EPPLER 587 AIRFOIL (e587-il) Xfoil prediction polar at RE=200,000 Ncrit=9
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Airfoil: EPPLER 587 AIRFOIL (e587-il) Reynolds number: 200,000 Max Cl/Cd: 75.22 at α=7.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e587-il-200000.txt Download as CSV file: xf-e587-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 587 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
------ -------- --------- --------- -------- -------- --------
-11.750 -0.0716 0.10841 0.10504 -0.1005 0.9537 0.0475
-11.500 -0.0868 0.10221 0.09887 -0.1067 0.9505 0.0492
-11.250 -0.0812 0.09665 0.09331 -0.1095 0.9486 0.0500
-11.000 -0.0582 0.09370 0.09034 -0.1104 0.9471 0.0512
-10.750 -0.0428 0.08993 0.08656 -0.1129 0.9458 0.0536
-10.500 -0.0401 0.08414 0.08077 -0.1179 0.9447 0.0567
-10.250 -0.1597 0.09102 0.08760 -0.1110 0.9507 0.0506
-10.000 -0.1403 0.08816 0.08472 -0.1130 0.9482 0.0520
-9.750 -0.0262 0.06970 0.06635 -0.1268 0.9335 0.0644
-9.500 -0.0346 0.06127 0.05792 -0.1348 0.9313 0.0670
-9.250 -0.0444 0.05472 0.05136 -0.1389 0.9252 0.0658
-9.000 -0.0736 0.04712 0.04363 -0.1460 0.9186 0.0667
-8.750 -0.0854 0.04220 0.03860 -0.1490 0.9124 0.0654
-8.500 -0.1202 0.03956 0.03571 -0.1487 0.9011 0.0675
-8.250 -0.2002 0.02573 0.02058 -0.1415 0.8872 0.0291
-8.000 -0.1862 0.02221 0.01671 -0.1421 0.8842 0.0289
-7.750 -0.1899 0.02085 0.01513 -0.1381 0.8750 0.0289
-7.500 -0.1866 0.03194 0.02557 -0.1429 0.8808 0.0287
-7.250 -0.1741 0.03001 0.02337 -0.1410 0.8744 0.0285
-7.000 -0.1463 0.02754 0.02057 -0.1416 0.8714 0.0279
-6.750 -0.1141 0.02535 0.01806 -0.1425 0.8692 0.0276
-6.500 -0.0995 0.02432 0.01686 -0.1401 0.8634 0.0280
-6.250 -0.0779 0.02327 0.01565 -0.1389 0.8586 0.0286
-6.000 -0.0485 0.02197 0.01426 -0.1392 0.8557 0.0300
-5.750 -0.0179 0.02088 0.01320 -0.1400 0.8533 0.0328
-5.500 -0.0054 0.02045 0.01278 -0.1376 0.8475 0.0368
-5.250 0.0129 0.01990 0.01224 -0.1364 0.8424 0.0426
-5.000 0.0401 0.01887 0.01128 -0.1370 0.8392 0.0561
-4.750 0.0707 0.01760 0.01023 -0.1386 0.8368 0.1008
-4.500 0.0826 0.01679 0.00995 -0.1372 0.8306 0.1946
-4.250 0.1047 0.01524 0.00993 -0.1382 0.8263 0.5255
-4.000 0.1354 0.01568 0.01039 -0.1380 0.8233 0.6055
-3.750 0.1680 0.01616 0.01075 -0.1380 0.8210 0.6352
-3.500 0.1859 0.01684 0.01138 -0.1356 0.8162 0.6519
-3.250 0.2045 0.01741 0.01191 -0.1333 0.8110 0.6663
-3.000 0.2325 0.01779 0.01218 -0.1326 0.8078 0.6806
-2.750 0.2608 0.01818 0.01251 -0.1316 0.8054 0.6910
-2.500 0.2837 0.01856 0.01285 -0.1301 0.8019 0.7005
-2.250 0.2979 0.01904 0.01327 -0.1277 0.7956 0.7123
-2.000 0.3156 0.01950 0.01376 -0.1242 0.7920 0.7205
-1.750 0.3453 0.01965 0.01382 -0.1239 0.7896 0.7319
-1.500 0.3761 0.01974 0.01383 -0.1238 0.7875 0.7383
-1.250 0.3849 0.02008 0.01415 -0.1213 0.7798 0.7461
-1.000 0.4090 0.02008 0.01411 -0.1203 0.7762 0.7495
-0.750 0.4419 0.01994 0.01390 -0.1212 0.7738 0.7536
-0.500 0.4811 0.01974 0.01358 -0.1238 0.7718 0.7582
-0.250 0.4918 0.02006 0.01391 -0.1216 0.7644 0.7627
0.000 0.5177 0.01999 0.01381 -0.1213 0.7605 0.7653
0.250 0.5516 0.01981 0.01357 -0.1225 0.7579 0.7681
0.500 0.5902 0.01960 0.01328 -0.1248 0.7557 0.7711
0.750 0.6023 0.01996 0.01367 -0.1228 0.7483 0.7755
1.000 0.6352 0.01983 0.01349 -0.1244 0.7444 0.7785
1.250 0.6693 0.01960 0.01322 -0.1256 0.7416 0.7806
1.500 0.7067 0.01939 0.01295 -0.1274 0.7393 0.7830
1.750 0.7133 0.01981 0.01346 -0.1241 0.7312 0.7865
2.000 0.7474 0.01964 0.01326 -0.1256 0.7274 0.7894
2.250 0.7890 0.01937 0.01293 -0.1286 0.7247 0.7923
2.500 0.8103 0.01951 0.01309 -0.1278 0.7189 0.7953
2.750 0.8318 0.01952 0.01314 -0.1268 0.7131 0.7981
3.000 0.8681 0.01925 0.01285 -0.1285 0.7097 0.8006
3.250 0.9070 0.01902 0.01259 -0.1307 0.7066 0.8032
3.500 0.9186 0.01933 0.01299 -0.1283 0.6983 0.8068
3.750 0.9572 0.01908 0.01272 -0.1307 0.6942 0.8101
4.000 0.9956 0.01876 0.01238 -0.1326 0.6910 0.8125
4.250 1.0030 0.01904 0.01279 -0.1291 0.6822 0.8157
4.500 1.0393 0.01873 0.01247 -0.1308 0.6776 0.8186
4.750 1.0649 0.01871 0.01251 -0.1307 0.6711 0.8219
5.000 1.0932 0.01863 0.01246 -0.1311 0.6642 0.8256
5.250 1.1308 0.01826 0.01209 -0.1329 0.6597 0.8283
5.500 1.1409 0.01842 0.01238 -0.1298 0.6507 0.8321
5.750 1.1769 0.01811 0.01207 -0.1313 0.6449 0.8355
6.000 1.1940 0.01821 0.01227 -0.1297 0.6359 0.8395
6.250 1.2291 0.01792 0.01197 -0.1311 0.6290 0.8427
6.500 1.2403 0.01798 0.01215 -0.1281 0.6192 0.8467
6.750 1.2712 0.01775 0.01194 -0.1287 0.6112 0.8509
7.000 1.2866 0.01781 0.01208 -0.1266 0.6004 0.8559
7.250 1.3029 0.01781 0.01215 -0.1246 0.5899 0.8601
7.500 1.3258 0.01771 0.01207 -0.1236 0.5796 0.8645
7.750 1.3374 0.01778 0.01221 -0.1208 0.5674 0.8701
8.000 1.3469 0.01794 0.01245 -0.1176 0.5546 0.8759
8.250 1.3582 0.01812 0.01267 -0.1147 0.5412 0.8826
8.500 1.3707 0.01835 0.01295 -0.1123 0.5268 0.8896
8.750 1.3804 0.01863 0.01326 -0.1093 0.5118 0.8972
9.000 1.3895 0.01901 0.01365 -0.1064 0.4957 0.9058
9.250 1.3962 0.01947 0.01413 -0.1031 0.4788 0.9166
9.500 1.3999 0.01997 0.01465 -0.0994 0.4618 0.9316
9.750 1.4022 0.02045 0.01517 -0.0957 0.4442 0.9791
10.250 1.4221 0.02261 0.01723 -0.0928 0.4026 1.0000
10.500 1.4291 0.02390 0.01846 -0.0910 0.3820 1.0000
10.750 1.4342 0.02532 0.01980 -0.0891 0.3619 1.0000
11.000 1.4380 0.02686 0.02129 -0.0871 0.3421 1.0000
11.250 1.4409 0.02849 0.02289 -0.0851 0.3225 1.0000
11.500 1.4426 0.03026 0.02460 -0.0831 0.3035 1.0000
11.750 1.4435 0.03214 0.02643 -0.0811 0.2852 1.0000
12.000 1.4438 0.03415 0.02837 -0.0792 0.2674 1.0000
12.250 1.4443 0.03622 0.03040 -0.0775 0.2500 1.0000
12.500 1.4451 0.03836 0.03253 -0.0759 0.2330 1.0000
12.750 1.4455 0.04061 0.03477 -0.0744 0.2167 1.0000
13.000 1.4456 0.04298 0.03712 -0.0731 0.2009 1.0000
13.250 1.4456 0.04544 0.03956 -0.0719 0.1859 1.0000
13.500 1.4452 0.04803 0.04213 -0.0708 0.1712 1.0000
13.750 1.4444 0.05075 0.04484 -0.0698 0.1571 1.0000
14.000 1.4431 0.05361 0.04768 -0.0690 0.1436 1.0000
14.250 1.4409 0.05665 0.05071 -0.0683 0.1307 1.0000
14.500 1.4380 0.05987 0.05392 -0.0677 0.1186 1.0000
14.750 1.4343 0.06329 0.05732 -0.0672 0.1071 1.0000
15.000 1.4322 0.06663 0.06068 -0.0670 0.0959 1.0000
15.250 1.4294 0.07015 0.06423 -0.0668 0.0857 1.0000
15.500 1.4255 0.07388 0.06799 -0.0668 0.0768 1.0000
15.750 1.4194 0.07799 0.07208 -0.0670 0.0695 1.0000
16.000 1.4151 0.08196 0.07609 -0.0673 0.0626 1.0000
16.250 1.4114 0.08595 0.08015 -0.0677 0.0565 1.0000
16.500 1.4037 0.09051 0.08469 -0.0684 0.0519 1.0000
16.750 1.4023 0.09436 0.08867 -0.0691 0.0469 1.0000
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