GM15 (smoothed) (gm15sm-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: GM15 (smoothed) (gm15sm-il) Reynolds number: 50,000 Max Cl/Cd: 46.07 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-gm15sm-il-50000-n5.txt Download as CSV file: xf-gm15sm-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GM15 (smoothed)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.500 -0.3455 0.10305 0.09633 -0.0270 1.0000 0.1008
-7.250 -0.3557 0.10209 0.09553 -0.0271 1.0000 0.1017
-7.000 -0.3591 0.10032 0.09388 -0.0287 1.0000 0.1021
-6.750 -0.3487 0.09569 0.08928 -0.0253 1.0000 0.1045
-6.500 -0.3441 0.09297 0.08661 -0.0237 1.0000 0.1085
-6.250 -0.3446 0.09085 0.08458 -0.0241 1.0000 0.1121
-5.750 -0.3355 0.08069 0.07448 -0.0353 1.0000 0.0625
-5.500 -0.3295 0.07792 0.07171 -0.0330 1.0000 0.0594
-5.250 -0.3215 0.07459 0.06842 -0.0341 1.0000 0.0574
-5.000 -0.3097 0.07064 0.06448 -0.0371 1.0000 0.0548
-4.750 -0.2703 0.06122 0.05482 -0.0532 1.0000 0.0486
-4.500 -0.2520 0.05724 0.05080 -0.0557 1.0000 0.0481
-4.250 -0.2252 0.05220 0.04561 -0.0609 1.0000 0.0474
-4.000 -0.1882 0.04598 0.03908 -0.0688 1.0000 0.0469
-3.750 -0.1434 0.03942 0.03192 -0.0778 1.0000 0.0468
-3.500 -0.0970 0.03378 0.02524 -0.0851 1.0000 0.0484
-3.250 -0.0697 0.03165 0.02295 -0.0868 1.0000 0.0532
-3.000 -0.0365 0.02904 0.01973 -0.0889 1.0000 0.0572
-2.750 -0.0040 0.02678 0.01678 -0.0902 1.0000 0.0606
-2.500 0.0224 0.02547 0.01530 -0.0905 1.0000 0.0678
-2.250 0.0487 0.02444 0.01402 -0.0906 1.0000 0.0789
-2.000 0.0764 0.02347 0.01275 -0.0907 1.0000 0.0916
-1.750 0.1099 0.02281 0.01202 -0.0923 0.9974 0.1287
-1.500 0.1512 0.02247 0.01187 -0.0954 0.9896 0.2121
-1.250 0.1895 0.02270 0.01213 -0.0979 0.9803 0.2853
-1.000 0.2283 0.02275 0.01205 -0.1002 0.9714 0.3338
-0.750 0.2686 0.02269 0.01186 -0.1028 0.9627 0.3727
-0.500 0.3064 0.02258 0.01166 -0.1050 0.9527 0.4081
-0.250 0.3450 0.02243 0.01149 -0.1072 0.9430 0.4434
0.000 0.3863 0.02222 0.01129 -0.1099 0.9342 0.4845
0.250 0.4226 0.02196 0.01116 -0.1116 0.9230 0.5333
0.500 0.4569 0.02145 0.01105 -0.1128 0.9117 0.6183
0.750 0.4886 0.02083 0.01078 -0.1132 0.8983 1.0000
1.000 0.5256 0.02097 0.01070 -0.1149 0.8858 1.0000
1.250 0.5621 0.02108 0.01065 -0.1164 0.8730 1.0000
1.500 0.5977 0.02116 0.01065 -0.1177 0.8599 1.0000
1.750 0.6317 0.02121 0.01063 -0.1185 0.8461 1.0000
2.000 0.6650 0.02124 0.01062 -0.1191 0.8319 1.0000
2.250 0.6979 0.02125 0.01062 -0.1196 0.8173 1.0000
2.500 0.7305 0.02125 0.01067 -0.1199 0.8022 1.0000
2.750 0.7632 0.02122 0.01066 -0.1202 0.7867 1.0000
3.000 0.7961 0.02118 0.01066 -0.1204 0.7709 1.0000
3.250 0.8277 0.02119 0.01072 -0.1204 0.7540 1.0000
3.500 0.8570 0.02128 0.01094 -0.1200 0.7352 1.0000
3.750 0.8880 0.02134 0.01107 -0.1198 0.7168 1.0000
4.000 0.9181 0.02145 0.01125 -0.1195 0.6977 1.0000
4.250 0.9459 0.02168 0.01156 -0.1188 0.6769 1.0000
4.500 0.9749 0.02189 0.01184 -0.1183 0.6567 1.0000
4.750 1.0007 0.02224 0.01240 -0.1174 0.6347 1.0000
5.000 1.0276 0.02258 0.01286 -0.1166 0.6132 1.0000
5.250 1.0527 0.02301 0.01344 -0.1155 0.5907 1.0000
5.500 1.0773 0.02347 0.01407 -0.1145 0.5681 1.0000
5.750 1.1025 0.02393 0.01468 -0.1134 0.5456 1.0000
6.000 1.1251 0.02448 0.01554 -0.1120 0.5210 1.0000
6.250 1.1438 0.02490 0.01606 -0.1096 0.4854 1.0000
6.500 1.1511 0.02531 0.01617 -0.1051 0.4169 1.0000
6.750 1.1577 0.02623 0.01669 -0.1013 0.3375 1.0000
7.000 1.1648 0.02770 0.01772 -0.0981 0.2447 1.0000
7.250 1.1664 0.03049 0.01957 -0.0950 0.1237 1.0000
7.500 1.1713 0.03339 0.02199 -0.0923 0.0826 1.0000
7.750 1.1782 0.03580 0.02430 -0.0898 0.0671 1.0000
8.000 1.1870 0.03788 0.02664 -0.0873 0.0597 1.0000
8.250 1.1936 0.04013 0.02897 -0.0846 0.0550 1.0000
8.500 1.2039 0.04219 0.03126 -0.0822 0.0502 1.0000
8.750 1.2141 0.04426 0.03347 -0.0800 0.0452 1.0000
9.000 1.2290 0.04689 0.03613 -0.0784 0.0419 1.0000
9.250 1.2562 0.04959 0.03922 -0.0776 0.0397 1.0000
9.500 1.2811 0.05282 0.04284 -0.0768 0.0379 1.0000
9.750 1.2972 0.05614 0.04654 -0.0755 0.0363 1.0000
10.000 1.3050 0.05923 0.04994 -0.0736 0.0343 1.0000
10.250 1.3083 0.06242 0.05331 -0.0717 0.0326 1.0000
10.500 1.3099 0.06681 0.05794 -0.0701 0.0313 1.0000
10.750 1.3008 0.07005 0.06159 -0.0672 0.0309 1.0000
11.000 1.2900 0.07374 0.06565 -0.0650 0.0307 1.0000
11.250 1.2773 0.07782 0.07005 -0.0634 0.0306 1.0000
11.500 1.2625 0.08225 0.07478 -0.0626 0.0306 1.0000
11.750 1.2462 0.08709 0.07988 -0.0627 0.0306 1.0000
12.000 1.2288 0.09241 0.08544 -0.0637 0.0306 1.0000
12.250 1.2110 0.09825 0.09150 -0.0658 0.0307 1.0000
12.500 1.1929 0.10465 0.09808 -0.0688 0.0309 1.0000
12.750 1.1753 0.11157 0.10516 -0.0726 0.0310 1.0000
13.000 1.1587 0.11896 0.11268 -0.0770 0.0312 1.0000
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Polar data table (+)
Polar graphs
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