S3025 9.38% (s3025-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: S3025 9.38% (s3025-il) Reynolds number: 200,000 Max Cl/Cd: 77.1 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s3025-il-200000-n5.txt Download as CSV file: xf-s3025-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.3482 0.10148 0.09789 -0.0339 1.0000 0.0247
-9.000 -0.3473 0.09822 0.09468 -0.0354 1.0000 0.0248
-8.750 -0.3483 0.09491 0.09143 -0.0371 1.0000 0.0250
-8.500 -0.3497 0.09100 0.08758 -0.0369 1.0000 0.0255
-8.250 -0.3502 0.08803 0.08467 -0.0372 1.0000 0.0256
-8.000 -0.3460 0.08584 0.08252 -0.0356 1.0000 0.0262
-7.750 -0.3489 0.08336 0.08010 -0.0351 1.0000 0.0265
-7.500 -0.3562 0.08110 0.07792 -0.0341 1.0000 0.0267
-6.500 -0.3000 0.05634 0.05303 -0.0642 0.9733 0.0201
-6.250 -0.2762 0.04450 0.04077 -0.0734 0.9613 0.0140
-6.000 -0.2546 0.03958 0.03561 -0.0770 0.9501 0.0136
-5.750 -0.2311 0.03436 0.02999 -0.0800 0.9391 0.0132
-5.500 -0.2050 0.02973 0.02487 -0.0821 0.9294 0.0129
-5.250 -0.1791 0.02569 0.02025 -0.0831 0.9183 0.0126
-5.000 -0.1520 0.02261 0.01660 -0.0835 0.9074 0.0126
-4.750 -0.1229 0.02026 0.01373 -0.0839 0.8971 0.0127
-4.500 -0.0927 0.01842 0.01148 -0.0842 0.8869 0.0130
-4.250 -0.0637 0.01712 0.00986 -0.0843 0.8753 0.0136
-4.000 -0.0356 0.01600 0.00854 -0.0842 0.8631 0.0149
-3.750 -0.0079 0.01518 0.00761 -0.0841 0.8511 0.0160
-3.500 0.0194 0.01437 0.00664 -0.0838 0.8390 0.0167
-3.250 0.0464 0.01371 0.00584 -0.0835 0.8272 0.0175
-3.000 0.0732 0.01318 0.00516 -0.0830 0.8153 0.0187
-2.750 0.0997 0.01271 0.00455 -0.0826 0.8034 0.0204
-2.500 0.1265 0.01239 0.00412 -0.0823 0.7920 0.0250
-2.250 0.1530 0.01193 0.00367 -0.0819 0.7813 0.0405
-2.000 0.1791 0.01144 0.00337 -0.0815 0.7709 0.1036
-1.750 0.2039 0.01085 0.00323 -0.0813 0.7602 0.2304
-1.250 0.2524 0.00989 0.00306 -0.0801 0.7407 0.4994
-1.000 0.2739 0.00938 0.00304 -0.0786 0.7307 0.6572
-0.750 0.2964 0.00894 0.00304 -0.0765 0.7216 0.8358
-0.500 0.3507 0.00882 0.00288 -0.0815 0.7123 0.9748
-0.250 0.3892 0.00885 0.00275 -0.0838 0.7018 1.0000
0.000 0.4141 0.00894 0.00270 -0.0831 0.6919 1.0000
0.250 0.4393 0.00904 0.00266 -0.0825 0.6823 1.0000
0.500 0.4644 0.00913 0.00265 -0.0819 0.6718 1.0000
0.750 0.4898 0.00923 0.00264 -0.0813 0.6616 1.0000
1.000 0.5152 0.00934 0.00264 -0.0808 0.6518 1.0000
1.250 0.5407 0.00945 0.00267 -0.0802 0.6411 1.0000
1.500 0.5663 0.00956 0.00271 -0.0797 0.6305 1.0000
1.750 0.5919 0.00968 0.00276 -0.0792 0.6202 1.0000
2.000 0.6175 0.00981 0.00281 -0.0787 0.6096 1.0000
2.250 0.6431 0.00993 0.00289 -0.0782 0.5984 1.0000
2.500 0.6688 0.01006 0.00298 -0.0777 0.5872 1.0000
2.750 0.6943 0.01020 0.00308 -0.0772 0.5760 1.0000
3.000 0.7198 0.01036 0.00318 -0.0767 0.5643 1.0000
3.250 0.7452 0.01051 0.00329 -0.0762 0.5519 1.0000
3.500 0.7705 0.01067 0.00345 -0.0757 0.5387 1.0000
3.750 0.7957 0.01084 0.00359 -0.0752 0.5247 1.0000
4.000 0.8206 0.01102 0.00374 -0.0746 0.5099 1.0000
4.250 0.8453 0.01123 0.00393 -0.0740 0.4942 1.0000
4.500 0.8698 0.01144 0.00412 -0.0734 0.4774 1.0000
4.750 0.8942 0.01167 0.00433 -0.0727 0.4599 1.0000
5.000 0.9182 0.01193 0.00455 -0.0721 0.4413 1.0000
5.250 0.9418 0.01222 0.00482 -0.0713 0.4222 1.0000
5.500 0.9653 0.01252 0.00510 -0.0706 0.4022 1.0000
5.750 0.9881 0.01287 0.00540 -0.0697 0.3806 1.0000
6.000 1.0106 0.01324 0.00573 -0.0689 0.3586 1.0000
6.250 1.0326 0.01365 0.00612 -0.0680 0.3366 1.0000
6.500 1.0545 0.01408 0.00651 -0.0671 0.3151 1.0000
6.750 1.0758 0.01455 0.00694 -0.0661 0.2941 1.0000
7.000 1.0965 0.01506 0.00741 -0.0650 0.2701 1.0000
7.250 1.1157 0.01567 0.00794 -0.0638 0.2419 1.0000
7.500 1.1334 0.01639 0.00851 -0.0624 0.2092 1.0000
7.750 1.1511 0.01712 0.00912 -0.0611 0.1802 1.0000
8.000 1.1697 0.01777 0.00973 -0.0598 0.1580 1.0000
8.250 1.1866 0.01854 0.01041 -0.0584 0.1345 1.0000
8.500 1.2033 0.01930 0.01115 -0.0570 0.1153 1.0000
8.750 1.2182 0.02018 0.01194 -0.0553 0.0925 1.0000
9.000 1.2317 0.02114 0.01281 -0.0535 0.0715 1.0000
9.250 1.2426 0.02223 0.01379 -0.0513 0.0505 1.0000
9.500 1.2502 0.02339 0.01487 -0.0486 0.0343 1.0000
9.750 1.2576 0.02457 0.01604 -0.0459 0.0246 1.0000
10.000 1.2653 0.02574 0.01727 -0.0435 0.0204 1.0000
10.250 1.2736 0.02690 0.01855 -0.0412 0.0184 1.0000
10.500 1.2814 0.02812 0.01989 -0.0391 0.0172 1.0000
10.750 1.2872 0.02953 0.02142 -0.0369 0.0162 1.0000
11.000 1.2915 0.03111 0.02311 -0.0350 0.0155 1.0000
11.250 1.2936 0.03294 0.02507 -0.0331 0.0149 1.0000
11.500 1.2970 0.03476 0.02704 -0.0315 0.0145 1.0000
11.750 1.3000 0.03672 0.02915 -0.0302 0.0139 1.0000
12.000 1.3014 0.03891 0.03150 -0.0291 0.0135 1.0000
12.250 1.3029 0.04122 0.03395 -0.0283 0.0129 1.0000
12.500 1.3022 0.04387 0.03675 -0.0276 0.0126 1.0000
12.750 1.3011 0.04667 0.03969 -0.0272 0.0124 1.0000
13.000 1.2995 0.04964 0.04280 -0.0270 0.0121 1.0000
13.250 1.2969 0.05283 0.04612 -0.0269 0.0119 1.0000
13.500 1.2938 0.05620 0.04962 -0.0271 0.0117 1.0000
13.750 1.2899 0.05977 0.05331 -0.0274 0.0115 1.0000
14.000 1.2862 0.06341 0.05709 -0.0279 0.0114 1.0000
14.250 1.2818 0.06727 0.06107 -0.0286 0.0113 1.0000
14.500 1.2767 0.07132 0.06524 -0.0293 0.0111 1.0000
14.750 1.2726 0.07535 0.06939 -0.0300 0.0109 1.0000
15.000 1.2692 0.07941 0.07358 -0.0309 0.0108 1.0000
15.250 1.2657 0.08366 0.07801 -0.0322 0.0108 1.0000
15.500 1.2610 0.08823 0.08276 -0.0338 0.0107 1.0000
15.750 1.2552 0.09319 0.08791 -0.0358 0.0105 1.0000
16.000 1.2488 0.09836 0.09326 -0.0380 0.0104 1.0000
16.250 1.2411 0.10394 0.09903 -0.0405 0.0103 1.0000
16.500 1.2329 0.10978 0.10505 -0.0434 0.0102 1.0000
16.750 1.2233 0.11612 0.11161 -0.0468 0.0101 1.0000
17.000 1.2132 0.12276 0.11843 -0.0505 0.0099 1.0000
17.250 1.2025 0.12968 0.12553 -0.0544 0.0099 1.0000
17.500 1.1908 0.13708 0.13310 -0.0588 0.0099 1.0000
17.750 1.1788 0.14484 0.14103 -0.0636 0.0098 1.0000
18.000 1.1656 0.15324 0.14957 -0.0689 0.0098 1.0000
18.250 1.1514 0.16222 0.15870 -0.0746 0.0099 1.0000
18.500 1.1347 0.17237 0.16900 -0.0810 0.0100 1.0000
18.750 1.1152 0.18417 0.18094 -0.0883 0.0102 1.0000
19.000 1.0871 0.20050 0.19735 -0.0979 0.0105 1.0000
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Polar data table (+)
Polar graphs
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