GM15 (smoothed) (gm15sm-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GM15 (smoothed) (gm15sm-il) Reynolds number: 500,000 Max Cl/Cd: 123.6 at α=3.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-gm15sm-il-500000.txt Download as CSV file: xf-gm15sm-il-500000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.750 -0.3535 0.09508 0.09295 -0.0239 1.0000 0.0164
-7.500 -0.3624 0.09354 0.09145 -0.0215 1.0000 0.0164
-7.250 -0.3728 0.09209 0.09005 -0.0188 1.0000 0.0164
-7.000 -0.3528 0.08758 0.08554 -0.0248 0.9970 0.0165
-6.750 -0.3280 0.08238 0.08032 -0.0322 0.9937 0.0165
-6.500 -0.3138 0.07425 0.07222 -0.0407 0.9894 0.0174
-6.250 -0.2889 0.07080 0.06875 -0.0455 0.9869 0.0181
-6.000 -0.2638 0.06729 0.06522 -0.0508 0.9836 0.0192
-5.750 -0.2342 0.06279 0.06070 -0.0585 0.9795 0.0206
-5.500 -0.1920 0.05657 0.05443 -0.0708 0.9767 0.0233
-5.250 -0.1344 0.04954 0.04730 -0.0862 0.9749 0.0250
-5.000 -0.0792 0.03200 0.02930 -0.1106 0.9697 0.0268
-4.750 -0.0438 0.02926 0.02644 -0.1149 0.9673 0.0281
-4.500 -0.0021 0.02502 0.02185 -0.1210 0.9655 0.0299
-4.250 0.0464 0.01588 0.01122 -0.1267 0.9642 0.0170
-4.000 0.0841 0.01415 0.00920 -0.1289 0.9631 0.0168
-3.750 0.1216 0.01164 0.00632 -0.1312 0.9621 0.0177
-3.500 0.1525 0.01070 0.00527 -0.1318 0.9579 0.0196
-3.250 0.1881 0.01004 0.00453 -0.1333 0.9549 0.0217
-3.000 0.2258 0.00973 0.00415 -0.1352 0.9522 0.0251
-2.750 0.2639 0.00876 0.00307 -0.1373 0.9496 0.0339
-2.500 0.2954 0.00829 0.00258 -0.1379 0.9442 0.0528
-2.250 0.3277 0.00772 0.00231 -0.1389 0.9385 0.1412
-2.000 0.3603 0.00752 0.00219 -0.1398 0.9329 0.1876
-1.750 0.3884 0.00742 0.00210 -0.1396 0.9249 0.2135
-1.500 0.4172 0.00732 0.00204 -0.1396 0.9174 0.2385
-1.250 0.4454 0.00722 0.00197 -0.1395 0.9091 0.2632
-1.000 0.4717 0.00715 0.00190 -0.1388 0.8992 0.2847
-0.750 0.4989 0.00706 0.00182 -0.1384 0.8889 0.3025
-0.500 0.5261 0.00697 0.00174 -0.1380 0.8773 0.3200
-0.250 0.5528 0.00690 0.00167 -0.1375 0.8638 0.3378
0.000 0.5791 0.00683 0.00160 -0.1369 0.8478 0.3560
0.250 0.6056 0.00679 0.00155 -0.1363 0.8292 0.3760
0.500 0.6319 0.00678 0.00151 -0.1357 0.8083 0.3976
0.750 0.6576 0.00680 0.00150 -0.1350 0.7845 0.4224
1.250 0.7072 0.00688 0.00157 -0.1333 0.7341 0.4936
1.500 0.7307 0.00682 0.00166 -0.1323 0.7107 0.5815
2.000 0.7872 0.00642 0.00182 -0.1323 0.6667 1.0000
2.250 0.8121 0.00661 0.00191 -0.1315 0.6467 1.0000
2.500 0.8370 0.00681 0.00202 -0.1308 0.6279 1.0000
2.750 0.8621 0.00699 0.00213 -0.1301 0.6090 1.0000
3.000 0.8870 0.00719 0.00228 -0.1293 0.5907 1.0000
3.250 0.9119 0.00739 0.00242 -0.1286 0.5726 1.0000
3.500 0.9369 0.00758 0.00256 -0.1279 0.5538 1.0000
3.750 0.9617 0.00780 0.00273 -0.1272 0.5348 1.0000
4.000 0.9862 0.00803 0.00290 -0.1264 0.5144 1.0000
4.250 1.0088 0.00836 0.00311 -0.1253 0.4772 1.0000
4.500 1.0305 0.00879 0.00333 -0.1240 0.4289 1.0000
4.750 1.0523 0.00925 0.00359 -0.1229 0.3819 1.0000
5.000 1.0740 0.00978 0.00389 -0.1217 0.3357 1.0000
5.250 1.0958 0.01032 0.00423 -0.1207 0.2895 1.0000
5.500 1.1164 0.01101 0.00468 -0.1194 0.2332 1.0000
5.750 1.1324 0.01225 0.00537 -0.1176 0.1347 1.0000
6.000 1.1434 0.01417 0.00663 -0.1149 0.0315 1.0000
6.250 1.1649 0.01486 0.00736 -0.1136 0.0248 1.0000
6.500 1.1844 0.01576 0.00836 -0.1120 0.0209 1.0000
6.750 1.2056 0.01642 0.00912 -0.1107 0.0194 1.0000
7.000 1.2254 0.01720 0.00998 -0.1092 0.0178 1.0000
7.250 1.2448 0.01798 0.01084 -0.1077 0.0161 1.0000
7.500 1.2538 0.01996 0.01297 -0.1045 0.0139 1.0000
7.750 1.2719 0.02090 0.01400 -0.1028 0.0133 1.0000
8.000 1.2896 0.02191 0.01511 -0.1010 0.0125 1.0000
8.250 1.3063 0.02310 0.01640 -0.0991 0.0117 1.0000
8.500 1.3226 0.02446 0.01786 -0.0971 0.0110 1.0000
8.750 1.3389 0.02583 0.01934 -0.0953 0.0104 1.0000
9.000 1.3547 0.02705 0.02063 -0.0936 0.0097 1.0000
9.250 1.3678 0.02984 0.02356 -0.0917 0.0089 1.0000
9.500 1.3808 0.03364 0.02768 -0.0898 0.0085 1.0000
9.750 1.3935 0.03546 0.02972 -0.0876 0.0083 1.0000
10.000 1.4035 0.03760 0.03211 -0.0852 0.0082 1.0000
10.250 1.4096 0.04025 0.03504 -0.0823 0.0080 1.0000
10.500 1.4094 0.04298 0.03804 -0.0787 0.0079 1.0000
10.750 1.4033 0.04596 0.04129 -0.0745 0.0079 1.0000
11.000 1.3932 0.04910 0.04469 -0.0704 0.0079 1.0000
11.250 1.3791 0.05265 0.04849 -0.0667 0.0079 1.0000
11.500 1.3629 0.05645 0.05255 -0.0636 0.0079 1.0000
11.750 1.3444 0.06072 0.05704 -0.0615 0.0080 1.0000
12.000 1.3238 0.06562 0.06215 -0.0604 0.0081 1.0000
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Polar data table (+)
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