S3014-095-85 (s3014-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: S3014-095-85 (s3014-il) Reynolds number: 500,000 Max Cl/Cd: 82.62 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s3014-il-500000-n5.txt Download as CSV file: xf-s3014-il-500000-n5.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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.4738 0.08139 0.07924 -0.0244 1.0000 0.0088
-9.000 -0.4824 0.07547 0.07336 -0.0279 1.0000 0.0090
-8.750 -0.4939 0.06953 0.06748 -0.0319 1.0000 0.0089
-8.500 -0.5097 0.06186 0.05985 -0.0398 0.9852 0.0088
-8.250 -0.5432 0.03905 0.03639 -0.0554 0.9328 0.0089
-8.000 -0.5527 0.03155 0.02821 -0.0545 0.9150 0.0091
-7.750 -0.5422 0.02817 0.02435 -0.0535 0.9043 0.0095
-7.500 -0.5236 0.02660 0.02242 -0.0526 0.8962 0.0099
-7.250 -0.5116 0.02303 0.01835 -0.0514 0.8878 0.0103
-7.000 -0.4919 0.02117 0.01622 -0.0506 0.8808 0.0106
-6.750 -0.4699 0.01993 0.01479 -0.0500 0.8741 0.0109
-6.500 -0.4467 0.01882 0.01349 -0.0494 0.8680 0.0112
-6.250 -0.4228 0.01781 0.01230 -0.0489 0.8616 0.0115
-6.000 -0.3985 0.01686 0.01116 -0.0483 0.8558 0.0118
-5.750 -0.3735 0.01595 0.01008 -0.0478 0.8494 0.0121
-5.250 -0.3226 0.01448 0.00834 -0.0469 0.8376 0.0130
-5.000 -0.2968 0.01386 0.00759 -0.0465 0.8317 0.0135
-4.750 -0.2710 0.01316 0.00678 -0.0460 0.8258 0.0138
-4.500 -0.2451 0.01255 0.00606 -0.0456 0.8196 0.0141
-4.250 -0.2190 0.01204 0.00546 -0.0452 0.8140 0.0144
-4.000 -0.1924 0.01160 0.00495 -0.0448 0.8074 0.0147
-3.750 -0.1659 0.01124 0.00451 -0.0445 0.8013 0.0149
-3.500 -0.1399 0.01065 0.00384 -0.0441 0.7946 0.0156
-3.250 -0.1134 0.01027 0.00337 -0.0437 0.7879 0.0162
-3.000 -0.0863 0.00998 0.00302 -0.0435 0.7809 0.0169
-2.750 -0.0592 0.00974 0.00273 -0.0432 0.7738 0.0180
-2.500 -0.0317 0.00954 0.00248 -0.0431 0.7663 0.0192
-2.250 -0.0044 0.00937 0.00223 -0.0428 0.7588 0.0201
-2.000 0.0233 0.00922 0.00203 -0.0427 0.7505 0.0213
-1.750 0.0507 0.00905 0.00185 -0.0424 0.7422 0.0288
-1.500 0.0772 0.00871 0.00169 -0.0422 0.7323 0.0812
-1.250 0.1036 0.00837 0.00156 -0.0420 0.7214 0.1503
-1.000 0.1302 0.00812 0.00146 -0.0418 0.7096 0.2105
-0.750 0.1564 0.00782 0.00138 -0.0415 0.6970 0.2922
-0.500 0.1807 0.00729 0.00134 -0.0411 0.6836 0.4503
-0.250 0.2031 0.00672 0.00132 -0.0401 0.6692 0.6272
0.000 0.2267 0.00644 0.00132 -0.0391 0.6547 0.7261
0.250 0.2502 0.00621 0.00133 -0.0378 0.6401 0.8147
0.500 0.2810 0.00606 0.00136 -0.0380 0.6245 0.9104
0.750 0.3316 0.00614 0.00137 -0.0428 0.6059 0.9591
1.000 0.3704 0.00625 0.00138 -0.0451 0.5877 0.9805
1.250 0.4074 0.00637 0.00139 -0.0471 0.5684 0.9932
1.500 0.4447 0.00649 0.00141 -0.0492 0.5483 1.0000
1.750 0.4699 0.00663 0.00145 -0.0487 0.5283 1.0000
2.000 0.4951 0.00678 0.00150 -0.0482 0.5083 1.0000
2.250 0.5203 0.00695 0.00157 -0.0476 0.4866 1.0000
2.500 0.5453 0.00714 0.00165 -0.0471 0.4637 1.0000
2.750 0.5704 0.00734 0.00175 -0.0466 0.4404 1.0000
3.000 0.5952 0.00756 0.00186 -0.0460 0.4164 1.0000
3.250 0.6200 0.00779 0.00199 -0.0455 0.3920 1.0000
3.500 0.6448 0.00803 0.00213 -0.0450 0.3681 1.0000
3.750 0.6694 0.00829 0.00229 -0.0444 0.3448 1.0000
4.000 0.6940 0.00856 0.00246 -0.0439 0.3222 1.0000
4.250 0.7186 0.00882 0.00264 -0.0433 0.3016 1.0000
4.500 0.7432 0.00909 0.00283 -0.0428 0.2817 1.0000
5.000 0.7922 0.00965 0.00327 -0.0417 0.2470 1.0000
5.250 0.8169 0.00992 0.00349 -0.0412 0.2320 1.0000
5.500 0.8414 0.01020 0.00372 -0.0407 0.2168 1.0000
5.750 0.8659 0.01048 0.00397 -0.0402 0.2038 1.0000
6.000 0.8903 0.01078 0.00425 -0.0397 0.1903 1.0000
6.250 0.9144 0.01110 0.00452 -0.0392 0.1756 1.0000
6.500 0.9379 0.01148 0.00483 -0.0386 0.1566 1.0000
6.750 0.9609 0.01192 0.00517 -0.0379 0.1368 1.0000
7.000 0.9841 0.01232 0.00551 -0.0373 0.1208 1.0000
7.250 1.0070 0.01274 0.00590 -0.0366 0.1062 1.0000
7.500 1.0288 0.01327 0.00633 -0.0359 0.0878 1.0000
7.750 1.0506 0.01379 0.00677 -0.0351 0.0721 1.0000
8.000 1.0722 0.01431 0.00724 -0.0343 0.0587 1.0000
8.250 1.0930 0.01490 0.00776 -0.0334 0.0448 1.0000
8.500 1.1117 0.01568 0.00845 -0.0323 0.0276 1.0000
8.750 1.1288 0.01658 0.00925 -0.0309 0.0119 1.0000
9.000 1.1471 0.01734 0.01001 -0.0296 0.0075 1.0000
9.250 1.1664 0.01797 0.01070 -0.0285 0.0064 1.0000
9.500 1.1846 0.01866 0.01145 -0.0272 0.0056 1.0000
9.750 1.2014 0.01942 0.01231 -0.0258 0.0049 1.0000
10.000 1.2186 0.02011 0.01309 -0.0244 0.0047 1.0000
10.250 1.2346 0.02083 0.01392 -0.0229 0.0045 1.0000
10.500 1.2481 0.02161 0.01481 -0.0211 0.0044 1.0000
10.750 1.2587 0.02242 0.01571 -0.0188 0.0042 1.0000
11.000 1.2680 0.02333 0.01672 -0.0165 0.0041 1.0000
11.250 1.2763 0.02435 0.01784 -0.0143 0.0040 1.0000
11.500 1.2835 0.02550 0.01910 -0.0122 0.0039 1.0000
11.750 1.2900 0.02676 0.02047 -0.0103 0.0037 1.0000
12.000 1.2958 0.02813 0.02194 -0.0086 0.0037 1.0000
12.250 1.2990 0.02978 0.02371 -0.0069 0.0035 1.0000
12.500 1.3021 0.03153 0.02557 -0.0054 0.0035 1.0000
12.750 1.3024 0.03362 0.02778 -0.0041 0.0034 1.0000
13.000 1.3031 0.03579 0.03009 -0.0032 0.0033 1.0000
13.250 1.3008 0.03839 0.03281 -0.0024 0.0032 1.0000
13.500 1.2980 0.04121 0.03577 -0.0021 0.0032 1.0000
13.750 1.2914 0.04463 0.03932 -0.0021 0.0031 1.0000
14.000 1.2833 0.04848 0.04330 -0.0026 0.0031 1.0000
14.250 1.2751 0.05257 0.04754 -0.0035 0.0031 1.0000
14.500 1.2697 0.05651 0.05161 -0.0046 0.0031 1.0000
14.750 1.2598 0.06132 0.05655 -0.0063 0.0030 1.0000
15.000 1.2500 0.06638 0.06176 -0.0083 0.0030 1.0000
15.250 1.2352 0.07246 0.06798 -0.0109 0.0030 1.0000
15.500 1.2308 0.07714 0.07277 -0.0131 0.0031 1.0000
15.750 1.2128 0.08423 0.08001 -0.0164 0.0030 1.0000
16.000 1.2054 0.08972 0.08562 -0.0191 0.0030 1.0000
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Polar data table (+)
Polar graphs
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