E392 (10.15%) (e392-il) Xfoil prediction polar at RE=200,000 Ncrit=9
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Airfoil: E392 (10.15%) (e392-il) Reynolds number: 200,000 Max Cl/Cd: 86.19 at α=7° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e392-il-200000.txt Download as CSV file: xf-e392-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: E392 (10.15%)
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
------ -------- --------- --------- -------- -------- --------
-8.250 -0.3185 0.08934 0.08604 -0.0397 1.0000 0.0418
-8.000 -0.3185 0.08676 0.08353 -0.0396 1.0000 0.0429
-7.750 -0.3218 0.08437 0.08121 -0.0392 1.0000 0.0437
-7.500 -0.3309 0.08233 0.07927 -0.0379 1.0000 0.0444
-7.250 -0.3527 0.08159 0.07866 -0.0338 1.0000 0.0446
-7.000 -0.3403 0.07678 0.07389 -0.0420 0.9923 0.0471
-6.750 -0.2924 0.06468 0.06143 -0.0743 0.9752 0.0498
-6.500 -0.2735 0.05849 0.05539 -0.0762 0.9714 0.0516
-6.250 -0.2469 0.05530 0.05219 -0.0792 0.9624 0.0537
-6.000 -0.2115 0.04960 0.04628 -0.0883 0.9542 0.0590
-5.750 -0.1789 0.04231 0.03852 -0.0978 0.9437 0.0646
-5.500 -0.1510 0.04019 0.03639 -0.0994 0.9325 0.0709
-5.250 -0.1227 0.03605 0.03189 -0.1032 0.9204 0.0796
-5.000 -0.0880 0.02540 0.01972 -0.1050 0.9092 0.0373
-4.750 -0.0592 0.02168 0.01548 -0.1057 0.8990 0.0344
-4.500 -0.0314 0.01918 0.01245 -0.1053 0.8869 0.0328
-4.250 -0.0040 0.01753 0.01048 -0.1048 0.8747 0.0329
-4.000 0.0231 0.01630 0.00904 -0.1043 0.8633 0.0343
-3.750 0.0503 0.01541 0.00798 -0.1038 0.8528 0.0371
-3.500 0.0764 0.01438 0.00687 -0.1033 0.8424 0.0427
-3.250 0.1030 0.01368 0.00607 -0.1028 0.8315 0.0502
-3.000 0.1295 0.01261 0.00513 -0.1026 0.8219 0.0915
-2.750 0.1560 0.01183 0.00470 -0.1026 0.8130 0.1824
-2.500 0.1812 0.01104 0.00453 -0.1027 0.8032 0.3532
-2.250 0.2065 0.01060 0.00450 -0.1023 0.7952 0.5009
-2.000 0.2315 0.01037 0.00449 -0.1015 0.7863 0.5976
-1.750 0.2559 0.01022 0.00449 -0.1004 0.7784 0.6751
-1.500 0.2791 0.01009 0.00447 -0.0989 0.7707 0.7459
-1.250 0.3004 0.00998 0.00447 -0.0969 0.7630 0.8130
-1.000 0.3206 0.00987 0.00441 -0.0945 0.7559 0.8832
-0.750 0.3589 0.00973 0.00422 -0.0961 0.7488 0.9720
-0.500 0.3930 0.00979 0.00410 -0.0976 0.7416 1.0000
-0.250 0.4207 0.00992 0.00409 -0.0978 0.7346 1.0000
0.000 0.4486 0.01005 0.00408 -0.0979 0.7277 1.0000
0.250 0.4764 0.01020 0.00411 -0.0980 0.7213 1.0000
0.500 0.5040 0.01034 0.00416 -0.0980 0.7142 1.0000
0.750 0.5321 0.01050 0.00420 -0.0981 0.7085 1.0000
1.000 0.5594 0.01065 0.00431 -0.0981 0.7012 1.0000
1.250 0.5876 0.01081 0.00435 -0.0981 0.6957 1.0000
1.500 0.6147 0.01098 0.00451 -0.0981 0.6886 1.0000
1.750 0.6426 0.01114 0.00461 -0.0981 0.6827 1.0000
2.000 0.6700 0.01132 0.00477 -0.0981 0.6763 1.0000
2.250 0.6975 0.01149 0.00491 -0.0981 0.6698 1.0000
2.500 0.7253 0.01168 0.00505 -0.0981 0.6640 1.0000
2.750 0.7522 0.01185 0.00526 -0.0980 0.6568 1.0000
3.000 0.7805 0.01202 0.00536 -0.0980 0.6513 1.0000
3.250 0.8067 0.01220 0.00560 -0.0978 0.6431 1.0000
3.500 0.8348 0.01234 0.00568 -0.0977 0.6369 1.0000
3.750 0.8608 0.01249 0.00593 -0.0974 0.6280 1.0000
4.000 0.8883 0.01263 0.00604 -0.0973 0.6209 1.0000
4.250 0.9146 0.01276 0.00623 -0.0970 0.6119 1.0000
4.500 0.9413 0.01289 0.00641 -0.0967 0.6034 1.0000
4.750 0.9683 0.01298 0.00650 -0.0964 0.5946 1.0000
5.000 0.9940 0.01309 0.00670 -0.0960 0.5843 1.0000
5.250 1.0203 0.01319 0.00684 -0.0956 0.5745 1.0000
5.500 1.0469 0.01326 0.00693 -0.0952 0.5644 1.0000
5.750 1.0720 0.01334 0.00711 -0.0946 0.5521 1.0000
6.000 1.0970 0.01340 0.00726 -0.0940 0.5388 1.0000
6.250 1.1217 0.01346 0.00740 -0.0933 0.5239 1.0000
6.500 1.1457 0.01353 0.00750 -0.0925 0.5058 1.0000
6.750 1.1681 0.01360 0.00762 -0.0913 0.4800 1.0000
7.000 1.1894 0.01380 0.00780 -0.0901 0.4486 1.0000
7.250 1.2091 0.01416 0.00811 -0.0887 0.4079 1.0000
7.500 1.2247 0.01486 0.00856 -0.0867 0.3471 1.0000
7.750 1.2349 0.01605 0.00935 -0.0842 0.2744 1.0000
8.000 1.2433 0.01747 0.01039 -0.0817 0.2109 1.0000
8.250 1.2518 0.01888 0.01150 -0.0792 0.1574 1.0000
8.500 1.2564 0.02054 0.01281 -0.0763 0.1036 1.0000
8.750 1.2513 0.02274 0.01460 -0.0720 0.0560 1.0000
9.000 1.2483 0.02457 0.01635 -0.0678 0.0431 1.0000
9.250 1.2515 0.02606 0.01796 -0.0648 0.0383 1.0000
9.500 1.2554 0.02759 0.01954 -0.0622 0.0348 1.0000
9.750 1.2516 0.02981 0.02181 -0.0593 0.0326 1.0000
10.000 1.2579 0.03145 0.02357 -0.0574 0.0311 1.0000
10.250 1.2635 0.03326 0.02549 -0.0556 0.0298 1.0000
10.500 1.2700 0.03514 0.02746 -0.0539 0.0285 1.0000
10.750 1.2777 0.03704 0.02944 -0.0524 0.0276 1.0000
11.000 1.2870 0.03897 0.03143 -0.0510 0.0266 1.0000
11.250 1.2991 0.04094 0.03345 -0.0497 0.0258 1.0000
11.500 1.3243 0.04390 0.03648 -0.0486 0.0243 1.0000
11.750 1.3326 0.04572 0.03852 -0.0474 0.0237 1.0000
12.000 1.3440 0.04802 0.04106 -0.0463 0.0232 1.0000
12.250 1.3543 0.05078 0.04409 -0.0451 0.0229 1.0000
12.500 1.3606 0.05395 0.04754 -0.0440 0.0228 1.0000
12.750 1.3615 0.05751 0.05140 -0.0429 0.0227 1.0000
13.000 1.3578 0.06144 0.05562 -0.0419 0.0227 1.0000
13.250 1.3499 0.06574 0.06022 -0.0413 0.0228 1.0000
13.500 1.3384 0.07043 0.06519 -0.0411 0.0229 1.0000
13.750 1.3244 0.07540 0.07043 -0.0414 0.0230 1.0000
14.000 1.3081 0.08079 0.07607 -0.0423 0.0231 1.0000
14.250 1.2904 0.08653 0.08205 -0.0437 0.0232 1.0000
14.500 1.2714 0.09274 0.08848 -0.0458 0.0233 1.0000
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Polar data table (+)
Polar graphs
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