EPPLER 654 AIRFOIL (e654-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 654 AIRFOIL (e654-il) Reynolds number: 1,000,000 Max Cl/Cd: 145.44 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e654-il-1000000-n5.txt Download as CSV file: xf-e654-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 654 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.250 -0.4276 0.07313 0.06939 -0.1235 0.7317 0.0040
-15.000 -0.4617 0.06370 0.05982 -0.1289 0.7290 0.0040
-14.750 -0.4897 0.05532 0.05128 -0.1340 0.7258 0.0040
-14.500 -0.5138 0.04806 0.04385 -0.1388 0.7226 0.0040
-14.250 -0.5238 0.04348 0.03914 -0.1416 0.7192 0.0040
-14.000 -0.5337 0.03942 0.03496 -0.1438 0.7165 0.0040
-13.750 -0.5464 0.03558 0.03098 -0.1452 0.7135 0.0040
-13.500 -0.5504 0.03299 0.02827 -0.1457 0.7103 0.0040
-13.250 -0.5527 0.03077 0.02593 -0.1456 0.7072 0.0040
-13.000 -0.5561 0.02863 0.02366 -0.1451 0.7042 0.0040
-12.750 -0.5523 0.02716 0.02210 -0.1445 0.7014 0.0040
-12.500 -0.5512 0.02552 0.02035 -0.1435 0.6991 0.0040
-12.250 -0.5456 0.02427 0.01902 -0.1424 0.6964 0.0040
-12.000 -0.5408 0.02305 0.01770 -0.1410 0.6935 0.0040
-11.750 -0.5340 0.02202 0.01658 -0.1396 0.6909 0.0040
-11.500 -0.5271 0.02109 0.01556 -0.1378 0.6885 0.0040
-11.250 -0.5250 0.02018 0.01455 -0.1351 0.6860 0.0040
-11.000 -0.5148 0.01947 0.01377 -0.1335 0.6842 0.0040
-10.750 -0.4997 0.01878 0.01300 -0.1324 0.6825 0.0040
-10.500 -0.4829 0.01810 0.01224 -0.1314 0.6807 0.0041
-10.250 -0.4654 0.01740 0.01147 -0.1305 0.6788 0.0041
-10.000 -0.4472 0.01668 0.01066 -0.1297 0.6767 0.0041
-9.750 -0.4271 0.01606 0.00996 -0.1291 0.6746 0.0042
-9.500 -0.4059 0.01549 0.00931 -0.1285 0.6725 0.0042
-9.250 -0.3841 0.01492 0.00867 -0.1281 0.6706 0.0043
-9.000 -0.3609 0.01447 0.00815 -0.1277 0.6688 0.0044
-8.750 -0.3367 0.01404 0.00767 -0.1275 0.6674 0.0045
-8.500 -0.3118 0.01363 0.00723 -0.1274 0.6661 0.0046
-8.250 -0.2864 0.01327 0.00683 -0.1274 0.6646 0.0047
-8.000 -0.2606 0.01293 0.00646 -0.1273 0.6630 0.0048
-7.750 -0.2345 0.01261 0.00610 -0.1273 0.6611 0.0050
-7.500 -0.2082 0.01231 0.00577 -0.1274 0.6594 0.0051
-7.250 -0.1816 0.01203 0.00545 -0.1274 0.6578 0.0054
-7.000 -0.1547 0.01177 0.00516 -0.1275 0.6562 0.0056
-6.750 -0.1276 0.01154 0.00489 -0.1276 0.6547 0.0059
-6.500 -0.1007 0.01127 0.00458 -0.1277 0.6530 0.0066
-6.250 -0.0733 0.01105 0.00435 -0.1279 0.6513 0.0073
-6.000 -0.0453 0.01084 0.00412 -0.1282 0.6501 0.0080
-5.750 -0.0173 0.01061 0.00390 -0.1284 0.6487 0.0095
-5.500 0.0108 0.01041 0.00370 -0.1287 0.6474 0.0114
-5.250 0.0391 0.01022 0.00351 -0.1290 0.6460 0.0138
-5.000 0.0675 0.01003 0.00334 -0.1294 0.6445 0.0176
-4.750 0.0959 0.00986 0.00318 -0.1297 0.6429 0.0228
-4.500 0.1244 0.00968 0.00303 -0.1300 0.6413 0.0289
-4.250 0.1529 0.00953 0.00289 -0.1304 0.6396 0.0360
-4.000 0.1815 0.00937 0.00276 -0.1308 0.6379 0.0452
-3.750 0.2100 0.00919 0.00263 -0.1312 0.6364 0.0624
-3.500 0.2386 0.00894 0.00251 -0.1317 0.6349 0.0944
-3.250 0.2677 0.00867 0.00239 -0.1323 0.6338 0.1333
-3.000 0.2970 0.00845 0.00230 -0.1329 0.6324 0.1675
-2.750 0.3264 0.00827 0.00222 -0.1335 0.6308 0.1998
-2.500 0.3559 0.00807 0.00214 -0.1341 0.6292 0.2393
-2.250 0.3855 0.00783 0.00207 -0.1349 0.6277 0.2944
-2.000 0.4153 0.00761 0.00200 -0.1356 0.6261 0.3487
-1.500 0.4749 0.00721 0.00190 -0.1371 0.6226 0.4615
-1.250 0.5048 0.00702 0.00187 -0.1378 0.6208 0.5255
-1.000 0.5345 0.00693 0.00189 -0.1384 0.6189 0.5739
-0.750 0.5643 0.00688 0.00192 -0.1390 0.6174 0.6014
-0.500 0.5939 0.00687 0.00195 -0.1395 0.6155 0.6206
-0.250 0.6235 0.00687 0.00197 -0.1399 0.6133 0.6361
0.000 0.6528 0.00689 0.00200 -0.1403 0.6109 0.6486
0.250 0.6819 0.00691 0.00203 -0.1407 0.6083 0.6584
0.500 0.7108 0.00696 0.00205 -0.1411 0.6057 0.6665
0.750 0.7394 0.00701 0.00210 -0.1413 0.6029 0.6738
1.000 0.7688 0.00703 0.00214 -0.1418 0.6006 0.6808
1.250 0.7980 0.00706 0.00218 -0.1422 0.5977 0.6862
1.500 0.8267 0.00710 0.00223 -0.1425 0.5944 0.6916
1.750 0.8552 0.00715 0.00227 -0.1428 0.5910 0.6968
2.000 0.8833 0.00723 0.00231 -0.1430 0.5875 0.7013
2.250 0.9122 0.00726 0.00237 -0.1434 0.5843 0.7055
2.500 0.9407 0.00730 0.00244 -0.1437 0.5804 0.7095
2.750 0.9688 0.00736 0.00250 -0.1439 0.5760 0.7133
3.000 0.9962 0.00745 0.00256 -0.1440 0.5717 0.7166
3.250 1.0247 0.00750 0.00263 -0.1443 0.5672 0.7194
3.500 1.0523 0.00757 0.00270 -0.1444 0.5615 0.7222
3.750 1.0790 0.00766 0.00279 -0.1444 0.5559 0.7251
4.000 1.1065 0.00774 0.00288 -0.1446 0.5495 0.7279
4.250 1.1325 0.00786 0.00299 -0.1444 0.5418 0.7308
4.500 1.1590 0.00797 0.00310 -0.1444 0.5334 0.7336
4.750 1.1839 0.00814 0.00322 -0.1441 0.5232 0.7362
5.000 1.2081 0.00832 0.00337 -0.1436 0.5109 0.7384
5.250 1.2318 0.00852 0.00355 -0.1431 0.4978 0.7411
5.500 1.2540 0.00875 0.00375 -0.1423 0.4832 0.7439
5.750 1.2742 0.00906 0.00400 -0.1411 0.4658 0.7468
6.000 1.2928 0.00941 0.00428 -0.1396 0.4480 0.7496
6.250 1.3097 0.00980 0.00459 -0.1379 0.4294 0.7524
6.500 1.3232 0.01020 0.00492 -0.1354 0.4106 0.7552
6.750 1.3339 0.01062 0.00529 -0.1325 0.3928 0.7584
7.000 1.3444 0.01110 0.00571 -0.1296 0.3754 0.7618
7.250 1.3543 0.01162 0.00618 -0.1267 0.3585 0.7652
7.500 1.3638 0.01219 0.00669 -0.1238 0.3427 0.7686
7.750 1.3732 0.01279 0.00725 -0.1211 0.3285 0.7719
8.000 1.3802 0.01351 0.00792 -0.1181 0.3129 0.7752
8.250 1.3869 0.01430 0.00868 -0.1152 0.2984 0.7791
8.500 1.3933 0.01518 0.00953 -0.1124 0.2847 0.7835
8.750 1.3994 0.01616 0.01048 -0.1098 0.2715 0.7878
9.000 1.4062 0.01718 0.01148 -0.1074 0.2582 0.7916
9.250 1.4123 0.01831 0.01258 -0.1051 0.2450 0.7959
9.500 1.4197 0.01943 0.01370 -0.1031 0.2341 0.8004
9.750 1.4253 0.02072 0.01495 -0.1010 0.2217 0.8050
10.000 1.4306 0.02207 0.01628 -0.0990 0.2097 0.8097
10.250 1.4394 0.02324 0.01746 -0.0974 0.1999 0.8152
10.500 1.4456 0.02461 0.01882 -0.0956 0.1889 0.8211
10.750 1.4503 0.02611 0.02030 -0.0938 0.1774 0.8268
11.000 1.4566 0.02755 0.02173 -0.0922 0.1674 0.8333
11.250 1.4641 0.02893 0.02312 -0.0907 0.1578 0.8400
11.500 1.4702 0.03043 0.02463 -0.0892 0.1494 0.8478
12.000 1.4832 0.03348 0.02770 -0.0865 0.1312 0.8677
12.250 1.4894 0.03502 0.02926 -0.0851 0.1231 0.8826
12.500 1.4938 0.03656 0.03087 -0.0834 0.1150 0.9136
13.000 1.5069 0.03992 0.03426 -0.0814 0.0997 1.0000
13.250 1.5162 0.04148 0.03583 -0.0807 0.0938 1.0000
13.500 1.5221 0.04338 0.03772 -0.0798 0.0868 1.0000
13.750 1.5301 0.04514 0.03948 -0.0791 0.0813 1.0000
14.000 1.5373 0.04699 0.04132 -0.0785 0.0756 1.0000
14.250 1.5433 0.04900 0.04333 -0.0778 0.0700 1.0000
14.500 1.5509 0.05087 0.04521 -0.0773 0.0654 1.0000
14.750 1.5558 0.05306 0.04740 -0.0767 0.0599 1.0000
15.000 1.5622 0.05514 0.04949 -0.0762 0.0551 1.0000
15.250 1.5674 0.05738 0.05173 -0.0758 0.0508 1.0000
15.500 1.5733 0.05958 0.05395 -0.0754 0.0469 1.0000
15.750 1.5776 0.06198 0.05635 -0.0751 0.0425 1.0000
16.000 1.5823 0.06439 0.05879 -0.0749 0.0393 1.0000
16.250 1.5873 0.06680 0.06123 -0.0747 0.0363 1.0000
16.500 1.5903 0.06951 0.06396 -0.0746 0.0329 1.0000
16.750 1.5942 0.07213 0.06660 -0.0746 0.0298 1.0000
17.000 1.5966 0.07497 0.06947 -0.0746 0.0275 1.0000
17.250 1.5998 0.07777 0.07230 -0.0747 0.0247 1.0000
17.500 1.6010 0.08086 0.07543 -0.0749 0.0227 1.0000
17.750 1.6051 0.08361 0.07823 -0.0752 0.0211 1.0000
18.000 1.6047 0.08701 0.08168 -0.0755 0.0190 1.0000
18.250 1.6079 0.08993 0.08465 -0.0760 0.0177 1.0000
18.500 1.6083 0.09330 0.08808 -0.0765 0.0165 1.0000
18.750 1.6096 0.09658 0.09141 -0.0771 0.0153 1.0000
19.000 1.6099 0.10003 0.09492 -0.0779 0.0142 1.0000
19.250 1.6086 0.10373 0.09868 -0.0787 0.0131 1.0000
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