S3025 9.38% (s3025-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: S3025 9.38% (s3025-il) Reynolds number: 200,000 Max Cl/Cd: 79.99 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s3025-il-200000.txt Download as CSV file: xf-s3025-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.3341 0.09136 0.08795 -0.0334 1.0000 0.0394
-8.000 -0.3401 0.08874 0.08541 -0.0351 1.0000 0.0418
-7.750 -0.3450 0.08616 0.08291 -0.0352 1.0000 0.0420
-7.500 -0.2902 0.07064 0.06778 -0.0342 1.0000 0.0454
-7.250 -0.3033 0.06911 0.06633 -0.0312 1.0000 0.0457
-7.000 -0.3242 0.06826 0.06559 -0.0277 0.9994 0.0458
-6.750 -0.3075 0.06351 0.06083 -0.0321 0.9942 0.0476
-6.500 -0.2900 0.05785 0.05515 -0.0398 0.9869 0.0498
-6.250 -0.3697 0.06831 0.06539 -0.0397 0.9941 0.0463
-6.000 -0.3386 0.06353 0.06055 -0.0468 0.9876 0.0491
-5.750 -0.2869 0.05593 0.05227 -0.0648 0.9768 0.0553
-5.500 -0.2642 0.04913 0.04561 -0.0684 0.9730 0.0574
-5.250 -0.2365 0.04625 0.04270 -0.0708 0.9651 0.0601
-5.000 -0.1952 0.04057 0.03637 -0.0786 0.9592 0.0698
-4.750 -0.1678 0.03759 0.03347 -0.0802 0.9511 0.0725
-4.500 -0.1289 0.03395 0.02935 -0.0846 0.9461 0.0842
-4.250 -0.0918 0.02568 0.02002 -0.0850 0.9387 0.0412
-4.000 -0.0541 0.02186 0.01537 -0.0858 0.9330 0.0326
-3.750 -0.0204 0.01923 0.01237 -0.0867 0.9261 0.0318
-3.500 0.0138 0.01755 0.01036 -0.0876 0.9188 0.0340
-3.250 0.0455 0.01597 0.00868 -0.0880 0.9104 0.0353
-3.000 0.0785 0.01476 0.00741 -0.0885 0.9027 0.0371
-2.750 0.1069 0.01391 0.00650 -0.0882 0.8919 0.0400
-2.500 0.1356 0.01304 0.00556 -0.0880 0.8819 0.0465
-2.250 0.1633 0.01171 0.00465 -0.0877 0.8726 0.1428
-2.000 0.1868 0.01086 0.00446 -0.0872 0.8606 0.3291
-1.750 0.2050 0.00979 0.00446 -0.0852 0.8492 0.6123
-1.500 0.2418 0.00900 0.00439 -0.0851 0.8415 0.9258
-1.250 0.3081 0.00885 0.00400 -0.0928 0.8325 1.0000
-1.000 0.3320 0.00892 0.00386 -0.0919 0.8207 1.0000
-0.750 0.3563 0.00899 0.00375 -0.0910 0.8094 1.0000
-0.500 0.3812 0.00908 0.00364 -0.0902 0.7990 1.0000
-0.250 0.4051 0.00917 0.00360 -0.0893 0.7872 1.0000
0.000 0.4295 0.00928 0.00358 -0.0885 0.7759 1.0000
0.250 0.4544 0.00939 0.00355 -0.0877 0.7653 1.0000
0.500 0.4798 0.00950 0.00352 -0.0870 0.7553 1.0000
0.750 0.5044 0.00961 0.00354 -0.0863 0.7438 1.0000
1.000 0.5294 0.00973 0.00358 -0.0856 0.7329 1.0000
1.250 0.5549 0.00986 0.00360 -0.0849 0.7226 1.0000
1.500 0.5806 0.00998 0.00363 -0.0843 0.7122 1.0000
1.750 0.6057 0.01010 0.00370 -0.0837 0.7008 1.0000
2.000 0.6311 0.01023 0.00377 -0.0831 0.6899 1.0000
2.250 0.6570 0.01037 0.00383 -0.0826 0.6797 1.0000
2.500 0.6826 0.01049 0.00392 -0.0820 0.6686 1.0000
2.750 0.7079 0.01062 0.00403 -0.0814 0.6569 1.0000
3.000 0.7334 0.01076 0.00413 -0.0808 0.6454 1.0000
3.250 0.7590 0.01090 0.00423 -0.0802 0.6339 1.0000
3.500 0.7846 0.01104 0.00435 -0.0797 0.6221 1.0000
3.750 0.8099 0.01118 0.00446 -0.0791 0.6094 1.0000
4.000 0.8349 0.01131 0.00459 -0.0784 0.5957 1.0000
4.250 0.8598 0.01146 0.00473 -0.0778 0.5817 1.0000
4.500 0.8846 0.01161 0.00489 -0.0771 0.5670 1.0000
4.750 0.9093 0.01178 0.00505 -0.0764 0.5518 1.0000
5.000 0.9337 0.01196 0.00521 -0.0756 0.5359 1.0000
5.250 0.9577 0.01214 0.00542 -0.0749 0.5181 1.0000
5.500 0.9815 0.01234 0.00565 -0.0740 0.4995 1.0000
5.750 1.0049 0.01259 0.00587 -0.0731 0.4800 1.0000
6.000 1.0279 0.01285 0.00613 -0.0722 0.4586 1.0000
6.250 1.0503 0.01316 0.00643 -0.0712 0.4368 1.0000
6.500 1.0724 0.01350 0.00676 -0.0702 0.4133 1.0000
6.750 1.0937 0.01391 0.00712 -0.0691 0.3897 1.0000
7.000 1.1144 0.01436 0.00753 -0.0679 0.3645 1.0000
7.250 1.1342 0.01485 0.00798 -0.0666 0.3368 1.0000
7.500 1.1529 0.01542 0.00847 -0.0652 0.3076 1.0000
7.750 1.1707 0.01604 0.00900 -0.0637 0.2781 1.0000
8.000 1.1881 0.01671 0.00958 -0.0622 0.2491 1.0000
8.250 1.2053 0.01740 0.01021 -0.0607 0.2219 1.0000
8.500 1.2222 0.01812 0.01090 -0.0592 0.1960 1.0000
8.750 1.2378 0.01891 0.01162 -0.0576 0.1697 1.0000
9.000 1.2523 0.01977 0.01241 -0.0558 0.1437 1.0000
9.250 1.2645 0.02077 0.01330 -0.0538 0.1155 1.0000
9.500 1.2694 0.02226 0.01451 -0.0509 0.0752 1.0000
9.750 1.2657 0.02420 0.01621 -0.0466 0.0458 1.0000
10.000 1.2660 0.02587 0.01790 -0.0430 0.0375 1.0000
10.250 1.2655 0.02762 0.01970 -0.0398 0.0337 1.0000
10.500 1.2660 0.02941 0.02161 -0.0369 0.0316 1.0000
10.750 1.2693 0.03110 0.02344 -0.0346 0.0300 1.0000
11.000 1.2728 0.03288 0.02532 -0.0327 0.0283 1.0000
11.250 1.2747 0.03490 0.02742 -0.0310 0.0269 1.0000
11.500 1.2745 0.03728 0.02985 -0.0293 0.0258 1.0000
11.750 1.2753 0.03991 0.03255 -0.0276 0.0248 1.0000
12.000 1.2824 0.04194 0.03472 -0.0264 0.0243 1.0000
12.250 1.2899 0.04410 0.03703 -0.0252 0.0237 1.0000
12.500 1.2979 0.04637 0.03946 -0.0240 0.0232 1.0000
12.750 1.3056 0.04879 0.04207 -0.0230 0.0227 1.0000
13.000 1.3121 0.05147 0.04495 -0.0220 0.0224 1.0000
13.250 1.3161 0.05442 0.04812 -0.0211 0.0220 1.0000
13.500 1.3169 0.05761 0.05152 -0.0205 0.0217 1.0000
13.750 1.3154 0.06076 0.05484 -0.0203 0.0211 1.0000
14.000 1.3119 0.06422 0.05848 -0.0204 0.0206 1.0000
14.250 1.3058 0.06835 0.06285 -0.0207 0.0206 1.0000
14.500 1.2988 0.07242 0.06710 -0.0214 0.0202 1.0000
14.750 1.2896 0.07704 0.07190 -0.0224 0.0199 1.0000
15.000 1.2758 0.08251 0.07763 -0.0241 0.0200 1.0000
15.250 1.2588 0.08877 0.08416 -0.0265 0.0202 1.0000
15.500 1.2406 0.09559 0.09123 -0.0296 0.0204 1.0000
15.750 1.2194 0.10331 0.09920 -0.0337 0.0205 1.0000
16.000 1.1921 0.11289 0.10906 -0.0395 0.0209 1.0000
16.250 1.1643 0.12341 0.11981 -0.0463 0.0213 1.0000
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Polar data table (+)
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