S3025 9.38% (s3025-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: S3025 9.38% (s3025-il) Reynolds number: 500,000 Max Cl/Cd: 109.72 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s3025-il-500000.txt Download as CSV file: xf-s3025-il-500000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.3450 0.08359 0.08147 -0.0336 1.0000 0.0157
-7.750 -0.3508 0.08105 0.07897 -0.0331 1.0000 0.0157
-7.500 -0.3622 0.07900 0.07699 -0.0313 1.0000 0.0160
-7.250 -0.3727 0.07667 0.07472 -0.0307 0.9990 0.0162
-7.000 -0.3445 0.06997 0.06800 -0.0425 0.9937 0.0169
-6.750 -0.3012 0.05789 0.05577 -0.0638 0.9862 0.0186
-6.500 -0.2813 0.04724 0.04490 -0.0747 0.9784 0.0191
-6.250 -0.2542 0.04522 0.04286 -0.0782 0.9746 0.0199
-6.000 -0.2246 0.04151 0.03902 -0.0827 0.9694 0.0212
-5.750 -0.1952 0.03633 0.03354 -0.0869 0.9611 0.0233
-5.500 -0.1728 0.02996 0.02660 -0.0894 0.9490 0.0261
-5.250 -0.1471 0.02844 0.02505 -0.0904 0.9385 0.0274
-5.000 -0.1213 0.02639 0.02279 -0.0909 0.9259 0.0295
-4.750 -0.0904 0.02669 0.02264 -0.0902 0.9116 0.0330
-4.500 -0.0738 0.02133 0.01696 -0.0904 0.8954 0.0355
-4.250 -0.0485 0.01534 0.00997 -0.0877 0.8805 0.0176
-4.000 -0.0235 0.01332 0.00759 -0.0867 0.8656 0.0162
-3.750 0.0021 0.01212 0.00615 -0.0859 0.8511 0.0159
-3.500 0.0278 0.01135 0.00522 -0.0852 0.8372 0.0164
-3.250 0.0536 0.01076 0.00450 -0.0845 0.8239 0.0171
-3.000 0.0797 0.01030 0.00392 -0.0840 0.8115 0.0180
-2.750 0.1056 0.00983 0.00333 -0.0834 0.7995 0.0196
-2.500 0.1320 0.00946 0.00289 -0.0830 0.7876 0.0218
-2.250 0.1588 0.00921 0.00254 -0.0826 0.7764 0.0244
-2.000 0.1849 0.00866 0.00212 -0.0821 0.7660 0.0726
-1.750 0.2104 0.00818 0.00197 -0.0819 0.7558 0.1848
-1.500 0.2361 0.00777 0.00190 -0.0816 0.7452 0.3009
-1.250 0.2610 0.00730 0.00186 -0.0813 0.7353 0.4503
-0.750 0.3018 0.00616 0.00191 -0.0778 0.7159 0.8495
-0.500 0.3492 0.00605 0.00188 -0.0813 0.7064 0.9772
0.000 0.4252 0.00614 0.00173 -0.0857 0.6863 1.0000
0.250 0.4501 0.00622 0.00171 -0.0850 0.6766 1.0000
0.750 0.5003 0.00637 0.00170 -0.0837 0.6571 1.0000
1.000 0.5256 0.00646 0.00171 -0.0832 0.6478 1.0000
1.250 0.5510 0.00656 0.00173 -0.0826 0.6384 1.0000
1.500 0.5767 0.00663 0.00176 -0.0821 0.6283 1.0000
1.750 0.6024 0.00672 0.00180 -0.0816 0.6186 1.0000
2.250 0.6540 0.00692 0.00189 -0.0807 0.5981 1.0000
2.500 0.6800 0.00702 0.00196 -0.0803 0.5875 1.0000
2.750 0.7059 0.00713 0.00203 -0.0798 0.5765 1.0000
3.000 0.7316 0.00726 0.00210 -0.0794 0.5648 1.0000
3.250 0.7575 0.00737 0.00218 -0.0790 0.5523 1.0000
3.500 0.7834 0.00750 0.00229 -0.0786 0.5391 1.0000
3.750 0.8092 0.00763 0.00239 -0.0782 0.5257 1.0000
4.000 0.8349 0.00778 0.00251 -0.0777 0.5115 1.0000
4.250 0.8604 0.00794 0.00263 -0.0773 0.4965 1.0000
4.500 0.8857 0.00812 0.00278 -0.0768 0.4805 1.0000
4.750 0.9108 0.00833 0.00294 -0.0763 0.4630 1.0000
5.000 0.9359 0.00853 0.00311 -0.0759 0.4438 1.0000
5.250 0.9604 0.00878 0.00330 -0.0753 0.4234 1.0000
5.500 0.9848 0.00905 0.00352 -0.0747 0.4034 1.0000
5.750 1.0091 0.00933 0.00375 -0.0741 0.3817 1.0000
6.000 1.0325 0.00968 0.00401 -0.0735 0.3558 1.0000
6.250 1.0546 0.01014 0.00433 -0.0726 0.3221 1.0000
6.500 1.0765 0.01062 0.00467 -0.0717 0.2902 1.0000
6.750 1.0992 0.01104 0.00501 -0.0710 0.2659 1.0000
7.000 1.1215 0.01149 0.00537 -0.0702 0.2410 1.0000
7.250 1.1427 0.01202 0.00579 -0.0692 0.2122 1.0000
7.500 1.1639 0.01255 0.00622 -0.0683 0.1870 1.0000
7.750 1.1844 0.01313 0.00669 -0.0673 0.1611 1.0000
8.000 1.2040 0.01376 0.00720 -0.0662 0.1358 1.0000
8.250 1.2227 0.01446 0.00778 -0.0649 0.1100 1.0000
8.500 1.2404 0.01522 0.00841 -0.0635 0.0841 1.0000
8.750 1.2535 0.01633 0.00927 -0.0615 0.0486 1.0000
9.000 1.2632 0.01766 0.01040 -0.0589 0.0221 1.0000
9.250 1.2783 0.01850 0.01126 -0.0570 0.0178 1.0000
9.500 1.2939 0.01925 0.01209 -0.0552 0.0161 1.0000
9.750 1.3064 0.02005 0.01297 -0.0530 0.0151 1.0000
10.000 1.3142 0.02106 0.01407 -0.0500 0.0142 1.0000
10.250 1.3190 0.02225 0.01538 -0.0468 0.0136 1.0000
10.500 1.3275 0.02325 0.01647 -0.0442 0.0133 1.0000
10.750 1.3341 0.02440 0.01773 -0.0417 0.0131 1.0000
11.000 1.3397 0.02567 0.01911 -0.0393 0.0128 1.0000
11.250 1.3438 0.02713 0.02068 -0.0369 0.0125 1.0000
11.500 1.3480 0.02866 0.02231 -0.0349 0.0122 1.0000
11.750 1.3510 0.03040 0.02416 -0.0331 0.0118 1.0000
12.000 1.3539 0.03225 0.02612 -0.0315 0.0115 1.0000
12.250 1.3549 0.03438 0.02835 -0.0300 0.0112 1.0000
12.500 1.3559 0.03663 0.03069 -0.0289 0.0109 1.0000
12.750 1.3551 0.03918 0.03335 -0.0279 0.0107 1.0000
13.000 1.3532 0.04196 0.03623 -0.0270 0.0105 1.0000
13.250 1.3505 0.04497 0.03936 -0.0262 0.0103 1.0000
13.500 1.3484 0.04805 0.04256 -0.0255 0.0102 1.0000
13.750 1.3441 0.05161 0.04626 -0.0246 0.0100 1.0000
14.000 1.3427 0.05489 0.04969 -0.0242 0.0099 1.0000
14.250 1.3426 0.05809 0.05303 -0.0239 0.0099 1.0000
14.500 1.3405 0.06141 0.05651 -0.0245 0.0098 1.0000
14.750 1.3372 0.06510 0.06037 -0.0251 0.0097 1.0000
15.000 1.3334 0.06894 0.06437 -0.0261 0.0095 1.0000
15.250 1.3282 0.07318 0.06877 -0.0273 0.0094 1.0000
15.500 1.3206 0.07800 0.07378 -0.0286 0.0095 1.0000
15.750 1.3139 0.08277 0.07871 -0.0306 0.0092 1.0000
16.000 1.3051 0.08811 0.08422 -0.0329 0.0091 1.0000
16.250 1.2952 0.09388 0.09016 -0.0356 0.0090 1.0000
16.500 1.2839 0.10009 0.09654 -0.0386 0.0089 1.0000
16.750 1.2708 0.10688 0.10350 -0.0420 0.0090 1.0000
17.000 1.2574 0.11400 0.11079 -0.0459 0.0089 1.0000
17.250 1.2423 0.12176 0.11872 -0.0503 0.0089 1.0000
17.500 1.2274 0.12975 0.12688 -0.0552 0.0089 1.0000
17.750 1.2114 0.13829 0.13558 -0.0604 0.0090 1.0000
18.000 1.1941 0.14753 0.14497 -0.0662 0.0091 1.0000
18.250 1.1763 0.15734 0.15494 -0.0725 0.0092 1.0000
18.500 1.1576 0.16781 0.16553 -0.0793 0.0093 1.0000
18.750 1.1358 0.17979 0.17763 -0.0869 0.0095 1.0000
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Polar data table (+)
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