EPPLER 562 AIRFOIL (e562-il) Xfoil prediction polar at RE=200,000 Ncrit=9
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Airfoil: EPPLER 562 AIRFOIL (e562-il) Reynolds number: 200,000 Max Cl/Cd: 73.76 at α=7.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e562-il-200000.txt Download as CSV file: xf-e562-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 562 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
------ -------- --------- --------- -------- -------- --------
-12.250 -0.6504 0.06640 0.06210 -0.0750 1.0000 0.0300
-12.000 -0.6832 0.06025 0.05574 -0.0788 1.0000 0.0298
-11.750 -0.7053 0.05656 0.05191 -0.0806 1.0000 0.0295
-11.500 -0.7295 0.05308 0.04831 -0.0808 1.0000 0.0295
-11.250 -0.7531 0.05095 0.04609 -0.0791 1.0000 0.0294
-11.000 -0.7715 0.04828 0.04330 -0.0780 1.0000 0.0293
-10.750 -0.7845 0.04558 0.04039 -0.0769 1.0000 0.0294
-10.500 -0.7911 0.04251 0.03712 -0.0757 1.0000 0.0295
-10.250 -0.7900 0.03963 0.03416 -0.0746 1.0000 0.0301
-10.000 -0.7833 0.03791 0.03241 -0.0735 1.0000 0.0309
-9.750 -0.7744 0.03640 0.03082 -0.0725 1.0000 0.0317
-9.500 -0.7644 0.03473 0.02900 -0.0717 1.0000 0.0325
-9.250 -0.7528 0.03294 0.02700 -0.0710 1.0000 0.0333
-9.000 -0.7322 0.03112 0.02492 -0.0716 0.9988 0.0342
-8.750 -0.6937 0.02943 0.02288 -0.0751 0.9946 0.0354
-8.500 -0.6612 0.02728 0.02078 -0.0774 0.9904 0.0372
-8.250 -0.6231 0.02615 0.01959 -0.0806 0.9858 0.0400
-8.000 -0.5857 0.02498 0.01826 -0.0833 0.9811 0.0428
-7.750 -0.5507 0.02350 0.01684 -0.0859 0.9758 0.0462
-7.500 -0.5086 0.02256 0.01577 -0.0894 0.9723 0.0509
-7.250 -0.4763 0.02118 0.01446 -0.0915 0.9652 0.0571
-7.000 -0.4346 0.01991 0.01318 -0.0952 0.9614 0.0679
-6.750 -0.3995 0.01851 0.01189 -0.0978 0.9547 0.0945
-6.500 -0.3590 0.01717 0.01084 -0.1015 0.9503 0.1505
-6.250 -0.3201 0.01659 0.01036 -0.1042 0.9449 0.1915
-6.000 -0.2828 0.01621 0.00998 -0.1062 0.9382 0.2208
-5.750 -0.2390 0.01590 0.00962 -0.1094 0.9346 0.2471
-5.500 -0.2064 0.01570 0.00940 -0.1103 0.9258 0.2679
-5.250 -0.1635 0.01552 0.00912 -0.1131 0.9216 0.2914
-5.000 -0.1274 0.01530 0.00886 -0.1145 0.9146 0.3076
-4.750 -0.0886 0.01499 0.00854 -0.1164 0.9089 0.3219
-4.500 -0.0449 0.01464 0.00817 -0.1192 0.9057 0.3364
-4.250 -0.0106 0.01436 0.00788 -0.1202 0.8970 0.3477
-4.000 0.0333 0.01400 0.00746 -0.1230 0.8920 0.3602
-3.750 0.0757 0.01374 0.00710 -0.1257 0.8850 0.3728
-3.500 0.1170 0.01346 0.00685 -0.1280 0.8766 0.3838
-3.250 0.1568 0.01324 0.00660 -0.1301 0.8665 0.3953
-3.000 0.2015 0.01301 0.00627 -0.1332 0.8575 0.4078
-2.750 0.2362 0.01289 0.00611 -0.1343 0.8437 0.4174
-2.500 0.2704 0.01276 0.00592 -0.1354 0.8295 0.4269
-2.250 0.3036 0.01272 0.00576 -0.1362 0.8150 0.4375
-2.000 0.3349 0.01265 0.00566 -0.1366 0.8003 0.4458
-1.750 0.3656 0.01264 0.00552 -0.1370 0.7857 0.4562
-1.500 0.3948 0.01263 0.00549 -0.1370 0.7712 0.4649
-1.250 0.4239 0.01264 0.00539 -0.1371 0.7570 0.4746
-1.000 0.4525 0.01267 0.00536 -0.1370 0.7432 0.4840
-0.750 0.4795 0.01270 0.00533 -0.1366 0.7289 0.4934
-0.500 0.5062 0.01275 0.00532 -0.1362 0.7148 0.5036
-0.250 0.5328 0.01278 0.00533 -0.1358 0.7013 0.5126
0.000 0.5601 0.01286 0.00532 -0.1356 0.6884 0.5234
0.250 0.5873 0.01292 0.00536 -0.1352 0.6763 0.5330
0.500 0.6139 0.01298 0.00538 -0.1348 0.6638 0.5433
0.750 0.6400 0.01307 0.00544 -0.1344 0.6512 0.5545
1.000 0.6664 0.01314 0.00551 -0.1339 0.6396 0.5647
1.250 0.6938 0.01324 0.00556 -0.1337 0.6289 0.5762
1.500 0.7195 0.01333 0.00565 -0.1332 0.6170 0.5886
1.750 0.7453 0.01342 0.00577 -0.1327 0.6061 0.6002
2.000 0.7724 0.01354 0.00585 -0.1324 0.5962 0.6130
2.250 0.7975 0.01362 0.00599 -0.1318 0.5851 0.6266
2.500 0.8236 0.01374 0.00613 -0.1314 0.5751 0.6415
2.750 0.8500 0.01387 0.00625 -0.1310 0.5656 0.6576
3.000 0.8747 0.01396 0.00645 -0.1303 0.5554 0.6748
3.250 0.9009 0.01410 0.00660 -0.1298 0.5466 0.6943
3.500 0.9248 0.01419 0.00679 -0.1289 0.5368 0.7168
3.750 0.9493 0.01431 0.00699 -0.1281 0.5282 0.7427
4.000 0.9722 0.01439 0.00718 -0.1269 0.5193 0.7748
4.250 0.9931 0.01447 0.00738 -0.1253 0.5110 0.8170
4.500 1.0083 0.01440 0.00747 -0.1222 0.5030 0.8854
4.750 1.0353 0.01447 0.00758 -0.1220 0.4946 1.0000
5.000 1.0633 0.01474 0.00778 -0.1222 0.4860 1.0000
5.250 1.0898 0.01503 0.00805 -0.1221 0.4775 1.0000
5.500 1.1166 0.01532 0.00828 -0.1220 0.4693 1.0000
5.750 1.1419 0.01562 0.00860 -0.1216 0.4608 1.0000
6.000 1.1681 0.01591 0.00884 -0.1214 0.4529 1.0000
6.250 1.1923 0.01622 0.00919 -0.1207 0.4444 1.0000
6.500 1.2181 0.01653 0.00945 -0.1204 0.4365 1.0000
6.750 1.2410 0.01683 0.00982 -0.1195 0.4277 1.0000
7.000 1.2665 0.01717 0.01010 -0.1192 0.4197 1.0000
7.250 1.2879 0.01746 0.01048 -0.1180 0.4106 1.0000
7.500 1.3129 0.01782 0.01077 -0.1175 0.4026 1.0000
7.750 1.3327 0.01810 0.01117 -0.1161 0.3933 1.0000
8.000 1.3555 0.01846 0.01151 -0.1153 0.3849 1.0000
8.250 1.3750 0.01876 0.01188 -0.1138 0.3755 1.0000
8.500 1.3953 0.01912 0.01228 -0.1125 0.3664 1.0000
8.750 1.4148 0.01946 0.01263 -0.1110 0.3572 1.0000
9.000 1.4318 0.01982 0.01308 -0.1092 0.3474 1.0000
9.250 1.4501 0.02022 0.01346 -0.1076 0.3382 1.0000
9.500 1.4640 0.02057 0.01391 -0.1052 0.3281 1.0000
9.750 1.4774 0.02099 0.01438 -0.1027 0.3184 1.0000
10.000 1.4906 0.02147 0.01483 -0.1003 0.3088 1.0000
10.250 1.5008 0.02192 0.01542 -0.0974 0.2980 1.0000
10.500 1.5112 0.02248 0.01602 -0.0947 0.2873 1.0000
10.750 1.5200 0.02313 0.01666 -0.0919 0.2764 1.0000
11.000 1.5276 0.02382 0.01741 -0.0890 0.2645 1.0000
11.250 1.5347 0.02461 0.01828 -0.0862 0.2519 1.0000
11.500 1.5402 0.02555 0.01925 -0.0833 0.2391 1.0000
11.750 1.5445 0.02663 0.02037 -0.0805 0.2262 1.0000
12.000 1.5471 0.02791 0.02165 -0.0778 0.2131 1.0000
12.250 1.5481 0.02939 0.02314 -0.0752 0.1999 1.0000
12.500 1.5476 0.03110 0.02486 -0.0727 0.1867 1.0000
12.750 1.5453 0.03308 0.02683 -0.0703 0.1737 1.0000
13.000 1.5427 0.03526 0.02903 -0.0683 0.1608 1.0000
13.250 1.5393 0.03768 0.03148 -0.0666 0.1484 1.0000
13.500 1.5346 0.04036 0.03419 -0.0651 0.1369 1.0000
13.750 1.5284 0.04336 0.03721 -0.0640 0.1266 1.0000
14.000 1.5194 0.04682 0.04066 -0.0630 0.1178 1.0000
14.250 1.5126 0.05026 0.04415 -0.0625 0.1087 1.0000
14.500 1.5052 0.05395 0.04789 -0.0622 0.1006 1.0000
14.750 1.4939 0.05823 0.05217 -0.0623 0.0942 1.0000
15.000 1.4876 0.06213 0.05617 -0.0625 0.0870 1.0000
15.250 1.4749 0.06694 0.06096 -0.0631 0.0817 1.0000
15.500 1.4693 0.07105 0.06520 -0.0637 0.0755 1.0000
15.750 1.4574 0.07609 0.07023 -0.0648 0.0709 1.0000
16.000 1.4508 0.08056 0.07482 -0.0658 0.0658 1.0000
16.250 1.4418 0.08548 0.07978 -0.0671 0.0617 1.0000
16.500 1.4331 0.09035 0.08469 -0.0684 0.0578 1.0000
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Polar data table (+)
Polar graphs
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