EPPLER 562 AIRFOIL (e562-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 562 AIRFOIL (e562-il) Reynolds number: 200,000 Max Cl/Cd: 74.81 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e562-il-200000-n5.txt Download as CSV file: xf-e562-il-200000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.750 -0.5779 0.10895 0.10473 -0.0488 1.0000 0.0158
-14.500 -0.6078 0.09885 0.09448 -0.0539 1.0000 0.0156
-14.250 -0.6328 0.09027 0.08574 -0.0585 1.0000 0.0156
-14.000 -0.6527 0.08313 0.07844 -0.0623 1.0000 0.0158
-13.750 -0.6673 0.07738 0.07256 -0.0652 1.0000 0.0158
-13.500 -0.6803 0.07226 0.06732 -0.0676 1.0000 0.0158
-13.250 -0.6962 0.06703 0.06191 -0.0702 1.0000 0.0162
-13.000 -0.7057 0.06308 0.05786 -0.0716 1.0000 0.0162
-12.750 -0.7152 0.05931 0.05397 -0.0727 1.0000 0.0163
-12.500 -0.7233 0.05599 0.05063 -0.0736 1.0000 0.0167
-12.250 -0.7299 0.05304 0.04762 -0.0738 1.0000 0.0168
-12.000 -0.7368 0.05023 0.04477 -0.0740 1.0000 0.0170
-11.750 -0.7450 0.04751 0.04201 -0.0738 1.0000 0.0172
-11.500 -0.7541 0.04497 0.03943 -0.0733 1.0000 0.0174
-11.250 -0.7660 0.04256 0.03698 -0.0721 1.0000 0.0175
-11.000 -0.7831 0.04036 0.03474 -0.0701 1.0000 0.0176
-10.750 -0.7954 0.03800 0.03231 -0.0694 0.9995 0.0178
-10.500 -0.7694 0.03500 0.02913 -0.0758 0.9946 0.0185
-10.250 -0.7437 0.03260 0.02654 -0.0802 0.9896 0.0193
-10.000 -0.7152 0.03064 0.02437 -0.0839 0.9852 0.0201
-9.750 -0.6897 0.02868 0.02236 -0.0869 0.9800 0.0209
-9.500 -0.6610 0.02715 0.02076 -0.0897 0.9750 0.0221
-9.250 -0.6311 0.02583 0.01929 -0.0921 0.9706 0.0237
-9.000 -0.6045 0.02447 0.01783 -0.0938 0.9643 0.0251
-8.750 -0.5715 0.02320 0.01649 -0.0966 0.9607 0.0269
-8.500 -0.5462 0.02215 0.01534 -0.0974 0.9532 0.0287
-8.250 -0.5130 0.02102 0.01412 -0.0998 0.9490 0.0313
-8.000 -0.4853 0.02013 0.01316 -0.1007 0.9420 0.0343
-7.750 -0.4526 0.01916 0.01213 -0.1026 0.9370 0.0383
-7.500 -0.4198 0.01829 0.01119 -0.1043 0.9320 0.0444
-7.250 -0.3903 0.01743 0.01032 -0.1053 0.9248 0.0535
-6.750 -0.3263 0.01577 0.00876 -0.1082 0.9127 0.0926
-6.500 -0.2917 0.01506 0.00809 -0.1100 0.9071 0.1169
-6.250 -0.2582 0.01445 0.00754 -0.1115 0.9004 0.1435
-6.000 -0.2238 0.01394 0.00708 -0.1131 0.8931 0.1710
-5.750 -0.1858 0.01349 0.00666 -0.1153 0.8869 0.2004
-5.500 -0.1502 0.01315 0.00635 -0.1170 0.8782 0.2284
-5.250 -0.1093 0.01286 0.00603 -0.1196 0.8709 0.2490
-5.000 -0.0694 0.01263 0.00574 -0.1221 0.8612 0.2647
-4.750 -0.0292 0.01244 0.00548 -0.1245 0.8510 0.2801
-4.500 0.0125 0.01226 0.00519 -0.1273 0.8401 0.2932
-4.250 0.0499 0.01212 0.00498 -0.1291 0.8269 0.3043
-4.000 0.0851 0.01201 0.00479 -0.1305 0.8128 0.3142
-3.750 0.1188 0.01195 0.00460 -0.1315 0.7982 0.3252
-3.500 0.1507 0.01190 0.00449 -0.1323 0.7835 0.3361
-3.250 0.1814 0.01188 0.00438 -0.1327 0.7688 0.3466
-3.000 0.2112 0.01188 0.00426 -0.1330 0.7544 0.3559
-2.750 0.2402 0.01187 0.00418 -0.1330 0.7401 0.3635
-2.500 0.2688 0.01189 0.00408 -0.1331 0.7261 0.3727
-2.250 0.2966 0.01190 0.00404 -0.1329 0.7123 0.3803
-2.000 0.3242 0.01193 0.00397 -0.1327 0.6985 0.3886
-1.750 0.3514 0.01196 0.00395 -0.1325 0.6854 0.3964
-1.500 0.3788 0.01201 0.00391 -0.1323 0.6727 0.4053
-1.250 0.4059 0.01205 0.00391 -0.1320 0.6602 0.4128
-1.000 0.4329 0.01212 0.00389 -0.1317 0.6479 0.4217
-0.750 0.4596 0.01217 0.00391 -0.1314 0.6358 0.4294
-0.500 0.4865 0.01224 0.00391 -0.1311 0.6242 0.4383
-0.250 0.5131 0.01231 0.00395 -0.1307 0.6131 0.4462
0.000 0.5398 0.01239 0.00398 -0.1304 0.6016 0.4552
0.250 0.5663 0.01246 0.00404 -0.1301 0.5908 0.4631
0.500 0.5929 0.01256 0.00408 -0.1297 0.5806 0.4725
0.750 0.6192 0.01263 0.00416 -0.1293 0.5699 0.4805
1.250 0.6719 0.01283 0.00432 -0.1286 0.5502 0.4987
1.500 0.6983 0.01293 0.00441 -0.1283 0.5404 0.5082
1.750 0.7243 0.01305 0.00452 -0.1278 0.5314 0.5179
2.000 0.7504 0.01315 0.00464 -0.1274 0.5219 0.5279
2.250 0.7765 0.01328 0.00476 -0.1270 0.5132 0.5388
2.500 0.8023 0.01339 0.00491 -0.1266 0.5041 0.5497
2.750 0.8281 0.01352 0.00506 -0.1262 0.4956 0.5613
3.000 0.8537 0.01365 0.00523 -0.1257 0.4870 0.5741
3.250 0.8793 0.01378 0.00540 -0.1252 0.4787 0.5878
3.500 0.9043 0.01393 0.00558 -0.1246 0.4705 0.6024
3.750 0.9296 0.01406 0.00579 -0.1241 0.4626 0.6188
4.000 0.9543 0.01422 0.00599 -0.1234 0.4546 0.6367
4.250 0.9792 0.01436 0.00621 -0.1228 0.4470 0.6569
4.500 1.0033 0.01451 0.00645 -0.1221 0.4392 0.6799
4.750 1.0272 0.01465 0.00669 -0.1212 0.4320 0.7067
5.000 1.0501 0.01479 0.00694 -0.1202 0.4245 0.7388
5.250 1.0719 0.01492 0.00718 -0.1189 0.4176 0.7787
5.500 1.0911 0.01499 0.00741 -0.1170 0.4103 0.8340
5.750 1.1091 0.01497 0.00751 -0.1147 0.4038 1.0000
6.000 1.1340 0.01522 0.00779 -0.1142 0.3958 1.0000
6.250 1.1578 0.01554 0.00808 -0.1136 0.3888 1.0000
6.500 1.1820 0.01580 0.00839 -0.1130 0.3809 1.0000
6.750 1.2048 0.01613 0.00869 -0.1122 0.3734 1.0000
7.000 1.2280 0.01642 0.00902 -0.1114 0.3653 1.0000
7.250 1.2496 0.01677 0.00936 -0.1104 0.3574 1.0000
7.500 1.2717 0.01707 0.00972 -0.1094 0.3488 1.0000
7.750 1.2917 0.01745 0.01008 -0.1081 0.3407 1.0000
8.000 1.3119 0.01777 0.01047 -0.1068 0.3317 1.0000
8.250 1.3303 0.01816 0.01087 -0.1052 0.3234 1.0000
8.500 1.3484 0.01855 0.01129 -0.1036 0.3138 1.0000
8.750 1.3659 0.01897 0.01175 -0.1019 0.3045 1.0000
9.000 1.3815 0.01946 0.01224 -0.1000 0.2949 1.0000
9.250 1.3983 0.01992 0.01275 -0.0983 0.2844 1.0000
9.500 1.4135 0.02045 0.01331 -0.0963 0.2744 1.0000
9.750 1.4264 0.02107 0.01393 -0.0941 0.2638 1.0000
10.000 1.4406 0.02167 0.01458 -0.0922 0.2524 1.0000
10.250 1.4531 0.02236 0.01530 -0.0901 0.2411 1.0000
10.500 1.4638 0.02315 0.01611 -0.0878 0.2296 1.0000
10.750 1.4728 0.02405 0.01701 -0.0854 0.2175 1.0000
11.000 1.4803 0.02507 0.01803 -0.0829 0.2047 1.0000
11.250 1.4872 0.02619 0.01915 -0.0806 0.1913 1.0000
11.500 1.4927 0.02745 0.02042 -0.0783 0.1780 1.0000
11.750 1.4967 0.02888 0.02186 -0.0760 0.1648 1.0000
12.000 1.4993 0.03049 0.02346 -0.0738 0.1521 1.0000
12.250 1.5006 0.03229 0.02527 -0.0718 0.1400 1.0000
12.500 1.5009 0.03428 0.02726 -0.0699 0.1292 1.0000
12.750 1.4996 0.03652 0.02951 -0.0683 0.1191 1.0000
13.000 1.4992 0.03882 0.03185 -0.0669 0.1099 1.0000
13.250 1.4979 0.04131 0.03439 -0.0657 0.1016 1.0000
13.500 1.4940 0.04421 0.03731 -0.0648 0.0944 1.0000
13.750 1.4929 0.04696 0.04014 -0.0641 0.0873 1.0000
14.000 1.4881 0.05022 0.04346 -0.0637 0.0813 1.0000
14.250 1.4853 0.05341 0.04673 -0.0634 0.0754 1.0000
14.500 1.4791 0.05713 0.05051 -0.0635 0.0707 1.0000
14.750 1.4759 0.06061 0.05408 -0.0636 0.0658 1.0000
15.000 1.4689 0.06470 0.05824 -0.0641 0.0615 1.0000
15.250 1.4640 0.06868 0.06231 -0.0647 0.0577 1.0000
15.500 1.4579 0.07289 0.06662 -0.0655 0.0539 1.0000
15.750 1.4489 0.07769 0.07148 -0.0666 0.0509 1.0000
16.000 1.4446 0.08189 0.07580 -0.0677 0.0476 1.0000
16.250 1.4373 0.08663 0.08063 -0.0690 0.0446 1.0000
16.500 1.4280 0.09181 0.08588 -0.0707 0.0422 1.0000
16.750 1.4233 0.09635 0.09054 -0.0722 0.0395 1.0000
17.000 1.4160 0.10137 0.09566 -0.0740 0.0371 1.0000
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Polar data table (+)
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