EPPLER 654 AIRFOIL (e654-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 654 AIRFOIL (e654-il) Reynolds number: 500,000 Max Cl/Cd: 122.52 at α=7.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e654-il-500000.txt Download as CSV file: xf-e654-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.000 0.0053 0.09462 0.09113 -0.1106 0.7522 0.0246
-11.750 -0.1385 0.05379 0.05025 -0.1270 0.7563 0.0161
-11.500 -0.1434 0.04920 0.04562 -0.1295 0.7539 0.0163
-11.250 -0.1413 0.04602 0.04247 -0.1311 0.7518 0.0165
-11.000 -0.1729 0.03798 0.03429 -0.1367 0.7499 0.0165
-10.750 -0.3060 0.03753 0.03284 -0.1479 0.7525 0.0129
-10.500 -0.3184 0.03444 0.02964 -0.1464 0.7494 0.0127
-10.250 -0.3274 0.03223 0.02728 -0.1443 0.7462 0.0126
-10.000 -0.3358 0.03044 0.02531 -0.1414 0.7431 0.0124
-9.750 -0.3357 0.02832 0.02293 -0.1394 0.7403 0.0122
-9.500 -0.3302 0.02630 0.02062 -0.1377 0.7375 0.0120
-9.250 -0.3205 0.02429 0.01833 -0.1362 0.7351 0.0118
-9.000 -0.3057 0.02276 0.01658 -0.1351 0.7329 0.0117
-8.750 -0.2882 0.02143 0.01507 -0.1342 0.7307 0.0117
-8.500 -0.2687 0.02032 0.01381 -0.1335 0.7284 0.0118
-8.250 -0.2479 0.01939 0.01275 -0.1329 0.7262 0.0119
-8.000 -0.2263 0.01857 0.01181 -0.1323 0.7241 0.0121
-7.750 -0.2042 0.01783 0.01097 -0.1318 0.7219 0.0123
-7.500 -0.1812 0.01722 0.01025 -0.1314 0.7196 0.0126
-7.250 -0.1579 0.01666 0.00962 -0.1310 0.7179 0.0130
-7.000 -0.1369 0.01581 0.00877 -0.1304 0.7160 0.0136
-6.750 -0.1128 0.01532 0.00827 -0.1302 0.7141 0.0146
-6.500 -0.0878 0.01489 0.00778 -0.1301 0.7121 0.0158
-6.250 -0.0634 0.01434 0.00722 -0.1299 0.7101 0.0173
-6.000 -0.0377 0.01390 0.00673 -0.1299 0.7080 0.0198
-5.750 -0.0114 0.01351 0.00632 -0.1300 0.7062 0.0239
-5.500 0.0154 0.01317 0.00597 -0.1301 0.7044 0.0311
-5.250 0.0425 0.01289 0.00572 -0.1304 0.7025 0.0422
-5.000 0.0693 0.01258 0.00550 -0.1306 0.7010 0.0572
-4.750 0.0962 0.01225 0.00528 -0.1308 0.6993 0.0778
-4.500 0.1233 0.01191 0.00508 -0.1311 0.6974 0.1070
-4.250 0.1507 0.01156 0.00490 -0.1316 0.6953 0.1491
-4.000 0.1785 0.01118 0.00473 -0.1321 0.6934 0.2054
-3.750 0.2067 0.01079 0.00457 -0.1328 0.6917 0.2737
-3.500 0.2355 0.01040 0.00443 -0.1335 0.6900 0.3523
-3.250 0.2649 0.01002 0.00430 -0.1344 0.6884 0.4371
-3.000 0.2943 0.00974 0.00427 -0.1352 0.6867 0.5232
-2.750 0.3234 0.00971 0.00442 -0.1356 0.6848 0.5917
-2.500 0.3519 0.00972 0.00450 -0.1358 0.6831 0.6295
-2.250 0.3806 0.00979 0.00459 -0.1360 0.6814 0.6519
-2.000 0.4094 0.00988 0.00467 -0.1362 0.6795 0.6690
-1.750 0.4385 0.00998 0.00474 -0.1364 0.6775 0.6835
-1.500 0.4669 0.01007 0.00484 -0.1365 0.6756 0.6946
-1.250 0.4963 0.01016 0.00488 -0.1369 0.6738 0.7042
-1.000 0.5252 0.01026 0.00497 -0.1371 0.6721 0.7121
-0.750 0.5552 0.01039 0.00502 -0.1376 0.6703 0.7206
-0.500 0.5837 0.01060 0.00521 -0.1377 0.6682 0.7272
-0.250 0.6115 0.01067 0.00530 -0.1378 0.6664 0.7344
0.000 0.6392 0.01073 0.00538 -0.1378 0.6642 0.7405
0.250 0.6666 0.01080 0.00548 -0.1378 0.6618 0.7460
0.500 0.6953 0.01087 0.00553 -0.1380 0.6595 0.7522
0.750 0.7244 0.01091 0.00554 -0.1384 0.6572 0.7573
1.000 0.7529 0.01095 0.00557 -0.1385 0.6551 0.7616
1.250 0.7823 0.01104 0.00563 -0.1389 0.6529 0.7663
1.500 0.8110 0.01117 0.00574 -0.1393 0.6505 0.7712
1.750 0.8378 0.01117 0.00580 -0.1392 0.6478 0.7751
2.000 0.8647 0.01119 0.00586 -0.1392 0.6449 0.7786
2.250 0.8928 0.01120 0.00588 -0.1393 0.6421 0.7824
2.500 0.9222 0.01120 0.00585 -0.1398 0.6394 0.7862
2.750 0.9527 0.01124 0.00583 -0.1405 0.6369 0.7898
3.000 0.9803 0.01129 0.00591 -0.1407 0.6340 0.7926
3.250 1.0059 0.01129 0.00598 -0.1404 0.6307 0.7956
3.500 1.0330 0.01129 0.00601 -0.1404 0.6273 0.7988
3.750 1.0615 0.01127 0.00600 -0.1407 0.6240 0.8023
4.000 1.0912 0.01127 0.00597 -0.1413 0.6210 0.8056
4.250 1.1190 0.01131 0.00602 -0.1415 0.6176 0.8084
4.500 1.1436 0.01130 0.00611 -0.1411 0.6134 0.8114
4.750 1.1701 0.01128 0.00612 -0.1410 0.6093 0.8145
5.000 1.1979 0.01126 0.00609 -0.1412 0.6054 0.8177
5.250 1.2250 0.01129 0.00615 -0.1413 0.6011 0.8210
5.500 1.2497 0.01130 0.00622 -0.1409 0.5957 0.8245
5.750 1.2749 0.01126 0.00622 -0.1406 0.5907 0.8275
6.000 1.3004 0.01128 0.00627 -0.1403 0.5855 0.8307
6.250 1.3236 0.01132 0.00639 -0.1396 0.5791 0.8343
6.500 1.3488 0.01135 0.00641 -0.1394 0.5730 0.8381
6.750 1.3711 0.01141 0.00656 -0.1386 0.5656 0.8419
7.000 1.3930 0.01146 0.00663 -0.1376 0.5578 0.8456
7.250 1.4135 0.01156 0.00680 -0.1365 0.5486 0.8497
7.500 1.4335 0.01170 0.00693 -0.1352 0.5388 0.8542
7.750 1.4505 0.01187 0.00712 -0.1335 0.5270 0.8586
8.000 1.4636 0.01206 0.00734 -0.1309 0.5144 0.8636
8.250 1.4739 0.01234 0.00763 -0.1279 0.5007 0.8699
8.500 1.4811 0.01273 0.00801 -0.1244 0.4848 0.8764
8.750 1.4861 0.01325 0.00851 -0.1207 0.4680 0.8840
9.000 1.4879 0.01391 0.00914 -0.1166 0.4504 0.8925
9.250 1.4880 0.01472 0.00992 -0.1125 0.4333 0.9034
9.500 1.4845 0.01566 0.01086 -0.1080 0.4164 0.9187
9.750 1.4806 0.01663 0.01187 -0.1037 0.4001 0.9716
10.000 1.4831 0.01803 0.01320 -0.1013 0.3825 1.0000
10.250 1.4855 0.01953 0.01465 -0.0990 0.3650 1.0000
10.500 1.4871 0.02115 0.01621 -0.0968 0.3484 1.0000
10.750 1.4887 0.02283 0.01784 -0.0946 0.3328 1.0000
11.000 1.4897 0.02459 0.01955 -0.0925 0.3172 1.0000
11.250 1.4908 0.02641 0.02132 -0.0905 0.3024 1.0000
11.500 1.4926 0.02822 0.02310 -0.0887 0.2878 1.0000
11.750 1.4953 0.03003 0.02487 -0.0870 0.2735 1.0000
12.000 1.4985 0.03186 0.02667 -0.0855 0.2599 1.0000
12.250 1.5012 0.03378 0.02856 -0.0840 0.2463 1.0000
12.500 1.5045 0.03570 0.03045 -0.0827 0.2333 1.0000
12.750 1.5072 0.03774 0.03245 -0.0814 0.2210 1.0000
13.000 1.5095 0.03986 0.03453 -0.0802 0.2086 1.0000
13.250 1.5131 0.04191 0.03655 -0.0791 0.1964 1.0000
13.500 1.5178 0.04393 0.03856 -0.0782 0.1847 1.0000
13.750 1.5220 0.04603 0.04064 -0.0773 0.1740 1.0000
14.000 1.5249 0.04830 0.04288 -0.0764 0.1637 1.0000
14.250 1.5285 0.05055 0.04512 -0.0757 0.1534 1.0000
14.500 1.5339 0.05266 0.04723 -0.0751 0.1441 1.0000
14.750 1.5366 0.05510 0.04966 -0.0745 0.1355 1.0000
15.000 1.5403 0.05748 0.05204 -0.0740 0.1266 1.0000
15.250 1.5445 0.05985 0.05443 -0.0736 0.1185 1.0000
15.500 1.5463 0.06253 0.05709 -0.0731 0.1106 1.0000
15.750 1.5500 0.06505 0.05964 -0.0729 0.1033 1.0000
16.000 1.5528 0.06772 0.06232 -0.0727 0.0964 1.0000
16.250 1.5535 0.07068 0.06528 -0.0725 0.0898 1.0000
16.500 1.5569 0.07337 0.06801 -0.0725 0.0837 1.0000
16.750 1.5557 0.07668 0.07132 -0.0725 0.0779 1.0000
17.000 1.5591 0.07946 0.07416 -0.0726 0.0727 1.0000
17.250 1.5570 0.08300 0.07770 -0.0728 0.0678 1.0000
17.500 1.5598 0.08595 0.08072 -0.0731 0.0635 1.0000
17.750 1.5573 0.08963 0.08441 -0.0736 0.0592 1.0000
18.000 1.5587 0.09286 0.08772 -0.0741 0.0555 1.0000
18.250 1.5564 0.09663 0.09153 -0.0747 0.0520 1.0000
18.500 1.5558 0.10021 0.09518 -0.0754 0.0488 1.0000
18.750 1.5539 0.10402 0.09904 -0.0763 0.0457 1.0000
19.000 1.5493 0.10825 0.10332 -0.0773 0.0431 1.0000
19.250 1.5497 0.11177 0.10693 -0.0783 0.0405 1.0000
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