S5010 (s5010-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: S5010 (s5010-il) Reynolds number: 200,000 Max Cl/Cd: 62.22 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s5010-il-200000-n5.txt Download as CSV file: xf-s5010-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: S5010
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.5519 0.08521 0.08221 0.0096 1.0000 0.0136
-8.250 -0.5569 0.07970 0.07677 0.0055 1.0000 0.0132
-8.000 -0.5664 0.07360 0.07073 -0.0002 1.0000 0.0131
-7.750 -0.5719 0.06607 0.06314 -0.0069 0.9514 0.0129
-7.500 -0.5754 0.05766 0.05443 -0.0119 0.8919 0.0125
-7.250 -0.5732 0.05264 0.04916 -0.0129 0.8671 0.0128
-7.000 -0.5666 0.04811 0.04433 -0.0133 0.8492 0.0134
-6.750 -0.5588 0.04289 0.03870 -0.0132 0.8346 0.0140
-6.500 -0.5488 0.03755 0.03283 -0.0125 0.8221 0.0146
-6.250 -0.5355 0.03284 0.02752 -0.0114 0.8110 0.0148
-6.000 -0.5184 0.02893 0.02297 -0.0101 0.8004 0.0152
-5.750 -0.4977 0.02600 0.01943 -0.0089 0.7899 0.0157
-5.500 -0.4751 0.02385 0.01675 -0.0079 0.7802 0.0163
-5.250 -0.4522 0.02225 0.01498 -0.0073 0.7708 0.0175
-5.000 -0.4271 0.02137 0.01392 -0.0069 0.7609 0.0190
-4.750 -0.4017 0.02015 0.01242 -0.0063 0.7521 0.0203
-4.500 -0.3758 0.01893 0.01095 -0.0056 0.7432 0.0213
-4.250 -0.3494 0.01801 0.00982 -0.0050 0.7344 0.0221
-4.000 -0.3248 0.01686 0.00860 -0.0044 0.7264 0.0243
-3.750 -0.2986 0.01617 0.00783 -0.0040 0.7173 0.0260
-3.500 -0.2727 0.01547 0.00702 -0.0034 0.7092 0.0273
-3.250 -0.2465 0.01487 0.00631 -0.0029 0.7007 0.0287
-3.000 -0.2202 0.01436 0.00571 -0.0025 0.6923 0.0307
-2.750 -0.1941 0.01385 0.00513 -0.0020 0.6843 0.0338
-2.500 -0.1671 0.01347 0.00466 -0.0017 0.6756 0.0366
-2.250 -0.1402 0.01316 0.00422 -0.0013 0.6679 0.0408
-2.000 -0.1132 0.01277 0.00385 -0.0010 0.6590 0.0546
-1.750 -0.0875 0.01219 0.00353 -0.0006 0.6511 0.1236
-1.500 -0.0630 0.01142 0.00328 -0.0003 0.6426 0.2635
-1.250 -0.0401 0.01061 0.00313 0.0004 0.6345 0.4426
-1.000 -0.0186 0.00992 0.00303 0.0018 0.6265 0.6059
-0.750 0.0056 0.00915 0.00309 0.0037 0.6181 0.8397
-0.500 0.0737 0.00916 0.00310 -0.0036 0.6078 0.9603
-0.250 0.1209 0.00922 0.00299 -0.0073 0.5977 0.9871
0.000 0.1648 0.00921 0.00284 -0.0107 0.5873 0.9997
0.250 0.1906 0.00924 0.00274 -0.0102 0.5783 1.0000
0.500 0.2160 0.00928 0.00267 -0.0097 0.5687 1.0000
0.750 0.2417 0.00932 0.00262 -0.0093 0.5589 1.0000
1.000 0.2674 0.00938 0.00258 -0.0088 0.5496 1.0000
1.250 0.2932 0.00945 0.00255 -0.0083 0.5396 1.0000
1.500 0.3193 0.00952 0.00256 -0.0079 0.5292 1.0000
1.750 0.3453 0.00960 0.00256 -0.0075 0.5192 1.0000
2.000 0.3712 0.00970 0.00258 -0.0071 0.5090 1.0000
2.250 0.3974 0.00979 0.00263 -0.0067 0.4977 1.0000
2.500 0.4236 0.00990 0.00268 -0.0064 0.4866 1.0000
2.750 0.4498 0.01002 0.00274 -0.0060 0.4753 1.0000
3.000 0.4759 0.01015 0.00283 -0.0056 0.4639 1.0000
3.250 0.5020 0.01028 0.00292 -0.0053 0.4518 1.0000
3.500 0.5283 0.01043 0.00303 -0.0050 0.4393 1.0000
3.750 0.5544 0.01058 0.00315 -0.0046 0.4262 1.0000
4.000 0.5805 0.01075 0.00330 -0.0043 0.4129 1.0000
4.250 0.6066 0.01094 0.00346 -0.0040 0.3990 1.0000
4.500 0.6326 0.01114 0.00363 -0.0037 0.3844 1.0000
4.750 0.6586 0.01136 0.00383 -0.0034 0.3695 1.0000
5.000 0.6845 0.01160 0.00404 -0.0031 0.3542 1.0000
5.250 0.7103 0.01186 0.00427 -0.0029 0.3389 1.0000
5.500 0.7359 0.01214 0.00453 -0.0026 0.3231 1.0000
5.750 0.7615 0.01244 0.00482 -0.0023 0.3073 1.0000
6.000 0.7870 0.01275 0.00513 -0.0021 0.2913 1.0000
6.250 0.8123 0.01309 0.00546 -0.0018 0.2754 1.0000
6.500 0.8374 0.01346 0.00582 -0.0016 0.2593 1.0000
6.750 0.8623 0.01386 0.00622 -0.0013 0.2436 1.0000
7.000 0.8870 0.01428 0.00664 -0.0011 0.2280 1.0000
7.250 0.9114 0.01473 0.00709 -0.0008 0.2132 1.0000
7.500 0.9356 0.01521 0.00756 -0.0005 0.1982 1.0000
7.750 0.9594 0.01572 0.00807 -0.0002 0.1836 1.0000
8.000 0.9829 0.01625 0.00863 0.0001 0.1698 1.0000
8.250 1.0061 0.01681 0.00921 0.0004 0.1568 1.0000
8.500 1.0289 0.01739 0.00982 0.0008 0.1444 1.0000
8.750 1.0511 0.01801 0.01048 0.0012 0.1322 1.0000
9.000 1.0728 0.01868 0.01117 0.0016 0.1208 1.0000
9.250 1.0937 0.01939 0.01194 0.0021 0.1101 1.0000
9.500 1.1136 0.02018 0.01275 0.0026 0.1003 1.0000
9.750 1.1334 0.02095 0.01358 0.0032 0.0910 1.0000
10.000 1.1521 0.02177 0.01447 0.0039 0.0827 1.0000
10.250 1.1687 0.02274 0.01547 0.0046 0.0751 1.0000
10.500 1.1854 0.02364 0.01647 0.0054 0.0679 1.0000
10.750 1.1995 0.02470 0.01760 0.0063 0.0611 1.0000
11.000 1.2111 0.02587 0.01880 0.0073 0.0539 1.0000
11.250 1.2217 0.02699 0.02001 0.0084 0.0476 1.0000
11.500 1.2240 0.02852 0.02153 0.0098 0.0421 1.0000
11.750 1.2304 0.02996 0.02308 0.0107 0.0371 1.0000
12.000 1.2328 0.03189 0.02506 0.0113 0.0335 1.0000
12.250 1.2373 0.03377 0.02707 0.0117 0.0303 1.0000
12.500 1.2397 0.03596 0.02935 0.0118 0.0271 1.0000
12.750 1.2386 0.03862 0.03206 0.0117 0.0245 1.0000
13.000 1.2397 0.04117 0.03474 0.0114 0.0211 1.0000
13.250 1.2365 0.04430 0.03794 0.0108 0.0190 1.0000
13.500 1.2320 0.04770 0.04146 0.0100 0.0172 1.0000
13.750 1.2278 0.05121 0.04513 0.0089 0.0153 1.0000
14.000 1.2202 0.05530 0.04931 0.0075 0.0140 1.0000
14.250 1.2096 0.05995 0.05405 0.0057 0.0132 1.0000
14.500 1.2015 0.06442 0.05868 0.0039 0.0126 1.0000
14.750 1.1912 0.06941 0.06384 0.0017 0.0119 1.0000
15.000 1.1801 0.07481 0.06938 -0.0008 0.0115 1.0000
15.250 1.1685 0.08050 0.07521 -0.0036 0.0111 1.0000
15.500 1.1551 0.08676 0.08161 -0.0067 0.0106 1.0000
15.750 1.1421 0.09311 0.08810 -0.0099 0.0106 1.0000
16.000 1.1280 0.09986 0.09499 -0.0134 0.0105 1.0000
16.250 1.1142 0.10678 0.10204 -0.0170 0.0103 1.0000
16.500 1.0991 0.11410 0.10948 -0.0208 0.0102 1.0000
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Polar data table (+)
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