GM15 (smoothed) (gm15sm-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GM15 (smoothed) (gm15sm-il) Reynolds number: 500,000 Max Cl/Cd: 112.35 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-gm15sm-il-500000-n5.txt Download as CSV file: xf-gm15sm-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.3456 0.09591 0.09367 -0.0261 1.0000 0.0096
-8.000 -0.3492 0.09374 0.09154 -0.0248 1.0000 0.0090
-7.750 -0.3357 0.08923 0.08703 -0.0293 0.9980 0.0084
-7.500 -0.3219 0.08438 0.08220 -0.0343 0.9928 0.0080
-7.250 -0.3100 0.07992 0.07774 -0.0389 0.9830 0.0079
-7.000 -0.2914 0.07471 0.07253 -0.0455 0.9759 0.0078
-6.750 -0.2712 0.06963 0.06744 -0.0526 0.9708 0.0079
-6.500 -0.2456 0.06432 0.06211 -0.0610 0.9667 0.0082
-6.250 -0.2123 0.05767 0.05543 -0.0726 0.9636 0.0084
-5.750 -0.0869 0.01969 0.01597 -0.1294 0.9545 0.0086
-5.500 -0.0502 0.01599 0.01161 -0.1332 0.9517 0.0086
-5.250 -0.0146 0.01395 0.00916 -0.1356 0.9493 0.0087
-5.000 0.0161 0.01265 0.00757 -0.1366 0.9452 0.0091
-4.750 0.0459 0.01167 0.00638 -0.1371 0.9405 0.0094
-4.500 0.0782 0.01091 0.00542 -0.1382 0.9367 0.0101
-4.250 0.1079 0.01039 0.00477 -0.1385 0.9320 0.0106
-4.000 0.1355 0.00968 0.00394 -0.1385 0.9262 0.0117
-3.750 0.1663 0.00929 0.00346 -0.1391 0.9215 0.0129
-3.500 0.1925 0.00905 0.00318 -0.1387 0.9148 0.0149
-3.250 0.2214 0.00881 0.00285 -0.1387 0.9087 0.0168
-3.000 0.2483 0.00843 0.00242 -0.1384 0.9015 0.0215
-2.750 0.2767 0.00823 0.00214 -0.1383 0.8942 0.0261
-2.500 0.3033 0.00800 0.00192 -0.1379 0.8852 0.0382
-2.250 0.3307 0.00772 0.00171 -0.1377 0.8757 0.0672
-2.000 0.3579 0.00746 0.00154 -0.1375 0.8645 0.1111
-1.750 0.3850 0.00732 0.00142 -0.1372 0.8511 0.1419
-1.500 0.4119 0.00721 0.00133 -0.1369 0.8352 0.1722
-1.250 0.4387 0.00713 0.00127 -0.1365 0.8168 0.2033
-1.000 0.4651 0.00712 0.00120 -0.1360 0.7952 0.2283
-0.750 0.4908 0.00716 0.00115 -0.1353 0.7699 0.2451
-0.500 0.5160 0.00723 0.00113 -0.1345 0.7436 0.2601
-0.250 0.5410 0.00733 0.00113 -0.1338 0.7188 0.2747
0.000 0.5660 0.00743 0.00115 -0.1330 0.6956 0.2892
0.250 0.5910 0.00753 0.00118 -0.1323 0.6736 0.3042
0.500 0.6162 0.00763 0.00122 -0.1316 0.6538 0.3192
0.750 0.6415 0.00773 0.00128 -0.1309 0.6347 0.3349
1.000 0.6667 0.00784 0.00135 -0.1303 0.6166 0.3508
1.500 0.7176 0.00803 0.00150 -0.1291 0.5818 0.3867
1.750 0.7430 0.00812 0.00159 -0.1285 0.5650 0.4082
2.000 0.7683 0.00822 0.00171 -0.1279 0.5481 0.4331
2.250 0.7935 0.00831 0.00183 -0.1273 0.5321 0.4648
2.500 0.8186 0.00836 0.00196 -0.1267 0.5159 0.5124
2.750 0.8406 0.00806 0.00215 -0.1255 0.5001 0.7196
3.250 0.9002 0.00803 0.00242 -0.1263 0.4647 1.0000
3.500 0.9253 0.00825 0.00258 -0.1257 0.4471 1.0000
3.750 0.9505 0.00846 0.00274 -0.1251 0.4291 1.0000
4.000 0.9754 0.00870 0.00293 -0.1244 0.4096 1.0000
4.250 0.9978 0.00915 0.00320 -0.1234 0.3659 1.0000
4.500 1.0184 0.00981 0.00352 -0.1221 0.3009 1.0000
4.750 1.0391 0.01051 0.00389 -0.1209 0.2395 1.0000
5.000 1.0598 0.01123 0.00431 -0.1198 0.1816 1.0000
5.250 1.0793 0.01211 0.00484 -0.1185 0.1158 1.0000
5.500 1.0982 0.01307 0.00548 -0.1170 0.0564 1.0000
5.750 1.1196 0.01374 0.00604 -0.1159 0.0309 1.0000
6.000 1.1422 0.01426 0.00653 -0.1150 0.0214 1.0000
6.250 1.1654 0.01469 0.00701 -0.1141 0.0179 1.0000
6.500 1.1873 0.01528 0.00763 -0.1130 0.0145 1.0000
6.750 1.2096 0.01578 0.00819 -0.1120 0.0129 1.0000
7.000 1.2316 0.01631 0.00880 -0.1109 0.0118 1.0000
7.250 1.2530 0.01688 0.00946 -0.1098 0.0108 1.0000
7.500 1.2738 0.01750 0.01011 -0.1086 0.0097 1.0000
7.750 1.2917 0.01840 0.01110 -0.1069 0.0085 1.0000
8.000 1.3118 0.01903 0.01181 -0.1056 0.0080 1.0000
8.250 1.3308 0.01975 0.01262 -0.1042 0.0075 1.0000
8.500 1.3487 0.02054 0.01351 -0.1025 0.0069 1.0000
8.750 1.3662 0.02133 0.01438 -0.1009 0.0064 1.0000
9.000 1.3827 0.02218 0.01533 -0.0992 0.0060 1.0000
9.250 1.3959 0.02329 0.01653 -0.0969 0.0055 1.0000
9.500 1.4027 0.02499 0.01836 -0.0937 0.0051 1.0000
9.750 1.4157 0.02586 0.01935 -0.0914 0.0050 1.0000
10.000 1.4278 0.02674 0.02034 -0.0890 0.0047 1.0000
10.250 1.4374 0.02780 0.02153 -0.0863 0.0044 1.0000
10.500 1.4462 0.02892 0.02278 -0.0836 0.0041 1.0000
10.750 1.4521 0.03035 0.02435 -0.0807 0.0040 1.0000
11.000 1.4577 0.03182 0.02596 -0.0780 0.0038 1.0000
11.250 1.4619 0.03345 0.02775 -0.0753 0.0037 1.0000
11.500 1.4661 0.03510 0.02954 -0.0728 0.0035 1.0000
11.750 1.4689 0.03692 0.03154 -0.0705 0.0034 1.0000
12.000 1.4701 0.03900 0.03378 -0.0682 0.0034 1.0000
12.250 1.4715 0.04103 0.03595 -0.0663 0.0033 1.0000
12.500 1.4718 0.04326 0.03832 -0.0646 0.0032 1.0000
12.750 1.4692 0.04599 0.04122 -0.0632 0.0031 1.0000
13.000 1.4652 0.04901 0.04440 -0.0621 0.0031 1.0000
13.250 1.4589 0.05250 0.04807 -0.0614 0.0030 1.0000
13.500 1.4497 0.05662 0.05239 -0.0612 0.0030 1.0000
13.750 1.4378 0.06141 0.05737 -0.0617 0.0029 1.0000
14.000 1.4239 0.06686 0.06303 -0.0628 0.0029 1.0000
14.250 1.4072 0.07310 0.06950 -0.0648 0.0028 1.0000
14.500 1.3896 0.07997 0.07658 -0.0675 0.0028 1.0000
14.750 1.3726 0.08718 0.08399 -0.0708 0.0028 1.0000
15.000 1.3562 0.09473 0.09171 -0.0746 0.0028 1.0000
15.250 1.3380 0.10314 0.10031 -0.0792 0.0028 1.0000
15.500 1.3207 0.11179 0.10912 -0.0841 0.0028 1.0000
15.750 1.3047 0.12058 0.11808 -0.0893 0.0028 1.0000
16.000 1.2890 0.12979 0.12743 -0.0948 0.0029 1.0000
16.250 1.2705 0.14015 0.13795 -0.1011 0.0029 1.0000
16.500 1.2480 0.15241 0.15036 -0.1086 0.0030 1.0000
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Polar data table (+)
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