GM15 (smoothed) (gm15sm-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GM15 (smoothed) (gm15sm-il) Reynolds number: 1,000,000 Max Cl/Cd: 146.49 at α=3.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-gm15sm-il-1000000.txt Download as CSV file: xf-gm15sm-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.3490 0.10134 0.09972 -0.0251 1.0000 0.0100
-8.500 -0.3483 0.09879 0.09720 -0.0250 1.0000 0.0101
-8.250 -0.3546 0.09702 0.09546 -0.0233 1.0000 0.0104
-8.000 -0.3423 0.09346 0.09191 -0.0266 0.9991 0.0105
-7.750 -0.3254 0.08927 0.08772 -0.0313 0.9973 0.0106
-7.500 -0.3093 0.08505 0.08351 -0.0361 0.9947 0.0106
-7.250 -0.2954 0.08104 0.07950 -0.0403 0.9903 0.0106
-7.000 -0.2751 0.07635 0.07481 -0.0465 0.9858 0.0106
-6.750 -0.2563 0.07175 0.07021 -0.0523 0.9806 0.0107
-6.500 -0.2309 0.06593 0.06438 -0.0608 0.9771 0.0107
-5.250 -0.0024 0.01471 0.01119 -0.1381 0.9629 0.0113
-5.000 0.0321 0.01327 0.00949 -0.1400 0.9599 0.0111
-4.750 0.0635 0.01265 0.00875 -0.1408 0.9557 0.0108
-4.500 0.0964 0.01072 0.00651 -0.1423 0.9518 0.0106
-4.250 0.1308 0.00964 0.00522 -0.1438 0.9482 0.0107
-4.000 0.1551 0.00804 0.00336 -0.1431 0.9421 0.0120
-3.750 0.1847 0.00770 0.00296 -0.1434 0.9372 0.0134
-3.500 0.2132 0.00744 0.00263 -0.1434 0.9321 0.0149
-3.250 0.2399 0.00721 0.00232 -0.1430 0.9260 0.0161
-3.000 0.2689 0.00681 0.00183 -0.1430 0.9207 0.0214
-2.750 0.2942 0.00662 0.00162 -0.1423 0.9135 0.0273
-2.500 0.3223 0.00636 0.00137 -0.1422 0.9074 0.0444
-2.250 0.3474 0.00605 0.00121 -0.1415 0.8995 0.0906
-2.000 0.3745 0.00583 0.00109 -0.1413 0.8920 0.1401
-1.750 0.4006 0.00568 0.00102 -0.1408 0.8820 0.1747
-1.500 0.4270 0.00560 0.00095 -0.1403 0.8708 0.1972
-1.250 0.4535 0.00555 0.00089 -0.1398 0.8576 0.2156
-1.000 0.4797 0.00551 0.00084 -0.1392 0.8414 0.2379
-0.750 0.5055 0.00550 0.00081 -0.1386 0.8221 0.2601
-0.500 0.5307 0.00554 0.00078 -0.1378 0.7985 0.2766
-0.250 0.5555 0.00561 0.00078 -0.1369 0.7723 0.2916
0.000 0.5800 0.00571 0.00079 -0.1360 0.7453 0.3070
0.250 0.6046 0.00581 0.00082 -0.1352 0.7199 0.3222
0.500 0.6292 0.00593 0.00086 -0.1344 0.6957 0.3388
0.750 0.6541 0.00603 0.00091 -0.1336 0.6736 0.3559
1.000 0.6793 0.00612 0.00097 -0.1329 0.6535 0.3748
1.500 0.7299 0.00629 0.00111 -0.1317 0.6164 0.4197
1.750 0.7553 0.00636 0.00119 -0.1311 0.5994 0.4503
2.000 0.7807 0.00640 0.00129 -0.1305 0.5824 0.4924
2.250 0.8054 0.00633 0.00142 -0.1298 0.5659 0.5929
2.500 0.8372 0.00575 0.00156 -0.1308 0.5482 1.0000
2.750 0.8628 0.00592 0.00165 -0.1303 0.5315 1.0000
3.000 0.8885 0.00607 0.00176 -0.1297 0.5144 1.0000
3.250 0.9141 0.00624 0.00187 -0.1292 0.4967 1.0000
3.500 0.9394 0.00642 0.00200 -0.1286 0.4781 1.0000
3.750 0.9634 0.00671 0.00214 -0.1278 0.4445 1.0000
4.000 0.9854 0.00719 0.00234 -0.1267 0.3871 1.0000
4.250 1.0076 0.00767 0.00259 -0.1256 0.3353 1.0000
4.500 1.0314 0.00803 0.00281 -0.1248 0.3014 1.0000
4.750 1.0546 0.00846 0.00307 -0.1239 0.2648 1.0000
5.000 1.0770 0.00897 0.00337 -0.1230 0.2207 1.0000
5.250 1.0979 0.00964 0.00377 -0.1218 0.1656 1.0000
5.500 1.1145 0.01080 0.00444 -0.1199 0.0762 1.0000
5.750 1.1337 0.01172 0.00509 -0.1184 0.0277 1.0000
6.000 1.1565 0.01222 0.00557 -0.1174 0.0187 1.0000
6.250 1.1782 0.01288 0.00629 -0.1161 0.0142 1.0000
6.500 1.2012 0.01333 0.00680 -0.1151 0.0133 1.0000
6.750 1.2249 0.01368 0.00718 -0.1144 0.0124 1.0000
7.000 1.2476 0.01413 0.00768 -0.1134 0.0114 1.0000
7.250 1.2698 0.01462 0.00820 -0.1124 0.0104 1.0000
7.500 1.2862 0.01577 0.00949 -0.1103 0.0089 1.0000
7.750 1.3058 0.01650 0.01030 -0.1088 0.0083 1.0000
8.000 1.3275 0.01697 0.01081 -0.1078 0.0078 1.0000
8.250 1.3484 0.01750 0.01139 -0.1066 0.0071 1.0000
8.500 1.3696 0.01797 0.01187 -0.1056 0.0064 1.0000
8.750 1.3880 0.01871 0.01267 -0.1040 0.0058 1.0000
9.000 1.3913 0.02104 0.01521 -0.0999 0.0052 1.0000
9.250 1.4056 0.02220 0.01649 -0.0978 0.0051 1.0000
9.500 1.4222 0.02302 0.01739 -0.0960 0.0049 1.0000
9.750 1.4365 0.02407 0.01856 -0.0939 0.0048 1.0000
10.000 1.4495 0.02516 0.01976 -0.0916 0.0046 1.0000
10.250 1.4591 0.02638 0.02110 -0.0887 0.0045 1.0000
10.500 1.4679 0.02757 0.02240 -0.0858 0.0043 1.0000
10.750 1.4746 0.02900 0.02396 -0.0828 0.0041 1.0000
11.000 1.4813 0.03027 0.02535 -0.0799 0.0039 1.0000
11.250 1.4852 0.03191 0.02714 -0.0768 0.0038 1.0000
11.500 1.4902 0.03321 0.02858 -0.0741 0.0036 1.0000
11.750 1.4933 0.03478 0.03026 -0.0715 0.0035 1.0000
12.000 1.4928 0.03690 0.03254 -0.0687 0.0034 1.0000
12.250 1.4945 0.03860 0.03435 -0.0665 0.0033 1.0000
12.500 1.4941 0.04064 0.03651 -0.0644 0.0032 1.0000
12.750 1.4880 0.04359 0.03963 -0.0623 0.0032 1.0000
13.000 1.4801 0.04688 0.04309 -0.0607 0.0031 1.0000
13.250 1.4690 0.05077 0.04717 -0.0596 0.0031 1.0000
13.500 1.4550 0.05539 0.05199 -0.0591 0.0031 1.0000
13.750 1.4382 0.06072 0.05753 -0.0596 0.0030 1.0000
14.000 1.4218 0.06643 0.06344 -0.0608 0.0030 1.0000
14.250 1.4042 0.07279 0.06999 -0.0629 0.0030 1.0000
14.500 1.3858 0.07979 0.07717 -0.0658 0.0030 1.0000
14.750 1.3666 0.08749 0.08506 -0.0695 0.0031 1.0000
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Polar data table (+)
Polar graphs
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