GM15 (smoothed) (gm15sm-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: GM15 (smoothed) (gm15sm-il) Reynolds number: 100,000 Max Cl/Cd: 66.21 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-gm15sm-il-100000.txt Download as CSV file: xf-gm15sm-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.3467 0.10526 0.10043 -0.0289 1.0000 0.0743
-7.750 -0.3611 0.10520 0.10051 -0.0287 1.0000 0.0747
-7.500 -0.3715 0.10458 0.10001 -0.0299 1.0000 0.0750
-7.250 -0.3431 0.09623 0.09159 -0.0254 1.0000 0.0780
-7.000 -0.3428 0.09405 0.08947 -0.0235 1.0000 0.0802
-6.750 -0.3481 0.09238 0.08788 -0.0215 1.0000 0.0822
-6.500 -0.3529 0.09061 0.08618 -0.0209 1.0000 0.0850
-6.250 -0.3593 0.08967 0.08534 -0.0251 1.0000 0.0878
-6.000 -0.3562 0.08693 0.08267 -0.0317 1.0000 0.0890
-5.750 -0.3548 0.08322 0.07900 -0.0240 1.0000 0.0907
-5.500 -0.3504 0.08067 0.07648 -0.0218 1.0000 0.0934
-5.250 -0.3445 0.07817 0.07401 -0.0227 1.0000 0.0974
-5.000 -0.3251 0.07419 0.07003 -0.0347 1.0000 0.1031
-4.750 -0.3236 0.07161 0.06750 -0.0296 1.0000 0.1051
-4.500 -0.3143 0.06907 0.06494 -0.0292 1.0000 0.1098
-4.250 -0.2869 0.06463 0.06044 -0.0386 1.0000 0.1178
-4.000 -0.2789 0.06230 0.05815 -0.0364 1.0000 0.1215
-3.500 -0.2190 0.05463 0.05029 -0.0498 1.0000 0.1451
-3.250 -0.1964 0.05183 0.04745 -0.0521 1.0000 0.1592
-3.000 -0.0584 0.02949 0.02317 -0.0855 1.0000 0.0710
-2.750 -0.0158 0.02494 0.01764 -0.0892 1.0000 0.0660
-2.500 0.0149 0.02282 0.01497 -0.0900 1.0000 0.0669
-2.250 0.0414 0.02163 0.01342 -0.0899 1.0000 0.0719
-2.000 0.0664 0.02061 0.01222 -0.0897 1.0000 0.0813
-1.750 0.0915 0.01968 0.01113 -0.0893 1.0000 0.0914
-1.500 0.1148 0.01921 0.01068 -0.0889 1.0000 0.1167
-1.250 0.1586 0.01875 0.01065 -0.0923 0.9938 0.2289
-1.000 0.2032 0.01933 0.01131 -0.0959 0.9843 0.3083
-0.750 0.2476 0.01958 0.01157 -0.0995 0.9751 0.3586
-0.500 0.2895 0.01956 0.01152 -0.1024 0.9647 0.3972
-0.250 0.3315 0.01945 0.01145 -0.1054 0.9545 0.4330
0.000 0.3776 0.01927 0.01129 -0.1090 0.9454 0.4723
0.250 0.4245 0.01897 0.01106 -0.1127 0.9362 0.5180
0.500 0.4669 0.01855 0.01085 -0.1154 0.9252 0.5778
0.750 0.5124 0.01734 0.01045 -0.1185 0.9159 1.0000
1.000 0.5645 0.01719 0.01005 -0.1229 0.9077 1.0000
1.250 0.6059 0.01707 0.00981 -0.1252 0.8953 1.0000
1.500 0.6473 0.01690 0.00958 -0.1274 0.8831 1.0000
1.750 0.6869 0.01667 0.00932 -0.1290 0.8705 1.0000
2.000 0.7253 0.01639 0.00903 -0.1302 0.8575 1.0000
2.250 0.7623 0.01609 0.00877 -0.1311 0.8439 1.0000
2.500 0.7979 0.01579 0.00849 -0.1317 0.8294 1.0000
2.750 0.8326 0.01551 0.00822 -0.1320 0.8139 1.0000
3.000 0.8667 0.01525 0.00797 -0.1322 0.7977 1.0000
3.250 0.8955 0.01519 0.00798 -0.1316 0.7777 1.0000
3.500 0.9261 0.01512 0.00791 -0.1312 0.7580 1.0000
3.750 0.9544 0.01519 0.00799 -0.1305 0.7366 1.0000
4.000 0.9828 0.01531 0.00809 -0.1299 0.7150 1.0000
4.250 1.0085 0.01556 0.00836 -0.1288 0.6915 1.0000
4.500 1.0349 0.01585 0.00871 -0.1279 0.6686 1.0000
4.750 1.0603 0.01619 0.00905 -0.1268 0.6450 1.0000
5.000 1.0841 0.01658 0.00950 -0.1255 0.6201 1.0000
5.250 1.1077 0.01698 0.00994 -0.1241 0.5946 1.0000
5.500 1.1274 0.01715 0.01002 -0.1216 0.5570 1.0000
5.750 1.1422 0.01725 0.01004 -0.1182 0.5054 1.0000
6.000 1.1587 0.01759 0.01031 -0.1156 0.4575 1.0000
6.250 1.1739 0.01809 0.01070 -0.1128 0.3997 1.0000
6.500 1.1784 0.01952 0.01138 -0.1085 0.2592 1.0000
6.750 1.1720 0.02346 0.01373 -0.1034 0.0919 1.0000
7.000 1.1828 0.02542 0.01563 -0.1005 0.0715 1.0000
7.250 1.1934 0.02736 0.01759 -0.0976 0.0633 1.0000
7.500 1.2079 0.02920 0.01945 -0.0952 0.0580 1.0000
7.750 1.2285 0.03226 0.02238 -0.0939 0.0540 1.0000
8.000 1.2530 0.03415 0.02452 -0.0928 0.0505 1.0000
8.250 1.2764 0.03638 0.02689 -0.0918 0.0462 1.0000
8.500 1.3040 0.03965 0.03033 -0.0913 0.0446 1.0000
8.750 1.3282 0.04329 0.03429 -0.0903 0.0442 1.0000
9.000 1.3469 0.04695 0.03842 -0.0884 0.0447 1.0000
9.250 1.3603 0.05100 0.04283 -0.0865 0.0438 1.0000
9.500 1.3685 0.05601 0.04820 -0.0845 0.0430 1.0000
9.750 1.3737 0.05995 0.05258 -0.0819 0.0431 1.0000
10.000 1.3605 0.06283 0.05637 -0.0762 0.0461 1.0000
10.250 1.3464 0.06801 0.06210 -0.0723 0.0491 1.0000
10.500 1.3357 0.07304 0.06741 -0.0695 0.0512 1.0000
10.750 1.2190 0.07066 0.06561 -0.0570 0.0491 1.0000
11.000 1.1925 0.07578 0.07096 -0.0553 0.0498 1.0000
11.250 1.1652 0.08143 0.07681 -0.0549 0.0506 1.0000
11.500 1.1377 0.08757 0.08314 -0.0556 0.0513 1.0000
11.750 1.1116 0.09415 0.08987 -0.0573 0.0523 1.0000
12.000 1.0855 0.10103 0.09688 -0.0598 0.0530 1.0000
12.250 1.0030 0.11480 0.11106 -0.0716 0.0587 1.0000
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Polar data table (+)
Polar graphs
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