EPPLER 582 AIRFOIL (e582-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 582 AIRFOIL (e582-il) Reynolds number: 200,000 Max Cl/Cd: 77.97 at α=8.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e582-il-200000.txt Download as CSV file: xf-e582-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 582 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
------ -------- --------- --------- -------- -------- --------
-11.750 -0.0969 0.11331 0.11003 -0.0847 0.9653 0.0362
-11.500 -0.0989 0.10917 0.10589 -0.0896 0.9628 0.0371
-11.250 -0.0984 0.10458 0.10130 -0.0946 0.9608 0.0374
-11.000 -0.0826 0.09915 0.09588 -0.0959 0.9594 0.0382
-10.750 -0.0663 0.09573 0.09245 -0.0969 0.9552 0.0392
-10.500 -0.0540 0.09192 0.08862 -0.0991 0.9516 0.0404
-10.250 -0.0438 0.08764 0.08433 -0.1022 0.9489 0.0421
-10.000 -0.0351 0.08296 0.07964 -0.1061 0.9466 0.0436
-9.750 -0.0441 0.07704 0.07374 -0.1133 0.9418 0.0461
-9.500 -0.0474 0.07145 0.06815 -0.1192 0.9361 0.0464
-9.250 -0.0556 0.06420 0.06086 -0.1280 0.9319 0.0465
-9.000 -0.0181 0.06238 0.05906 -0.1215 0.9304 0.0489
-8.750 -0.0125 0.05910 0.05577 -0.1226 0.9226 0.0509
-8.500 -0.0103 0.05418 0.05084 -0.1269 0.9173 0.0526
-8.250 -0.0211 0.04903 0.04566 -0.1312 0.9086 0.0529
-8.000 -0.1124 0.05759 0.05389 -0.1368 0.9104 0.0483
-7.750 -0.1020 0.05505 0.05130 -0.1373 0.9038 0.0499
-7.500 -0.0992 0.05250 0.04864 -0.1372 0.8960 0.0515
-7.250 -0.0978 0.04973 0.04567 -0.1367 0.8883 0.0539
-7.000 -0.1161 0.04842 0.04366 -0.1332 0.8779 0.0578
-6.750 -0.0985 0.04396 0.03938 -0.1338 0.8737 0.0597
-6.500 -0.0785 0.02939 0.02461 -0.1250 0.8555 0.0699
-6.250 -0.0656 0.02487 0.02040 -0.1256 0.8518 0.0736
-6.000 -0.0555 0.02318 0.01860 -0.1240 0.8458 0.0785
-5.750 -0.0456 0.02042 0.01551 -0.1229 0.8416 0.0867
-5.500 -0.0364 0.02658 0.01957 -0.1231 0.8468 0.0307
-5.250 -0.0102 0.02481 0.01756 -0.1227 0.8431 0.0293
-5.000 0.0180 0.02282 0.01529 -0.1226 0.8403 0.0285
-4.750 0.0386 0.02163 0.01392 -0.1211 0.8354 0.0283
-4.500 0.0618 0.02057 0.01271 -0.1199 0.8306 0.0288
-4.250 0.0894 0.01963 0.01164 -0.1196 0.8272 0.0299
-4.000 0.1158 0.01845 0.01050 -0.1194 0.8245 0.0328
-3.750 0.1320 0.01811 0.01017 -0.1174 0.8188 0.0383
-3.500 0.1530 0.01740 0.00953 -0.1164 0.8143 0.0503
-3.250 0.1761 0.01621 0.00870 -0.1159 0.8110 0.1259
-3.000 0.1921 0.01437 0.00832 -0.1154 0.8076 0.4589
-2.750 0.1918 0.01468 0.00972 -0.1082 0.8012 0.7409
-2.500 0.2119 0.01541 0.01033 -0.1052 0.7974 0.7911
-2.250 0.2337 0.01593 0.01072 -0.1026 0.7946 0.8170
-2.000 0.2452 0.01649 0.01123 -0.0981 0.7898 0.8344
-1.750 0.2569 0.01689 0.01158 -0.0939 0.7846 0.8505
-1.500 0.2758 0.01710 0.01169 -0.0908 0.7812 0.8665
-1.250 0.3008 0.01718 0.01165 -0.0890 0.7787 0.8814
-1.000 0.3087 0.01745 0.01190 -0.0849 0.7726 0.8939
-0.750 0.3326 0.01756 0.01194 -0.0829 0.7686 0.9111
-0.500 0.3880 0.01761 0.01186 -0.0870 0.7665 0.9333
-0.250 0.4685 0.01740 0.01147 -0.0975 0.7650 0.9377
0.000 0.5128 0.01722 0.01115 -0.1010 0.7627 0.9412
0.250 0.5141 0.01745 0.01143 -0.0964 0.7555 0.9479
0.500 0.5533 0.01731 0.01121 -0.0990 0.7518 0.9501
0.750 0.5921 0.01712 0.01092 -0.1015 0.7489 0.9522
1.000 0.6103 0.01723 0.01102 -0.1001 0.7437 0.9559
1.250 0.6178 0.01731 0.01110 -0.0965 0.7379 0.9600
1.500 0.6567 0.01710 0.01083 -0.0990 0.7346 0.9611
1.750 0.6936 0.01697 0.01063 -0.1011 0.7311 0.9624
2.000 0.7089 0.01713 0.01085 -0.0993 0.7241 0.9653
2.250 0.7398 0.01698 0.01065 -0.1002 0.7200 0.9669
2.500 0.7756 0.01679 0.01040 -0.1019 0.7169 0.9680
2.750 0.7721 0.01708 0.01078 -0.0964 0.7090 0.9719
3.000 0.8051 0.01691 0.01058 -0.0977 0.7047 0.9730
3.250 0.8429 0.01670 0.01030 -0.0998 0.7015 0.9734
3.500 0.8569 0.01691 0.01063 -0.0978 0.6933 0.9760
3.750 0.8911 0.01669 0.01039 -0.0993 0.6888 0.9770
4.000 0.9148 0.01667 0.01038 -0.0988 0.6830 0.9786
4.250 0.9348 0.01666 0.01041 -0.0977 0.6762 0.9806
4.500 0.9712 0.01638 0.01012 -0.0994 0.6717 0.9816
4.750 0.9838 0.01652 0.01035 -0.0970 0.6637 0.9844
5.000 1.0177 0.01629 0.01011 -0.0984 0.6581 0.9851
5.250 1.0413 0.01630 0.01021 -0.0980 0.6504 0.9870
5.500 1.0719 0.01611 0.01004 -0.0988 0.6436 0.9884
5.750 1.0966 0.01610 0.01009 -0.0986 0.6355 0.9910
6.000 1.1269 0.01590 0.00992 -0.0993 0.6280 0.9928
6.250 1.1472 0.01593 0.01004 -0.0983 0.6185 0.9958
6.500 1.1787 0.01575 0.00986 -0.0992 0.6103 0.9976
6.750 1.1897 0.01578 0.00998 -0.0963 0.5999 1.0000
7.000 1.1916 0.01578 0.01004 -0.0915 0.5905 1.0000
7.250 1.2069 0.01567 0.00990 -0.0893 0.5811 1.0000
7.500 1.2112 0.01574 0.01005 -0.0852 0.5694 1.0000
7.750 1.2261 0.01584 0.01022 -0.0832 0.5567 1.0000
8.000 1.2426 0.01596 0.01038 -0.0815 0.5432 1.0000
8.250 1.2592 0.01615 0.01059 -0.0800 0.5282 1.0000
8.500 1.2758 0.01641 0.01086 -0.0784 0.5118 1.0000
8.750 1.2919 0.01675 0.01121 -0.0769 0.4941 1.0000
9.000 1.3060 0.01721 0.01165 -0.0752 0.4752 1.0000
9.250 1.3173 0.01781 0.01226 -0.0732 0.4551 1.0000
9.500 1.3281 0.01851 0.01292 -0.0712 0.4344 1.0000
9.750 1.3367 0.01935 0.01372 -0.0690 0.4130 1.0000
10.000 1.3435 0.02033 0.01467 -0.0667 0.3911 1.0000
10.250 1.3489 0.02146 0.01574 -0.0644 0.3694 1.0000
10.500 1.3530 0.02272 0.01696 -0.0621 0.3475 1.0000
10.750 1.3558 0.02414 0.01829 -0.0597 0.3269 1.0000
11.000 1.3588 0.02562 0.01975 -0.0577 0.3055 1.0000
11.250 1.3604 0.02727 0.02134 -0.0556 0.2852 1.0000
11.500 1.3616 0.02902 0.02304 -0.0536 0.2661 1.0000
11.750 1.3634 0.03082 0.02483 -0.0518 0.2465 1.0000
12.000 1.3640 0.03277 0.02674 -0.0501 0.2279 1.0000
12.250 1.3641 0.03485 0.02877 -0.0485 0.2104 1.0000
12.500 1.3644 0.03701 0.03089 -0.0471 0.1936 1.0000
12.750 1.3655 0.03919 0.03307 -0.0458 0.1770 1.0000
13.000 1.3657 0.04153 0.03540 -0.0446 0.1605 1.0000
13.250 1.3652 0.04401 0.03786 -0.0436 0.1451 1.0000
13.500 1.3642 0.04665 0.04047 -0.0426 0.1304 1.0000
13.750 1.3623 0.04946 0.04326 -0.0418 0.1163 1.0000
14.000 1.3600 0.05240 0.04620 -0.0411 0.1031 1.0000
14.250 1.3571 0.05552 0.04931 -0.0406 0.0910 1.0000
14.500 1.3537 0.05880 0.05260 -0.0402 0.0799 1.0000
14.750 1.3496 0.06228 0.05608 -0.0399 0.0705 1.0000
15.000 1.3428 0.06614 0.05990 -0.0397 0.0630 1.0000
15.250 1.3409 0.06958 0.06342 -0.0398 0.0558 1.0000
15.500 1.3365 0.07338 0.06727 -0.0399 0.0501 1.0000
15.750 1.3317 0.07734 0.07126 -0.0403 0.0452 1.0000
16.000 1.3285 0.08116 0.07518 -0.0407 0.0406 1.0000
16.250 1.3243 0.08523 0.07930 -0.0415 0.0369 1.0000
16.500 1.3201 0.08935 0.08351 -0.0422 0.0333 1.0000
16.750 1.3170 0.09345 0.08770 -0.0432 0.0302 1.0000
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