S3025 9.38% (s3025-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: S3025 9.38% (s3025-il) Reynolds number: 500,000 Max Cl/Cd: 99.4 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s3025-il-500000-n5.txt Download as CSV file: xf-s3025-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: S3025 9.38%
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.3469 0.08652 0.08432 -0.0349 1.0000 0.0100
-8.250 -0.3480 0.08365 0.08148 -0.0352 1.0000 0.0099
-8.000 -0.3511 0.08172 0.07959 -0.0338 1.0000 0.0092
-7.750 -0.3422 0.07724 0.07513 -0.0383 0.9943 0.0085
-7.500 -0.3306 0.07150 0.06940 -0.0458 0.9854 0.0081
-7.250 -0.3144 0.06355 0.06143 -0.0575 0.9745 0.0077
-7.000 -0.2951 0.05223 0.04998 -0.0724 0.9603 0.0073
-6.750 -0.2724 0.04704 0.04467 -0.0787 0.9462 0.0076
-6.500 -0.2523 0.03976 0.03712 -0.0845 0.9276 0.0077
-5.500 -0.1821 0.01848 0.01344 -0.0858 0.8491 0.0068
-5.250 -0.1594 0.01663 0.01118 -0.0851 0.8337 0.0068
-5.000 -0.1359 0.01498 0.00917 -0.0843 0.8192 0.0069
-4.750 -0.1115 0.01378 0.00770 -0.0837 0.8055 0.0070
-4.500 -0.0865 0.01288 0.00661 -0.0832 0.7928 0.0073
-4.250 -0.0609 0.01224 0.00584 -0.0827 0.7804 0.0076
-4.000 -0.0351 0.01171 0.00517 -0.0823 0.7689 0.0079
-3.750 -0.0090 0.01124 0.00459 -0.0819 0.7573 0.0084
-3.500 0.0173 0.01082 0.00405 -0.0815 0.7465 0.0088
-3.250 0.0438 0.01049 0.00362 -0.0812 0.7363 0.0094
-2.750 0.0971 0.00985 0.00281 -0.0806 0.7166 0.0112
-2.500 0.1240 0.00962 0.00248 -0.0803 0.7075 0.0120
-2.250 0.1511 0.00946 0.00222 -0.0800 0.6982 0.0132
-2.000 0.1784 0.00929 0.00199 -0.0798 0.6893 0.0156
-1.750 0.2052 0.00904 0.00179 -0.0796 0.6806 0.0383
-1.500 0.2316 0.00870 0.00167 -0.0794 0.6715 0.1054
-1.250 0.2583 0.00847 0.00158 -0.0793 0.6626 0.1644
-0.750 0.3107 0.00787 0.00149 -0.0789 0.6441 0.3583
-0.500 0.3363 0.00754 0.00148 -0.0787 0.6351 0.4771
-0.250 0.3615 0.00725 0.00147 -0.0782 0.6255 0.5904
0.000 0.3858 0.00694 0.00149 -0.0774 0.6162 0.7066
0.250 0.4067 0.00661 0.00154 -0.0756 0.6070 0.8431
0.500 0.4427 0.00652 0.00156 -0.0768 0.5964 0.9578
0.750 0.4840 0.00657 0.00153 -0.0798 0.5853 0.9898
1.000 0.5179 0.00664 0.00152 -0.0811 0.5749 1.0000
1.250 0.5432 0.00674 0.00154 -0.0806 0.5648 1.0000
1.500 0.5689 0.00684 0.00158 -0.0801 0.5538 1.0000
1.750 0.5947 0.00694 0.00162 -0.0796 0.5432 1.0000
2.000 0.6204 0.00705 0.00167 -0.0792 0.5321 1.0000
2.250 0.6461 0.00717 0.00173 -0.0787 0.5203 1.0000
2.750 0.6976 0.00744 0.00188 -0.0779 0.4945 1.0000
3.000 0.7232 0.00759 0.00197 -0.0774 0.4798 1.0000
3.250 0.7487 0.00775 0.00207 -0.0770 0.4643 1.0000
3.500 0.7742 0.00793 0.00220 -0.0766 0.4475 1.0000
3.750 0.7996 0.00812 0.00232 -0.0761 0.4307 1.0000
4.000 0.8248 0.00833 0.00247 -0.0757 0.4129 1.0000
4.250 0.8499 0.00855 0.00264 -0.0752 0.3951 1.0000
4.500 0.8747 0.00880 0.00281 -0.0747 0.3762 1.0000
4.750 0.8994 0.00906 0.00301 -0.0742 0.3558 1.0000
5.000 0.9237 0.00936 0.00322 -0.0736 0.3348 1.0000
5.250 0.9481 0.00966 0.00347 -0.0731 0.3142 1.0000
5.500 0.9717 0.01001 0.00373 -0.0725 0.2915 1.0000
5.750 0.9946 0.01043 0.00403 -0.0718 0.2638 1.0000
6.000 1.0178 0.01083 0.00433 -0.0711 0.2391 1.0000
6.250 1.0402 0.01129 0.00468 -0.0703 0.2120 1.0000
6.500 1.0614 0.01186 0.00508 -0.0694 0.1798 1.0000
6.750 1.0832 0.01235 0.00546 -0.0686 0.1551 1.0000
7.000 1.1051 0.01284 0.00586 -0.0678 0.1345 1.0000
7.250 1.1262 0.01337 0.00632 -0.0668 0.1144 1.0000
7.500 1.1461 0.01400 0.00682 -0.0658 0.0902 1.0000
7.750 1.1660 0.01461 0.00734 -0.0647 0.0709 1.0000
8.000 1.1849 0.01528 0.00792 -0.0634 0.0524 1.0000
8.250 1.2019 0.01608 0.00860 -0.0619 0.0323 1.0000
8.500 1.2174 0.01698 0.00941 -0.0602 0.0153 1.0000
8.750 1.2355 0.01763 0.01008 -0.0588 0.0123 1.0000
9.000 1.2535 0.01825 0.01075 -0.0574 0.0110 1.0000
9.250 1.2716 0.01883 0.01140 -0.0560 0.0103 1.0000
9.500 1.2885 0.01943 0.01208 -0.0545 0.0097 1.0000
9.750 1.3025 0.02009 0.01282 -0.0525 0.0092 1.0000
10.000 1.3151 0.02081 0.01363 -0.0503 0.0088 1.0000
10.250 1.3263 0.02162 0.01453 -0.0480 0.0085 1.0000
10.500 1.3365 0.02250 0.01550 -0.0457 0.0082 1.0000
10.750 1.3438 0.02360 0.01669 -0.0432 0.0079 1.0000
11.000 1.3496 0.02484 0.01803 -0.0407 0.0077 1.0000
11.250 1.3548 0.02616 0.01946 -0.0384 0.0075 1.0000
11.500 1.3608 0.02749 0.02089 -0.0364 0.0075 1.0000
11.750 1.3667 0.02890 0.02242 -0.0347 0.0074 1.0000
12.000 1.3705 0.03057 0.02420 -0.0330 0.0073 1.0000
12.250 1.3751 0.03227 0.02602 -0.0316 0.0071 1.0000
12.500 1.3780 0.03422 0.02809 -0.0304 0.0070 1.0000
12.750 1.3801 0.03636 0.03034 -0.0294 0.0069 1.0000
13.000 1.3832 0.03849 0.03258 -0.0286 0.0066 1.0000
13.250 1.3825 0.04112 0.03534 -0.0280 0.0065 1.0000
13.500 1.3824 0.04381 0.03814 -0.0276 0.0064 1.0000
13.750 1.3825 0.04657 0.04102 -0.0275 0.0062 1.0000
14.000 1.3805 0.04968 0.04425 -0.0275 0.0061 1.0000
14.250 1.3775 0.05304 0.04772 -0.0278 0.0060 1.0000
14.500 1.3736 0.05664 0.05146 -0.0283 0.0059 1.0000
14.750 1.3694 0.06039 0.05533 -0.0290 0.0059 1.0000
15.000 1.3647 0.06438 0.05945 -0.0300 0.0058 1.0000
15.250 1.3589 0.06870 0.06389 -0.0311 0.0058 1.0000
15.500 1.3528 0.07317 0.06849 -0.0326 0.0057 1.0000
15.750 1.3464 0.07789 0.07332 -0.0343 0.0056 1.0000
16.000 1.3394 0.08285 0.07841 -0.0361 0.0056 1.0000
16.250 1.3314 0.08809 0.08377 -0.0382 0.0055 1.0000
16.500 1.3239 0.09340 0.08921 -0.0405 0.0055 1.0000
16.750 1.3155 0.09901 0.09493 -0.0430 0.0054 1.0000
17.000 1.3068 0.10480 0.10085 -0.0457 0.0053 1.0000
17.250 1.2976 0.11076 0.10692 -0.0486 0.0053 1.0000
17.500 1.2880 0.11691 0.11320 -0.0516 0.0052 1.0000
17.750 1.2791 0.12308 0.11950 -0.0548 0.0052 1.0000
18.000 1.2681 0.12972 0.12627 -0.0583 0.0051 1.0000
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Polar data table (+)
Polar graphs
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