EPPLER 403 AIRFOIL (e403-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 403 AIRFOIL (e403-il) Reynolds number: 200,000 Max Cl/Cd: 66.92 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e403-il-200000.txt Download as CSV file: xf-e403-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 403 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
------ -------- --------- --------- -------- -------- --------
-9.500 -0.4776 0.09437 0.09154 -0.0364 1.0000 0.0718
-9.250 -0.5006 0.08715 0.08436 -0.0392 1.0000 0.0730
-9.000 -0.5426 0.07801 0.07520 -0.0431 1.0000 0.0726
-8.750 -0.5914 0.07075 0.06787 -0.0447 1.0000 0.0715
-8.500 -0.7466 0.07413 0.07072 -0.0432 1.0000 0.0647
-8.250 -0.7782 0.07275 0.06884 -0.0426 1.0000 0.0661
-6.750 -0.7213 0.03902 0.03243 -0.0426 1.0000 0.0348
-6.500 -0.7012 0.03510 0.02840 -0.0423 0.9999 0.0329
-6.250 -0.6144 0.03176 0.02447 -0.0534 0.9803 0.0310
-6.000 -0.5758 0.03028 0.02274 -0.0556 0.9748 0.0307
-5.750 -0.5401 0.02927 0.02161 -0.0572 0.9677 0.0323
-5.500 -0.5106 0.02851 0.02075 -0.0579 0.9641 0.0335
-5.250 -0.4744 0.02785 0.02002 -0.0597 0.9608 0.0344
-5.000 -0.4440 0.02670 0.01887 -0.0608 0.9559 0.0355
-4.750 -0.4149 0.02567 0.01788 -0.0622 0.9518 0.0374
-4.500 -0.3778 0.02502 0.01719 -0.0650 0.9487 0.0409
-4.250 -0.3337 0.02432 0.01644 -0.0693 0.9464 0.0510
-4.000 -0.2725 0.02102 0.01560 -0.0804 0.9463 0.5324
-3.750 -0.2483 0.02155 0.01611 -0.0795 0.9408 0.5703
-3.500 -0.2244 0.02248 0.01703 -0.0780 0.9355 0.5986
-3.250 -0.1920 0.02369 0.01817 -0.0779 0.9321 0.6216
-3.000 -0.1795 0.02470 0.01927 -0.0736 0.9250 0.6340
-2.750 -0.1599 0.02575 0.02036 -0.0705 0.9199 0.6454
-2.500 -0.1287 0.02673 0.02130 -0.0699 0.9168 0.6572
-2.250 -0.1144 0.02696 0.02151 -0.0672 0.9091 0.6638
-2.000 -0.0786 0.02698 0.02140 -0.0693 0.9053 0.6706
-1.750 -0.0437 0.02724 0.02161 -0.0703 0.9026 0.6737
-1.500 -0.0228 0.02722 0.02155 -0.0694 0.8954 0.6777
-1.250 0.0190 0.02701 0.02118 -0.0735 0.8915 0.6843
-1.000 0.0547 0.02702 0.02116 -0.0748 0.8885 0.6864
-0.750 0.0777 0.02704 0.02116 -0.0741 0.8819 0.6889
-0.500 0.1097 0.02695 0.02104 -0.0751 0.8767 0.6921
-0.250 0.1522 0.02678 0.02080 -0.0784 0.8741 0.6961
0.000 0.1926 0.02658 0.02052 -0.0816 0.8704 0.7004
0.250 0.2145 0.02647 0.02043 -0.0806 0.8625 0.7025
0.500 0.2537 0.02624 0.02020 -0.0826 0.8597 0.7048
0.750 0.2944 0.02598 0.01993 -0.0851 0.8571 0.7077
1.000 0.3180 0.02584 0.01978 -0.0849 0.8478 0.7117
1.250 0.3642 0.02540 0.01931 -0.0889 0.8454 0.7153
1.500 0.4020 0.02501 0.01897 -0.0905 0.8425 0.7173
1.750 0.4226 0.02489 0.01889 -0.0892 0.8332 0.7198
2.000 0.4641 0.02440 0.01844 -0.0916 0.8308 0.7226
2.250 0.5074 0.02384 0.01791 -0.0944 0.8285 0.7257
2.500 0.5342 0.02363 0.01772 -0.0948 0.8187 0.7294
2.750 0.5771 0.02286 0.01702 -0.0972 0.8164 0.7319
3.000 0.6203 0.02200 0.01625 -0.0993 0.8145 0.7342
3.250 0.6421 0.02172 0.01603 -0.0981 0.8036 0.7369
3.500 0.6875 0.02069 0.01508 -0.1008 0.8015 0.7397
3.750 0.7152 0.02029 0.01476 -0.1008 0.7914 0.7433
4.000 0.7600 0.01921 0.01376 -0.1034 0.7881 0.7464
4.250 0.7868 0.01866 0.01331 -0.1027 0.7778 0.7487
4.500 0.8314 0.01754 0.01230 -0.1050 0.7718 0.7511
4.750 0.8626 0.01694 0.01178 -0.1052 0.7574 0.7540
5.000 0.8962 0.01639 0.01129 -0.1059 0.7387 0.7575
5.250 0.9360 0.01581 0.01074 -0.1079 0.7151 0.7610
5.500 0.9743 0.01533 0.01025 -0.1093 0.6839 0.7633
5.750 1.0084 0.01521 0.01001 -0.1101 0.6425 0.7658
6.000 1.0339 0.01545 0.01005 -0.1095 0.5945 0.7686
6.250 1.0509 0.01597 0.01032 -0.1076 0.5461 0.7720
6.500 1.0644 0.01665 0.01074 -0.1053 0.4985 0.7758
6.750 1.0719 0.01731 0.01124 -0.1017 0.4550 0.7785
7.000 1.0801 0.01805 0.01179 -0.0985 0.4127 0.7815
7.250 1.0888 0.01886 0.01241 -0.0955 0.3705 0.7847
7.500 1.0994 0.01972 0.01308 -0.0932 0.3293 0.7882
7.750 1.1106 0.02060 0.01379 -0.0910 0.2881 0.7915
8.000 1.1194 0.02150 0.01453 -0.0883 0.2499 0.7945
8.250 1.1303 0.02243 0.01533 -0.0861 0.2128 0.7981
8.500 1.1419 0.02350 0.01620 -0.0842 0.1762 0.8018
8.750 1.1551 0.02463 0.01715 -0.0828 0.1383 0.8054
9.000 1.1627 0.02600 0.01828 -0.0803 0.0960 0.8082
9.250 1.1630 0.02815 0.02008 -0.0769 0.0527 0.8113
9.500 1.1690 0.02988 0.02180 -0.0743 0.0415 0.8150
9.750 1.1746 0.03171 0.02365 -0.0720 0.0369 0.8190
10.000 1.1860 0.03298 0.02504 -0.0702 0.0337 0.8226
10.250 1.1946 0.03442 0.02656 -0.0682 0.0314 0.8263
10.500 1.1982 0.03658 0.02875 -0.0659 0.0297 0.8300
10.750 1.2109 0.03813 0.03042 -0.0646 0.0287 0.8341
11.000 1.2233 0.03969 0.03211 -0.0632 0.0278 0.8378
11.250 1.2361 0.04129 0.03384 -0.0618 0.0269 0.8421
11.500 1.2513 0.04297 0.03565 -0.0608 0.0261 0.8470
11.750 1.2679 0.04472 0.03750 -0.0600 0.0254 0.8517
12.000 1.2848 0.04649 0.03939 -0.0590 0.0249 0.8564
12.250 1.3035 0.04849 0.04149 -0.0585 0.0243 0.8615
12.500 1.3290 0.05122 0.04432 -0.0588 0.0235 0.8664
12.750 1.3395 0.05412 0.04751 -0.0575 0.0231 0.8717
13.000 1.3411 0.05657 0.05025 -0.0556 0.0228 0.8782
13.250 1.3414 0.05937 0.05335 -0.0536 0.0226 0.8846
13.500 1.3399 0.06267 0.05696 -0.0519 0.0226 0.8918
13.750 1.3340 0.06616 0.06075 -0.0500 0.0226 0.8994
14.000 1.3250 0.07002 0.06491 -0.0485 0.0226 0.9085
14.250 1.3124 0.07398 0.06917 -0.0468 0.0227 0.9207
14.500 1.2951 0.07766 0.07312 -0.0448 0.0228 0.9617
14.750 1.2807 0.08291 0.07863 -0.0452 0.0229 1.0000
15.000 1.2656 0.08877 0.08473 -0.0463 0.0230 1.0000
15.250 1.2507 0.09523 0.09140 -0.0480 0.0232 1.0000
15.500 1.2376 0.10102 0.09741 -0.0504 0.0234 1.0000
15.750 1.2214 0.10705 0.10366 -0.0536 0.0235 1.0000
16.000 1.2012 0.11429 0.11114 -0.0582 0.0237 1.0000
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Polar data table (+)
Polar graphs
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