S3025 9.38% (s3025-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: S3025 9.38% (s3025-il) Reynolds number: 1,000,000 Max Cl/Cd: 114.31 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s3025-il-1000000-n5.txt Download as CSV file: xf-s3025-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.3587 0.09026 0.08865 -0.0321 1.0000 0.0039
-8.750 -0.3601 0.08676 0.08516 -0.0328 1.0000 0.0039
-8.500 -0.3620 0.07960 0.07804 -0.0376 0.9945 0.0044
-8.250 -0.3501 0.07606 0.07450 -0.0417 0.9884 0.0042
-7.500 -0.3090 0.05038 0.04868 -0.0779 0.9403 0.0044
-7.000 -0.3187 0.02545 0.02254 -0.0867 0.8629 0.0043
-6.750 -0.3088 0.02041 0.01679 -0.0860 0.8421 0.0044
-6.500 -0.2914 0.01757 0.01345 -0.0852 0.8245 0.0045
-6.250 -0.2695 0.01604 0.01161 -0.0846 0.8091 0.0046
-6.000 -0.2462 0.01474 0.01002 -0.0840 0.7950 0.0046
-5.750 -0.2221 0.01364 0.00866 -0.0835 0.7817 0.0047
-5.500 -0.1972 0.01278 0.00759 -0.0830 0.7691 0.0047
-5.250 -0.1718 0.01205 0.00667 -0.0826 0.7568 0.0048
-5.000 -0.1460 0.01144 0.00592 -0.0822 0.7454 0.0049
-4.750 -0.1199 0.01091 0.00526 -0.0819 0.7347 0.0050
-4.500 -0.0936 0.01045 0.00468 -0.0815 0.7245 0.0052
-4.250 -0.0671 0.01005 0.00417 -0.0812 0.7143 0.0054
-4.000 -0.0403 0.00968 0.00371 -0.0810 0.7051 0.0057
-3.750 -0.0135 0.00938 0.00332 -0.0807 0.6960 0.0061
-3.500 0.0136 0.00910 0.00297 -0.0805 0.6870 0.0064
-3.250 0.0408 0.00890 0.00269 -0.0804 0.6786 0.0066
-3.000 0.0680 0.00868 0.00241 -0.0802 0.6699 0.0069
-2.750 0.0952 0.00839 0.00204 -0.0800 0.6616 0.0074
-2.250 0.1501 0.00810 0.00166 -0.0797 0.6447 0.0090
-2.000 0.1776 0.00800 0.00149 -0.0796 0.6362 0.0096
-1.750 0.2052 0.00790 0.00133 -0.0794 0.6268 0.0110
-1.500 0.2327 0.00779 0.00121 -0.0793 0.6180 0.0174
-1.250 0.2597 0.00757 0.00111 -0.0792 0.6088 0.0610
-1.000 0.2868 0.00735 0.00104 -0.0791 0.5993 0.1174
-0.750 0.3138 0.00718 0.00099 -0.0790 0.5900 0.1736
-0.500 0.3409 0.00707 0.00097 -0.0789 0.5800 0.2215
-0.250 0.3676 0.00681 0.00096 -0.0788 0.5699 0.3215
0.000 0.3941 0.00657 0.00097 -0.0787 0.5602 0.4244
0.250 0.4208 0.00644 0.00098 -0.0785 0.5503 0.4960
0.500 0.4474 0.00627 0.00100 -0.0784 0.5401 0.5789
0.750 0.4731 0.00606 0.00104 -0.0780 0.5299 0.6830
1.000 0.4975 0.00584 0.00110 -0.0772 0.5196 0.7901
1.250 0.5192 0.00564 0.00117 -0.0756 0.5089 0.8980
1.500 0.5520 0.00565 0.00122 -0.0765 0.4965 0.9687
1.750 0.5901 0.00575 0.00125 -0.0788 0.4828 0.9903
2.000 0.6245 0.00586 0.00129 -0.0803 0.4687 1.0000
2.250 0.6500 0.00600 0.00135 -0.0798 0.4541 1.0000
2.500 0.6756 0.00614 0.00143 -0.0794 0.4386 1.0000
3.000 0.7268 0.00647 0.00160 -0.0785 0.4058 1.0000
3.250 0.7524 0.00665 0.00170 -0.0781 0.3885 1.0000
3.500 0.7781 0.00683 0.00182 -0.0777 0.3707 1.0000
3.750 0.8036 0.00703 0.00194 -0.0774 0.3534 1.0000
4.000 0.8290 0.00726 0.00209 -0.0769 0.3345 1.0000
4.250 0.8543 0.00748 0.00224 -0.0765 0.3158 1.0000
4.500 0.8791 0.00776 0.00242 -0.0761 0.2934 1.0000
4.750 0.9035 0.00808 0.00262 -0.0755 0.2668 1.0000
5.000 0.9280 0.00839 0.00282 -0.0750 0.2439 1.0000
5.250 0.9525 0.00870 0.00305 -0.0745 0.2234 1.0000
5.500 0.9771 0.00900 0.00327 -0.0741 0.2052 1.0000
5.750 1.0003 0.00942 0.00355 -0.0734 0.1771 1.0000
6.000 1.0225 0.00993 0.00388 -0.0726 0.1440 1.0000
6.250 1.0451 0.01040 0.00422 -0.0719 0.1187 1.0000
6.500 1.0679 0.01084 0.00456 -0.0711 0.0987 1.0000
6.750 1.0906 0.01127 0.00490 -0.0704 0.0803 1.0000
7.000 1.1128 0.01175 0.00529 -0.0696 0.0634 1.0000
7.250 1.1338 0.01232 0.00575 -0.0686 0.0432 1.0000
7.500 1.1543 0.01293 0.00626 -0.0676 0.0263 1.0000
7.750 1.1735 0.01362 0.00686 -0.0663 0.0106 1.0000
8.000 1.1958 0.01402 0.00728 -0.0655 0.0092 1.0000
8.250 1.2179 0.01443 0.00771 -0.0647 0.0084 1.0000
8.500 1.2393 0.01487 0.00820 -0.0637 0.0075 1.0000
8.750 1.2610 0.01528 0.00865 -0.0629 0.0073 1.0000
9.000 1.2820 0.01571 0.00913 -0.0619 0.0071 1.0000
9.250 1.3022 0.01618 0.00964 -0.0608 0.0068 1.0000
9.500 1.3218 0.01667 0.01019 -0.0597 0.0066 1.0000
9.750 1.3403 0.01721 0.01079 -0.0584 0.0063 1.0000
10.000 1.3580 0.01776 0.01140 -0.0569 0.0061 1.0000
10.250 1.3735 0.01837 0.01206 -0.0551 0.0059 1.0000
10.500 1.3868 0.01898 0.01273 -0.0530 0.0058 1.0000
10.750 1.3981 0.01970 0.01352 -0.0505 0.0056 1.0000
11.000 1.4085 0.02048 0.01437 -0.0481 0.0055 1.0000
11.250 1.4166 0.02143 0.01541 -0.0455 0.0053 1.0000
11.500 1.4227 0.02252 0.01660 -0.0429 0.0051 1.0000
11.750 1.4292 0.02364 0.01781 -0.0405 0.0050 1.0000
12.000 1.4382 0.02463 0.01888 -0.0386 0.0050 1.0000
12.250 1.4478 0.02565 0.01997 -0.0369 0.0048 1.0000
12.500 1.4547 0.02691 0.02132 -0.0351 0.0048 1.0000
12.750 1.4597 0.02839 0.02289 -0.0334 0.0047 1.0000
13.000 1.4670 0.02977 0.02435 -0.0321 0.0046 1.0000
13.250 1.4695 0.03163 0.02632 -0.0307 0.0045 1.0000
13.500 1.4723 0.03359 0.02838 -0.0295 0.0045 1.0000
13.750 1.4754 0.03561 0.03050 -0.0287 0.0044 1.0000
14.000 1.4772 0.03787 0.03286 -0.0279 0.0043 1.0000
14.250 1.4773 0.04041 0.03550 -0.0274 0.0042 1.0000
14.500 1.4773 0.04307 0.03827 -0.0271 0.0041 1.0000
14.750 1.4793 0.04560 0.04089 -0.0271 0.0040 1.0000
15.000 1.4780 0.04860 0.04399 -0.0272 0.0039 1.0000
15.250 1.4718 0.05236 0.04787 -0.0276 0.0039 1.0000
15.500 1.4662 0.05622 0.05185 -0.0283 0.0039 1.0000
15.750 1.4688 0.05910 0.05480 -0.0289 0.0037 1.0000
16.000 1.4590 0.06384 0.05967 -0.0302 0.0037 1.0000
16.250 1.4555 0.06787 0.06379 -0.0315 0.0036 1.0000
16.500 1.4471 0.07279 0.06884 -0.0332 0.0036 1.0000
16.750 1.4407 0.07755 0.07370 -0.0350 0.0036 1.0000
17.000 1.4307 0.08310 0.07937 -0.0373 0.0035 1.0000
17.250 1.4205 0.08886 0.08525 -0.0399 0.0035 1.0000
17.500 1.4081 0.09514 0.09165 -0.0427 0.0035 1.0000
17.750 1.3950 0.10175 0.09840 -0.0459 0.0035 1.0000
18.000 1.3838 0.10819 0.10494 -0.0491 0.0034 1.0000
18.250 1.3704 0.11512 0.11199 -0.0526 0.0034 1.0000
18.500 1.3554 0.12251 0.11951 -0.0565 0.0034 1.0000
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Polar data table (+)
Polar graphs
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