EPPLER E852 AIRFOIL (e852-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER E852 AIRFOIL (e852-il) Reynolds number: 200,000 Max Cl/Cd: 79.73 at α=4° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e852-il-200000-n5.txt Download as CSV file: xf-e852-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER E852 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
------ -------- --------- --------- -------- -------- --------
-9.750 -0.3514 0.09048 0.08719 -0.0431 1.0000 0.0120
-9.500 -0.3601 0.08515 0.08199 -0.0439 1.0000 0.0114
-9.250 -0.4400 0.08704 0.08368 -0.0453 1.0000 0.0102
-9.000 -0.4357 0.08396 0.08064 -0.0458 1.0000 0.0095
-8.750 -0.4458 0.07928 0.07603 -0.0469 1.0000 0.0096
-8.500 -0.4626 0.07398 0.07083 -0.0481 1.0000 0.0098
-7.500 -0.4442 0.04914 0.04544 -0.0763 0.9742 0.0091
-7.250 -0.4339 0.04279 0.03871 -0.0811 0.9654 0.0089
-7.000 -0.4173 0.03733 0.03280 -0.0844 0.9580 0.0088
-6.750 -0.3987 0.03284 0.02782 -0.0862 0.9506 0.0087
-6.500 -0.3737 0.02886 0.02330 -0.0880 0.9457 0.0087
-6.250 -0.3461 0.02561 0.01947 -0.0894 0.9419 0.0087
-6.000 -0.3206 0.02306 0.01650 -0.0897 0.9361 0.0087
-5.750 -0.2900 0.02081 0.01390 -0.0907 0.9329 0.0088
-5.500 -0.2571 0.01896 0.01177 -0.0921 0.9305 0.0091
-5.250 -0.2309 0.01736 0.01000 -0.0921 0.9245 0.0095
-5.000 -0.2009 0.01551 0.00793 -0.0931 0.9206 0.0113
-4.750 -0.1671 0.01455 0.00683 -0.0947 0.9177 0.0156
-4.500 -0.1380 0.01381 0.00602 -0.0953 0.9121 0.0294
-4.250 -0.1065 0.01305 0.00533 -0.0965 0.9078 0.0588
-4.000 -0.0733 0.01224 0.00475 -0.0983 0.9046 0.1235
-3.750 -0.0454 0.01132 0.00423 -0.0993 0.8991 0.2498
-3.500 -0.0159 0.01061 0.00405 -0.1003 0.8944 0.4080
-3.250 0.0173 0.01043 0.00392 -0.1015 0.8910 0.4697
-3.000 0.0454 0.01037 0.00384 -0.1016 0.8853 0.5021
-2.750 0.0761 0.01031 0.00371 -0.1022 0.8807 0.5261
-2.500 0.1083 0.01025 0.00362 -0.1031 0.8772 0.5529
-2.250 0.1349 0.01024 0.00358 -0.1029 0.8711 0.5753
-2.000 0.1650 0.01021 0.00349 -0.1033 0.8667 0.5893
-1.750 0.1952 0.01016 0.00340 -0.1039 0.8626 0.5992
-1.500 0.2228 0.01015 0.00336 -0.1039 0.8571 0.6082
-1.250 0.2525 0.01013 0.00327 -0.1043 0.8529 0.6175
-1.000 0.2813 0.01011 0.00324 -0.1046 0.8486 0.6261
-0.750 0.3087 0.01011 0.00324 -0.1046 0.8434 0.6352
-0.500 0.3379 0.01011 0.00323 -0.1049 0.8393 0.6451
-0.250 0.3659 0.01011 0.00326 -0.1050 0.8349 0.6544
0.000 0.3929 0.01013 0.00331 -0.1049 0.8299 0.6646
0.250 0.4217 0.01013 0.00335 -0.1051 0.8259 0.6754
0.500 0.4491 0.01016 0.00342 -0.1051 0.8214 0.6870
0.750 0.4758 0.01019 0.00351 -0.1050 0.8164 0.6991
1.000 0.5041 0.01020 0.00360 -0.1051 0.8122 0.7120
1.250 0.5303 0.01023 0.00372 -0.1047 0.8069 0.7259
1.500 0.5569 0.01025 0.00383 -0.1045 0.8013 0.7408
1.750 0.5841 0.01025 0.00393 -0.1043 0.7961 0.7571
2.000 0.6090 0.01027 0.00406 -0.1036 0.7887 0.7753
2.250 0.6347 0.01025 0.00420 -0.1030 0.7811 0.7956
2.500 0.6598 0.01021 0.00426 -0.1021 0.7716 0.8188
2.750 0.6828 0.01015 0.00433 -0.1008 0.7594 0.8464
3.000 0.7056 0.01005 0.00433 -0.0992 0.7440 0.8817
3.250 0.7310 0.00992 0.00431 -0.0983 0.7222 0.9386
3.500 0.7601 0.00991 0.00434 -0.0984 0.6995 1.0000
3.750 0.7847 0.01000 0.00449 -0.0976 0.6752 1.0000
4.000 0.8077 0.01013 0.00457 -0.0965 0.6365 1.0000
4.250 0.8266 0.01047 0.00463 -0.0944 0.5596 1.0000
4.500 0.8345 0.01147 0.00495 -0.0905 0.4320 1.0000
4.750 0.8407 0.01280 0.00561 -0.0868 0.3053 1.0000
5.000 0.8515 0.01401 0.00630 -0.0841 0.2035 1.0000
5.250 0.8669 0.01498 0.00696 -0.0823 0.1388 1.0000
5.500 0.8832 0.01591 0.00765 -0.0806 0.0904 1.0000
5.750 0.9007 0.01676 0.00836 -0.0790 0.0580 1.0000
6.000 0.9169 0.01774 0.00917 -0.0773 0.0271 1.0000
6.250 0.9321 0.01888 0.01016 -0.0753 0.0093 1.0000
6.500 0.9504 0.01976 0.01115 -0.0737 0.0061 1.0000
6.750 0.9674 0.02078 0.01230 -0.0719 0.0051 1.0000
7.000 0.9814 0.02218 0.01387 -0.0697 0.0044 1.0000
7.250 0.9949 0.02374 0.01560 -0.0674 0.0041 1.0000
7.500 1.0114 0.02519 0.01721 -0.0656 0.0040 1.0000
7.750 1.0296 0.02689 0.01911 -0.0641 0.0039 1.0000
8.000 1.0498 0.02896 0.02141 -0.0630 0.0037 1.0000
8.250 1.0701 0.03130 0.02404 -0.0620 0.0037 1.0000
8.500 1.0880 0.03394 0.02702 -0.0606 0.0036 1.0000
8.750 1.1017 0.03679 0.03024 -0.0587 0.0036 1.0000
9.000 1.1101 0.03988 0.03373 -0.0561 0.0036 1.0000
9.250 1.1122 0.04304 0.03728 -0.0528 0.0036 1.0000
9.500 1.1091 0.04618 0.04076 -0.0491 0.0036 1.0000
9.750 1.1013 0.04947 0.04439 -0.0453 0.0037 1.0000
10.000 1.0905 0.05285 0.04806 -0.0417 0.0037 1.0000
10.250 1.0768 0.05648 0.05197 -0.0387 0.0037 1.0000
10.500 1.0614 0.06036 0.05611 -0.0364 0.0037 1.0000
10.750 1.0447 0.06458 0.06056 -0.0351 0.0038 1.0000
11.000 1.0257 0.06946 0.06565 -0.0346 0.0038 1.0000
11.250 1.0064 0.07482 0.07120 -0.0354 0.0038 1.0000
11.500 0.9866 0.08090 0.07746 -0.0374 0.0038 1.0000
11.750 0.9662 0.08802 0.08474 -0.0410 0.0038 1.0000
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Polar data table (+)
Polar graphs
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