S3025 9.38% (s3025-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: S3025 9.38% (s3025-il) Reynolds number: 1,000,000 Max Cl/Cd: 130.15 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s3025-il-1000000.txt Download as CSV file: xf-s3025-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.3491 0.08451 0.08297 -0.0327 1.0000 0.0084
-8.000 -0.3543 0.08174 0.08024 -0.0323 1.0000 0.0088
-7.750 -0.3572 0.07880 0.07733 -0.0329 0.9995 0.0087
-7.500 -0.3406 0.07314 0.07167 -0.0411 0.9950 0.0091
-7.250 -0.3166 0.06448 0.06300 -0.0551 0.9883 0.0100
-7.000 -0.2852 0.05583 0.05428 -0.0691 0.9846 0.0101
-6.750 -0.2675 0.03877 0.03688 -0.0855 0.9737 0.0105
-6.500 -0.2478 0.03488 0.03281 -0.0883 0.9627 0.0108
-6.250 -0.2255 0.03299 0.03080 -0.0898 0.9506 0.0112
-6.000 -0.2052 0.03003 0.02762 -0.0906 0.9333 0.0118
-5.750 -0.1867 0.02607 0.02329 -0.0903 0.9119 0.0130
-5.500 -0.1718 0.02126 0.01770 -0.0890 0.8884 0.0144
-5.250 -0.1508 0.01956 0.01582 -0.0884 0.8688 0.0149
-5.000 -0.1278 0.01848 0.01458 -0.0879 0.8507 0.0154
-4.750 -0.1038 0.01762 0.01351 -0.0874 0.8340 0.0166
-4.500 -0.0752 0.01863 0.01430 -0.0867 0.8185 0.0186
-4.250 -0.0553 0.01214 0.00693 -0.0845 0.8057 0.0104
-4.000 -0.0302 0.01098 0.00562 -0.0839 0.7928 0.0100
-3.750 -0.0046 0.01016 0.00465 -0.0833 0.7804 0.0100
-3.500 0.0216 0.00968 0.00404 -0.0828 0.7686 0.0102
-3.250 0.0469 0.00884 0.00306 -0.0822 0.7572 0.0108
-3.000 0.0735 0.00847 0.00264 -0.0820 0.7464 0.0118
-2.750 0.1005 0.00824 0.00233 -0.0817 0.7362 0.0124
-2.250 0.1550 0.00787 0.00181 -0.0812 0.7160 0.0142
-2.000 0.1823 0.00766 0.00154 -0.0810 0.7065 0.0170
-1.500 0.2357 0.00700 0.00121 -0.0806 0.6873 0.1341
-1.250 0.2624 0.00675 0.00115 -0.0805 0.6782 0.2103
-1.000 0.2888 0.00647 0.00111 -0.0803 0.6688 0.3081
-0.750 0.3151 0.00614 0.00109 -0.0802 0.6597 0.4235
-0.500 0.3403 0.00575 0.00110 -0.0798 0.6507 0.5774
-0.250 0.3644 0.00534 0.00112 -0.0790 0.6415 0.7359
0.000 0.3839 0.00494 0.00119 -0.0768 0.6329 0.9025
0.500 0.4650 0.00497 0.00117 -0.0821 0.6136 0.9935
0.750 0.5032 0.00503 0.00115 -0.0844 0.6041 1.0000
1.250 0.5540 0.00517 0.00118 -0.0833 0.5848 1.0000
1.500 0.5795 0.00525 0.00121 -0.0827 0.5751 1.0000
1.750 0.6049 0.00535 0.00124 -0.0822 0.5650 1.0000
2.000 0.6308 0.00543 0.00128 -0.0817 0.5541 1.0000
2.250 0.6567 0.00552 0.00133 -0.0813 0.5429 1.0000
2.500 0.6826 0.00563 0.00139 -0.0809 0.5310 1.0000
2.750 0.7086 0.00575 0.00145 -0.0805 0.5183 1.0000
3.000 0.7346 0.00587 0.00151 -0.0801 0.5048 1.0000
3.250 0.7606 0.00600 0.00159 -0.0798 0.4914 1.0000
3.500 0.7867 0.00614 0.00169 -0.0794 0.4770 1.0000
3.750 0.8127 0.00629 0.00179 -0.0791 0.4617 1.0000
4.000 0.8386 0.00645 0.00189 -0.0787 0.4449 1.0000
4.250 0.8642 0.00664 0.00201 -0.0783 0.4263 1.0000
4.500 0.8896 0.00686 0.00216 -0.0779 0.4070 1.0000
4.750 0.9151 0.00707 0.00231 -0.0776 0.3870 1.0000
5.000 0.9405 0.00730 0.00247 -0.0772 0.3674 1.0000
5.250 0.9651 0.00760 0.00267 -0.0767 0.3419 1.0000
5.500 0.9891 0.00795 0.00289 -0.0761 0.3126 1.0000
5.750 1.0125 0.00835 0.00315 -0.0754 0.2810 1.0000
6.000 1.0365 0.00869 0.00339 -0.0749 0.2566 1.0000
6.250 1.0600 0.00909 0.00367 -0.0743 0.2308 1.0000
6.500 1.0832 0.00950 0.00397 -0.0736 0.2052 1.0000
6.750 1.1064 0.00991 0.00427 -0.0729 0.1817 1.0000
7.000 1.1289 0.01037 0.00461 -0.0722 0.1564 1.0000
7.250 1.1511 0.01085 0.00499 -0.0714 0.1336 1.0000
7.500 1.1727 0.01136 0.00539 -0.0705 0.1115 1.0000
7.750 1.1931 0.01198 0.00586 -0.0695 0.0855 1.0000
8.000 1.2117 0.01273 0.00643 -0.0682 0.0566 1.0000
8.250 1.2255 0.01388 0.00731 -0.0661 0.0201 1.0000
8.500 1.2448 0.01453 0.00793 -0.0648 0.0130 1.0000
8.750 1.2652 0.01506 0.00849 -0.0637 0.0116 1.0000
9.000 1.2842 0.01568 0.00917 -0.0624 0.0104 1.0000
9.250 1.3028 0.01630 0.00987 -0.0610 0.0098 1.0000
9.500 1.3216 0.01686 0.01050 -0.0597 0.0095 1.0000
9.750 1.3393 0.01747 0.01118 -0.0582 0.0093 1.0000
10.000 1.3555 0.01813 0.01191 -0.0565 0.0090 1.0000
10.250 1.3689 0.01881 0.01267 -0.0543 0.0087 1.0000
10.500 1.3801 0.01953 0.01344 -0.0518 0.0083 1.0000
10.750 1.3899 0.02032 0.01431 -0.0492 0.0081 1.0000
11.000 1.3975 0.02128 0.01533 -0.0465 0.0077 1.0000
11.250 1.4022 0.02243 0.01658 -0.0436 0.0075 1.0000
11.500 1.4032 0.02388 0.01815 -0.0404 0.0073 1.0000
11.750 1.3945 0.02610 0.02052 -0.0367 0.0071 1.0000
12.000 1.3940 0.02795 0.02248 -0.0343 0.0070 1.0000
12.250 1.3985 0.02953 0.02415 -0.0326 0.0069 1.0000
12.500 1.4057 0.03098 0.02569 -0.0313 0.0068 1.0000
12.750 1.4076 0.03298 0.02778 -0.0299 0.0067 1.0000
13.000 1.4131 0.03475 0.02965 -0.0290 0.0066 1.0000
13.250 1.4123 0.03723 0.03224 -0.0279 0.0065 1.0000
13.500 1.4158 0.03938 0.03448 -0.0273 0.0064 1.0000
13.750 1.4158 0.04198 0.03719 -0.0268 0.0063 1.0000
14.000 1.4162 0.04465 0.03996 -0.0265 0.0061 1.0000
14.250 1.4168 0.04738 0.04279 -0.0264 0.0060 1.0000
14.500 1.4158 0.05040 0.04591 -0.0266 0.0058 1.0000
14.750 1.4122 0.05387 0.04949 -0.0269 0.0057 1.0000
15.000 1.4110 0.05716 0.05287 -0.0275 0.0056 1.0000
15.250 1.4055 0.06112 0.05695 -0.0282 0.0055 1.0000
15.500 1.3993 0.06536 0.06131 -0.0292 0.0055 1.0000
15.750 1.3958 0.06940 0.06544 -0.0306 0.0054 1.0000
16.000 1.3892 0.07401 0.07016 -0.0321 0.0053 1.0000
16.250 1.3824 0.07882 0.07506 -0.0339 0.0052 1.0000
16.500 1.3749 0.08391 0.08025 -0.0359 0.0052 1.0000
16.750 1.3663 0.08928 0.08575 -0.0381 0.0052 1.0000
17.000 1.3561 0.09504 0.09161 -0.0406 0.0050 1.0000
17.250 1.3455 0.10105 0.09774 -0.0433 0.0050 1.0000
17.500 1.3282 0.10825 0.10508 -0.0464 0.0049 1.0000
17.750 1.3163 0.11488 0.11185 -0.0497 0.0048 1.0000
18.000 1.3032 0.12191 0.11902 -0.0534 0.0048 1.0000
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Polar data table (+)
Polar graphs
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