GM15 (smoothed) (gm15sm-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GM15 (smoothed) (gm15sm-il) Reynolds number: 200,000 Max Cl/Cd: 86.92 at α=4° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-gm15sm-il-200000-n5.txt Download as CSV file: xf-gm15sm-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.3414 0.10048 0.09696 -0.0295 1.0000 0.0245
-8.000 -0.3429 0.09821 0.09475 -0.0293 1.0000 0.0247
-7.500 -0.3535 0.09432 0.09098 -0.0265 1.0000 0.0248
-6.500 -0.3243 0.08098 0.07775 -0.0362 0.9919 0.0251
-6.250 -0.3037 0.07426 0.07105 -0.0441 0.9868 0.0256
-6.000 -0.2900 0.07158 0.06834 -0.0432 0.9833 0.0227
-5.500 -0.2199 0.05517 0.05178 -0.0678 0.9724 0.0161
-5.250 -0.1803 0.04750 0.04400 -0.0800 0.9674 0.0157
-5.000 -0.1110 0.03040 0.02617 -0.1050 0.9648 0.0149
-4.750 -0.0635 0.02355 0.01836 -0.1139 0.9629 0.0149
-4.500 -0.0258 0.02027 0.01439 -0.1172 0.9603 0.0154
-4.250 0.0067 0.01832 0.01197 -0.1186 0.9561 0.0160
-4.000 0.0414 0.01665 0.00991 -0.1203 0.9531 0.0169
-3.750 0.0770 0.01556 0.00869 -0.1223 0.9506 0.0198
-3.500 0.1144 0.01460 0.00755 -0.1243 0.9486 0.0222
-3.250 0.1447 0.01380 0.00660 -0.1247 0.9431 0.0241
-3.000 0.1795 0.01294 0.00561 -0.1261 0.9391 0.0278
-2.750 0.2163 0.01246 0.00500 -0.1279 0.9359 0.0360
-2.500 0.2468 0.01191 0.00442 -0.1283 0.9296 0.0505
-2.250 0.2800 0.01132 0.00400 -0.1295 0.9241 0.0982
-2.000 0.3121 0.01097 0.00379 -0.1303 0.9181 0.1569
-1.750 0.3424 0.01078 0.00365 -0.1307 0.9104 0.1999
-1.500 0.3721 0.01063 0.00356 -0.1309 0.9021 0.2350
-1.250 0.4038 0.01049 0.00342 -0.1315 0.8942 0.2611
-1.000 0.4314 0.01039 0.00332 -0.1312 0.8832 0.2811
-0.750 0.4601 0.01028 0.00319 -0.1312 0.8720 0.2995
-0.500 0.4891 0.01016 0.00308 -0.1311 0.8599 0.3177
-0.250 0.5180 0.01005 0.00297 -0.1311 0.8465 0.3365
0.000 0.5470 0.00995 0.00287 -0.1310 0.8315 0.3558
0.250 0.5762 0.00985 0.00278 -0.1310 0.8146 0.3761
0.500 0.6053 0.00978 0.00269 -0.1309 0.7956 0.3981
0.750 0.6337 0.00973 0.00263 -0.1308 0.7742 0.4232
1.000 0.6615 0.00971 0.00261 -0.1305 0.7522 0.4524
1.250 0.6880 0.00970 0.00262 -0.1299 0.7298 0.4907
1.500 0.7135 0.00964 0.00266 -0.1292 0.7079 0.5548
2.000 0.7713 0.00925 0.00276 -0.1292 0.6654 1.0000
2.250 0.7968 0.00947 0.00286 -0.1285 0.6454 1.0000
2.500 0.8220 0.00969 0.00298 -0.1278 0.6258 1.0000
2.750 0.8472 0.00992 0.00313 -0.1270 0.6067 1.0000
3.000 0.8721 0.01016 0.00330 -0.1263 0.5883 1.0000
3.250 0.8971 0.01039 0.00352 -0.1256 0.5697 1.0000
3.500 0.9218 0.01064 0.00372 -0.1248 0.5507 1.0000
3.750 0.9464 0.01090 0.00395 -0.1240 0.5326 1.0000
4.000 0.9709 0.01117 0.00419 -0.1233 0.5136 1.0000
4.250 0.9952 0.01145 0.00445 -0.1224 0.4942 1.0000
4.500 1.0192 0.01175 0.00478 -0.1216 0.4746 1.0000
4.750 1.0427 0.01208 0.00509 -0.1206 0.4504 1.0000
5.000 1.0628 0.01260 0.00541 -0.1191 0.4024 1.0000
5.250 1.0802 0.01337 0.00580 -0.1172 0.3320 1.0000
5.500 1.0988 0.01417 0.00629 -0.1157 0.2703 1.0000
5.750 1.1168 0.01511 0.00692 -0.1142 0.2037 1.0000
6.000 1.1316 0.01650 0.00778 -0.1123 0.1114 1.0000
6.250 1.1452 0.01812 0.00891 -0.1103 0.0431 1.0000
6.500 1.1644 0.01906 0.00983 -0.1088 0.0301 1.0000
6.750 1.1844 0.01987 0.01076 -0.1074 0.0252 1.0000
7.000 1.2009 0.02105 0.01206 -0.1054 0.0217 1.0000
7.250 1.2191 0.02198 0.01313 -0.1038 0.0202 1.0000
7.500 1.2371 0.02287 0.01419 -0.1021 0.0180 1.0000
7.750 1.2537 0.02388 0.01530 -0.1004 0.0162 1.0000
8.000 1.2675 0.02516 0.01667 -0.0982 0.0151 1.0000
8.250 1.2770 0.02699 0.01860 -0.0955 0.0141 1.0000
8.500 1.2888 0.02879 0.02052 -0.0931 0.0134 1.0000
8.750 1.3045 0.02999 0.02188 -0.0912 0.0125 1.0000
9.000 1.3194 0.03119 0.02322 -0.0894 0.0113 1.0000
9.250 1.3321 0.03259 0.02476 -0.0872 0.0105 1.0000
9.500 1.3436 0.03425 0.02661 -0.0850 0.0100 1.0000
9.750 1.3540 0.03602 0.02852 -0.0828 0.0096 1.0000
10.000 1.3627 0.03807 0.03072 -0.0804 0.0091 1.0000
10.250 1.3701 0.04084 0.03370 -0.0782 0.0088 1.0000
10.500 1.3738 0.04433 0.03749 -0.0756 0.0086 1.0000
10.750 1.3749 0.04689 0.04035 -0.0728 0.0085 1.0000
11.000 1.3723 0.04972 0.04349 -0.0699 0.0083 1.0000
11.250 1.3665 0.05285 0.04692 -0.0672 0.0083 1.0000
11.500 1.3576 0.05632 0.05069 -0.0648 0.0082 1.0000
11.750 1.3465 0.06009 0.05474 -0.0630 0.0082 1.0000
12.000 1.3334 0.06424 0.05917 -0.0618 0.0081 1.0000
12.250 1.3187 0.06881 0.06400 -0.0615 0.0081 1.0000
12.500 1.3027 0.07390 0.06934 -0.0621 0.0080 1.0000
12.750 1.2859 0.07956 0.07522 -0.0636 0.0080 1.0000
13.000 1.2682 0.08581 0.08170 -0.0660 0.0081 1.0000
13.250 1.2500 0.09272 0.08881 -0.0694 0.0081 1.0000
13.500 1.2314 0.10027 0.09654 -0.0736 0.0081 1.0000
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Polar data table (+)
Polar graphs
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