GM15 (smoothed) (gm15sm-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GM15 (smoothed) (gm15sm-il) Reynolds number: 100,000 Max Cl/Cd: 66.89 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-gm15sm-il-100000-n5.txt Download as CSV file: xf-gm15sm-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.3488 0.10592 0.10099 -0.0307 1.0000 0.0482
-8.000 -0.3533 0.10418 0.09934 -0.0308 1.0000 0.0484
-7.750 -0.3592 0.10239 0.09765 -0.0302 1.0000 0.0485
-7.500 -0.3634 0.10032 0.09567 -0.0299 1.0000 0.0486
-7.250 -0.3647 0.09780 0.09323 -0.0304 1.0000 0.0487
-7.000 -0.3642 0.09513 0.09061 -0.0312 1.0000 0.0487
-6.750 -0.3635 0.09077 0.08632 -0.0282 1.0000 0.0494
-6.500 -0.3618 0.08779 0.08338 -0.0269 1.0000 0.0498
-6.250 -0.3598 0.08500 0.08064 -0.0265 1.0000 0.0501
-5.750 -0.3514 0.07761 0.07326 -0.0269 1.0000 0.0341
-5.500 -0.3466 0.07454 0.07022 -0.0274 1.0000 0.0322
-5.250 -0.3339 0.07040 0.06608 -0.0311 0.9993 0.0303
-4.750 -0.2351 0.05150 0.04683 -0.0623 0.9896 0.0248
-4.500 -0.1795 0.04123 0.03618 -0.0779 0.9867 0.0243
-4.250 -0.1210 0.03220 0.02619 -0.0916 0.9846 0.0247
-4.000 -0.0802 0.02809 0.02152 -0.0973 0.9810 0.0274
-3.750 -0.0400 0.02521 0.01803 -0.1012 0.9775 0.0292
-3.500 0.0003 0.02272 0.01494 -0.1042 0.9747 0.0305
-3.250 0.0350 0.02097 0.01277 -0.1057 0.9697 0.0324
-3.000 0.0719 0.01969 0.01113 -0.1074 0.9653 0.0357
-2.750 0.1104 0.01859 0.00995 -0.1098 0.9618 0.0436
-2.500 0.1433 0.01767 0.00882 -0.1108 0.9552 0.0511
-2.250 0.1812 0.01690 0.00801 -0.1129 0.9505 0.0722
-2.000 0.2175 0.01609 0.00743 -0.1147 0.9451 0.1321
-1.750 0.2526 0.01582 0.00728 -0.1163 0.9384 0.2040
-1.500 0.2896 0.01572 0.00717 -0.1180 0.9326 0.2568
-1.250 0.3233 0.01560 0.00703 -0.1191 0.9247 0.2889
-1.000 0.3587 0.01544 0.00683 -0.1204 0.9176 0.3154
-0.750 0.3940 0.01527 0.00662 -0.1217 0.9097 0.3407
-0.500 0.4262 0.01510 0.00643 -0.1223 0.9002 0.3640
-0.250 0.4634 0.01486 0.00620 -0.1239 0.8929 0.3897
0.000 0.4942 0.01468 0.00604 -0.1242 0.8815 0.4150
0.250 0.5249 0.01448 0.00589 -0.1244 0.8696 0.4440
0.500 0.5560 0.01425 0.00575 -0.1247 0.8572 0.4794
0.750 0.5869 0.01395 0.00561 -0.1250 0.8443 0.5292
1.000 0.6157 0.01319 0.00548 -0.1247 0.8309 0.7100
1.500 0.6813 0.01284 0.00513 -0.1257 0.7994 1.0000
1.750 0.7126 0.01283 0.00502 -0.1259 0.7821 1.0000
2.000 0.7423 0.01287 0.00499 -0.1258 0.7628 1.0000
2.250 0.7726 0.01293 0.00499 -0.1258 0.7434 1.0000
2.500 0.8015 0.01305 0.00503 -0.1256 0.7231 1.0000
2.750 0.8299 0.01320 0.00511 -0.1254 0.7025 1.0000
3.000 0.8574 0.01340 0.00525 -0.1249 0.6818 1.0000
3.250 0.8843 0.01363 0.00548 -0.1244 0.6610 1.0000
3.500 0.9106 0.01389 0.00570 -0.1238 0.6404 1.0000
3.750 0.9363 0.01417 0.00596 -0.1231 0.6198 1.0000
4.000 0.9618 0.01447 0.00625 -0.1223 0.5997 1.0000
4.250 0.9866 0.01479 0.00658 -0.1215 0.5789 1.0000
4.500 1.0113 0.01513 0.00699 -0.1207 0.5586 1.0000
4.750 1.0355 0.01548 0.00740 -0.1197 0.5373 1.0000
5.000 1.0596 0.01586 0.00781 -0.1188 0.5164 1.0000
5.250 1.0831 0.01625 0.00828 -0.1177 0.4940 1.0000
5.500 1.1040 0.01670 0.00869 -0.1162 0.4594 1.0000
5.750 1.1194 0.01738 0.00909 -0.1137 0.3916 1.0000
6.000 1.1342 0.01830 0.00961 -0.1114 0.3144 1.0000
6.250 1.1497 0.01940 0.01035 -0.1094 0.2410 1.0000
6.500 1.1587 0.02144 0.01155 -0.1069 0.1131 1.0000
6.750 1.1689 0.02359 0.01319 -0.1044 0.0554 1.0000
7.000 1.1831 0.02518 0.01477 -0.1022 0.0425 1.0000
7.250 1.1995 0.02638 0.01612 -0.1004 0.0353 1.0000
7.500 1.2109 0.02806 0.01797 -0.0979 0.0316 1.0000
7.750 1.2237 0.02952 0.01964 -0.0955 0.0297 1.0000
8.000 1.2357 0.03111 0.02141 -0.0930 0.0280 1.0000
8.250 1.2482 0.03280 0.02324 -0.0907 0.0262 1.0000
8.500 1.2608 0.03444 0.02495 -0.0887 0.0237 1.0000
8.750 1.2723 0.03715 0.02766 -0.0868 0.0215 1.0000
9.000 1.2905 0.03918 0.02993 -0.0853 0.0207 1.0000
9.250 1.3092 0.04167 0.03270 -0.0839 0.0199 1.0000
9.500 1.3265 0.04451 0.03585 -0.0825 0.0192 1.0000
9.750 1.3394 0.04744 0.03920 -0.0806 0.0185 1.0000
10.000 1.3469 0.05008 0.04217 -0.0783 0.0174 1.0000
10.250 1.3501 0.05250 0.04486 -0.0757 0.0164 1.0000
10.500 1.3487 0.05483 0.04743 -0.0727 0.0156 1.0000
10.750 1.3445 0.05751 0.05035 -0.0698 0.0151 1.0000
11.000 1.3376 0.06056 0.05365 -0.0672 0.0148 1.0000
11.250 1.3280 0.06405 0.05742 -0.0649 0.0147 1.0000
11.500 1.3161 0.06788 0.06151 -0.0631 0.0145 1.0000
11.750 1.3024 0.07205 0.06595 -0.0620 0.0145 1.0000
12.000 1.2870 0.07664 0.07081 -0.0617 0.0145 1.0000
12.250 1.2702 0.08172 0.07615 -0.0624 0.0145 1.0000
12.500 1.2523 0.08741 0.08208 -0.0640 0.0145 1.0000
12.750 1.2332 0.09379 0.08870 -0.0667 0.0146 1.0000
13.000 1.2126 0.10110 0.09625 -0.0707 0.0148 1.0000
13.250 1.1905 0.10957 0.10494 -0.0760 0.0149 1.0000
13.500 1.1662 0.11969 0.11526 -0.0828 0.0153 1.0000
13.750 1.1357 0.13363 0.12937 -0.0927 0.0159 1.0000
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Polar data table (+)
Polar graphs
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