S3014-095-85 (s3014-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: S3014-095-85 (s3014-il) Reynolds number: 1,000,000 Max Cl/Cd: 106.55 at α=3.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s3014-il-1000000.txt Download as CSV file: xf-s3014-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: S3014-095-85
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
------ -------- --------- --------- -------- -------- --------
-9.750 -0.4471 0.09647 0.09489 -0.0171 1.0000 0.0113
-9.500 -0.4473 0.09177 0.09021 -0.0195 1.0000 0.0118
-6.500 -0.4424 0.02218 0.01819 -0.0497 0.8774 0.0131
-6.250 -0.4202 0.02076 0.01652 -0.0489 0.8715 0.0130
-6.000 -0.3969 0.01925 0.01481 -0.0483 0.8652 0.0129
-5.750 -0.3777 0.01584 0.01097 -0.0471 0.8593 0.0132
-5.500 -0.3543 0.01400 0.00895 -0.0465 0.8537 0.0138
-5.250 -0.3289 0.01306 0.00791 -0.0460 0.8478 0.0141
-5.000 -0.3032 0.01236 0.00711 -0.0456 0.8425 0.0146
-4.750 -0.2769 0.01167 0.00634 -0.0452 0.8366 0.0149
-4.500 -0.2508 0.01107 0.00565 -0.0448 0.8308 0.0152
-4.250 -0.2245 0.01048 0.00499 -0.0444 0.8251 0.0155
-4.000 -0.1979 0.00999 0.00443 -0.0440 0.8190 0.0159
-3.750 -0.1713 0.00960 0.00397 -0.0437 0.8133 0.0166
-3.500 -0.1443 0.00918 0.00350 -0.0434 0.8069 0.0171
-3.250 -0.1174 0.00886 0.00310 -0.0430 0.8008 0.0176
-3.000 -0.0898 0.00861 0.00281 -0.0429 0.7944 0.0180
-2.750 -0.0629 0.00823 0.00233 -0.0425 0.7878 0.0188
-2.500 -0.0354 0.00797 0.00201 -0.0423 0.7810 0.0199
-2.250 -0.0078 0.00778 0.00177 -0.0421 0.7735 0.0214
-2.000 0.0200 0.00762 0.00157 -0.0420 0.7654 0.0238
-1.750 0.0469 0.00731 0.00137 -0.0417 0.7570 0.0621
-1.500 0.0731 0.00682 0.00123 -0.0415 0.7476 0.1603
-1.250 0.0997 0.00652 0.00113 -0.0413 0.7383 0.2362
-1.000 0.1262 0.00623 0.00106 -0.0411 0.7281 0.3157
-0.750 0.1526 0.00591 0.00100 -0.0409 0.7170 0.4109
-0.500 0.1780 0.00552 0.00097 -0.0405 0.7062 0.5365
-0.250 0.2025 0.00515 0.00096 -0.0398 0.6949 0.6623
0.000 0.2244 0.00473 0.00097 -0.0384 0.6830 0.8064
0.250 0.2593 0.00445 0.00104 -0.0394 0.6701 0.9507
0.500 0.3046 0.00453 0.00104 -0.0431 0.6551 0.9752
0.750 0.3436 0.00462 0.00105 -0.0454 0.6394 0.9882
1.000 0.3832 0.00471 0.00106 -0.0480 0.6228 0.9953
1.250 0.4251 0.00480 0.00105 -0.0511 0.6043 0.9999
1.500 0.4511 0.00490 0.00106 -0.0507 0.5866 1.0000
1.750 0.4767 0.00500 0.00109 -0.0502 0.5688 1.0000
2.000 0.5023 0.00512 0.00112 -0.0497 0.5485 1.0000
2.250 0.5278 0.00526 0.00117 -0.0492 0.5277 1.0000
2.500 0.5534 0.00540 0.00123 -0.0488 0.5066 1.0000
2.750 0.5788 0.00557 0.00131 -0.0483 0.4846 1.0000
3.000 0.6043 0.00574 0.00139 -0.0478 0.4607 1.0000
3.250 0.6296 0.00594 0.00148 -0.0473 0.4366 1.0000
3.500 0.6547 0.00616 0.00159 -0.0469 0.4112 1.0000
3.750 0.6798 0.00638 0.00172 -0.0464 0.3860 1.0000
4.000 0.7047 0.00662 0.00186 -0.0459 0.3592 1.0000
4.250 0.7296 0.00687 0.00200 -0.0453 0.3343 1.0000
4.500 0.7544 0.00714 0.00216 -0.0448 0.3103 1.0000
4.750 0.7793 0.00738 0.00234 -0.0443 0.2895 1.0000
5.000 0.8040 0.00765 0.00252 -0.0438 0.2702 1.0000
5.250 0.8288 0.00790 0.00270 -0.0433 0.2516 1.0000
5.500 0.8536 0.00814 0.00289 -0.0428 0.2362 1.0000
5.750 0.8783 0.00840 0.00310 -0.0423 0.2200 1.0000
6.000 0.9027 0.00869 0.00332 -0.0418 0.2031 1.0000
6.250 0.9269 0.00900 0.00355 -0.0412 0.1842 1.0000
6.500 0.9511 0.00931 0.00379 -0.0407 0.1668 1.0000
6.750 0.9744 0.00971 0.00408 -0.0400 0.1455 1.0000
7.000 0.9984 0.01004 0.00435 -0.0395 0.1305 1.0000
7.250 1.0221 0.01039 0.00464 -0.0389 0.1167 1.0000
7.500 1.0457 0.01075 0.00496 -0.0383 0.1034 1.0000
7.750 1.0686 0.01117 0.00530 -0.0376 0.0877 1.0000
8.000 1.0911 0.01163 0.00569 -0.0369 0.0730 1.0000
8.250 1.1126 0.01218 0.00614 -0.0361 0.0567 1.0000
8.500 1.1329 0.01283 0.00667 -0.0351 0.0378 1.0000
8.750 1.1476 0.01404 0.00764 -0.0333 0.0102 1.0000
9.000 1.1676 0.01469 0.00831 -0.0322 0.0073 1.0000
9.250 1.1884 0.01524 0.00893 -0.0312 0.0066 1.0000
9.500 1.2090 0.01577 0.00952 -0.0302 0.0063 1.0000
9.750 1.2288 0.01635 0.01017 -0.0291 0.0059 1.0000
10.000 1.2478 0.01696 0.01084 -0.0279 0.0057 1.0000
10.250 1.2653 0.01766 0.01161 -0.0265 0.0053 1.0000
10.500 1.2811 0.01845 0.01247 -0.0249 0.0051 1.0000
10.750 1.2940 0.01938 0.01349 -0.0230 0.0048 1.0000
11.000 1.3028 0.02036 0.01459 -0.0203 0.0048 1.0000
11.250 1.2987 0.02189 0.01628 -0.0160 0.0045 1.0000
11.500 1.3099 0.02265 0.01710 -0.0140 0.0044 1.0000
11.750 1.3147 0.02386 0.01841 -0.0116 0.0044 1.0000
12.000 1.3205 0.02508 0.01973 -0.0095 0.0043 1.0000
12.250 1.3251 0.02649 0.02123 -0.0075 0.0042 1.0000
12.500 1.3272 0.02815 0.02300 -0.0056 0.0042 1.0000
12.750 1.3296 0.02991 0.02487 -0.0040 0.0040 1.0000
13.000 1.3306 0.03189 0.02695 -0.0027 0.0041 1.0000
13.250 1.3309 0.03407 0.02924 -0.0016 0.0040 1.0000
13.500 1.3266 0.03681 0.03211 -0.0007 0.0041 1.0000
13.750 1.3257 0.03939 0.03480 -0.0002 0.0040 1.0000
14.000 1.3209 0.04254 0.03807 0.0000 0.0039 1.0000
14.250 1.3176 0.04571 0.04137 -0.0002 0.0038 1.0000
14.500 1.3132 0.04916 0.04494 -0.0007 0.0038 1.0000
14.750 1.3069 0.05304 0.04894 -0.0016 0.0038 1.0000
15.000 1.2935 0.05809 0.05414 -0.0029 0.0038 1.0000
15.250 1.2939 0.06149 0.05762 -0.0044 0.0037 1.0000
15.500 1.2826 0.06677 0.06303 -0.0064 0.0037 1.0000
15.750 1.2717 0.07219 0.06858 -0.0087 0.0037 1.0000
16.000 1.2606 0.07786 0.07438 -0.0113 0.0037 1.0000
16.250 1.2491 0.08382 0.08046 -0.0141 0.0037 1.0000
16.500 1.2345 0.09049 0.08727 -0.0173 0.0037 1.0000
16.750 1.2246 0.09656 0.09345 -0.0204 0.0037 1.0000
17.000 1.2092 0.10376 0.10078 -0.0241 0.0037 1.0000
17.250 1.1949 0.11096 0.10810 -0.0279 0.0037 1.0000
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Polar data table (+)
Polar graphs
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