.250 0.9033 0.02022 0.01093 -0.1325 0.6202 0.6894
3.500 0.9296 0.02033 0.01108 -0.1323 0.6130 0.6925
3.750 0.9550 0.02050 0.01129 -0.1320 0.6057 0.6961
4.000 0.9815 0.02065 0.01146 -0.1320 0.5980 0.7000
4.250 1.0087 0.02083 0.01165 -0.1322 0.5907 0.7040
4.500 1.0325 0.02100 0.01191 -0.1316 0.5828 0.7072
4.750 1.0575 0.02118 0.01214 -0.1313 0.5753 0.7111
5.000 1.0821 0.02139 0.01240 -0.1309 0.5671 0.7157
5.250 1.1074 0.02160 0.01268 -0.1307 0.5592 0.7202
5.500 1.1307 0.02180 0.01296 -0.1300 0.5509 0.7239
5.750 1.1534 0.02204 0.01328 -0.1293 0.5425 0.7282
6.000 1.1787 0.02225 0.01353 -0.1290 0.5341 0.7334
6.250 1.1987 0.02254 0.01395 -0.1278 0.5250 0.7381
6.500 1.2241 0.02271 0.01414 -0.1274 0.5169 0.7433
6.750 1.2420 0.02307 0.01464 -0.1260 0.5066 0.7494
7.000 1.2627 0.02332 0.01498 -0.1249 0.4974 0.7547
7.250 1.2830 0.02359 0.01534 -0.1237 0.4875 0.7606
7.500 1.2999 0.02396 0.01583 -0.1220 0.4768 0.7673
7.750 1.3174 0.02425 0.01621 -0.1204 0.4668 0.7741
8.000 1.3344 0.02456 0.01659 -0.1186 0.4562 0.7823
8.250 1.3460 0.02498 0.01717 -0.1161 0.4449 0.7907
8.500 1.3600 0.02540 0.01770 -0.1139 0.4338 0.8002
8.750 1.3743 0.02582 0.01819 -0.1119 0.4226 0.8111
9.000 1.3853 0.02631 0.01879 -0.1093 0.4108 0.8232
9.250 1.3943 0.02688 0.01950 -0.1065 0.3986 0.8389
9.500 1.4019 0.02745 0.02021 -0.1036 0.3866 0.8610
9.750 1.4058 0.02792 0.02081 -0.0999 0.3753 0.9104
10.000 1.4145 0.02866 0.02159 -0.0976 0.3625 1.0000
10.250 1.4242 0.02969 0.02264 -0.0958 0.3489 1.0000
10.500 1.4318 0.03085 0.02385 -0.0939 0.3349 1.0000
10.750 1.4382 0.03213 0.02517 -0.0919 0.3209 1.0000
11.000 1.4433 0.03354 0.02664 -0.0899 0.3066 1.0000
11.250 1.4472 0.03510 0.02823 -0.0879 0.2924 1.0000
11.500 1.4497 0.03683 0.02999 -0.0860 0.2780 1.0000
11.750 1.4513 0.03872 0.03191 -0.0842 0.2636 1.0000
12.000 1.4517 0.04080 0.03402 -0.0825 0.2494 1.0000
12.250 1.4511 0.04307 0.03632 -0.0810 0.2353 1.0000
12.500 1.4498 0.04551 0.03878 -0.0796 0.2216 1.0000
12.750 1.4478 0.04815 0.04145 -0.0784 0.2085 1.0000
13.000 1.4451 0.05098 0.04430 -0.0774 0.1958 1.0000
13.250 1.4416 0.05399 0.04736 -0.0766 0.1840 1.0000
13.500 1.4376 0.05721 0.05061 -0.0760 0.1722 1.0000
13.750 1.4338 0.06056 0.05402 -0.0756 0.1605 1.0000
14.000 1.4291 0.06413 0.05764 -0.0754 0.1494 1.0000
14.250 1.4231 0.06797 0.06152 -0.0755 0.1387 1.0000
14.500 1.4158 0.07212 0.06566 -0.0757 0.1287 1.0000
14.750 1.4090 0.07637 0.06996 -0.0762 0.1182 1.0000
15.000 1.4021 0.08075 0.07441 -0.0769 0.1081 1.0000
15.250 1.3941 0.08542 0.07911 -0.0778 0.0987 1.0000
15.500 1.3846 0.09044 0.08413 -0.0790 0.0905 1.0000
15.750 1.3782 0.09515 0.08893 -0.0803 0.0818 1.0000
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Polar data table (+)
Polar graphs
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