MH 150 23.89% (mh150-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 150 23.89% (mh150-il) Reynolds number: 100,000 Max Cl/Cd: 14.2 at α=0.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh150-il-100000.txt Download as CSV file: xf-mh150-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: MH 150 23.89%
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.500 -0.0683 0.13136 0.12641 -0.0889 0.9602 0.1583
-13.250 -0.0871 0.12220 0.11719 -0.0940 0.9526 0.1466
-13.000 -0.0929 0.11552 0.11046 -0.0989 0.9468 0.1506
-12.750 -0.0675 0.11457 0.10947 -0.0998 0.9369 0.1591
-12.500 -0.0778 0.10847 0.10332 -0.1035 0.9293 0.1638
-12.250 -0.0544 0.10806 0.10287 -0.1032 0.9191 0.1716
-12.000 -0.0615 0.10346 0.09822 -0.1053 0.9103 0.1771
-11.750 -0.0616 0.10004 0.09476 -0.1064 0.9019 0.1830
-11.500 -0.4823 0.04398 0.03824 -0.1384 0.8870 0.1938
-11.000 -0.4249 0.04578 0.04020 -0.1360 0.8696 0.2117
-10.750 -0.1135 0.08082 0.07537 -0.1145 0.8677 0.2100
-10.500 -0.0362 0.08888 0.08336 -0.1071 0.8573 0.2141
-10.250 -0.0264 0.08737 0.08181 -0.1069 0.8483 0.2206
-10.000 -0.4030 0.04375 0.03800 -0.1336 0.8318 0.2415
-9.750 -0.0131 0.08341 0.07775 -0.1071 0.8325 0.2331
-9.500 -0.0842 0.07171 0.06604 -0.1147 0.8258 0.2433
-9.250 -0.0232 0.07663 0.07084 -0.1088 0.8193 0.2464
-9.000 -0.1009 0.06486 0.05910 -0.1174 0.8100 0.2597
-8.750 -0.2625 0.04628 0.04042 -0.1286 0.7987 0.2794
-8.500 -0.1284 0.05664 0.05075 -0.1200 0.7966 0.2785
-8.250 -0.0661 0.06206 0.05616 -0.1156 0.7873 0.2793
-8.000 -0.0078 0.06583 0.05983 -0.1114 0.7806 0.2817
-7.750 0.0269 0.06680 0.06069 -0.1089 0.7754 0.2872
-7.500 -0.1750 0.04613 0.04004 -0.1247 0.7605 0.3146
-7.250 -0.0990 0.05164 0.04557 -0.1174 0.7571 0.3144
-7.000 -0.0060 0.05794 0.05175 -0.1113 0.7538 0.3129
-6.750 -0.1311 0.04381 0.03747 -0.1252 0.7394 0.3384
-6.500 -0.0854 0.04635 0.04007 -0.1205 0.7354 0.3402
-6.250 -0.0701 0.04233 0.03572 -0.1270 0.7313 0.3559
-6.000 -0.0688 0.04328 0.03676 -0.1236 0.7200 0.3595
-5.750 -0.0350 0.04509 0.03862 -0.1193 0.7152 0.3617
-5.500 -0.0093 0.04092 0.03407 -0.1277 0.7110 0.3785
-5.250 0.0075 0.04222 0.03545 -0.1237 0.7045 0.3810
-5.000 0.0175 0.04374 0.03707 -0.1192 0.6955 0.3835
-4.750 0.0569 0.04021 0.03315 -0.1280 0.6913 0.3995
-4.500 0.0872 0.04072 0.03369 -0.1249 0.6884 0.4026
-4.250 0.0791 0.04248 0.03559 -0.1203 0.6771 0.4050
-4.000 0.1049 0.04272 0.03581 -0.1186 0.6722 0.4099
-3.750 0.1533 0.03982 0.03257 -0.1265 0.6690 0.4235
-3.500 0.1847 0.04003 0.03277 -0.1242 0.6664 0.4271
-3.250 0.1684 0.04187 0.03475 -0.1205 0.6534 0.4305
-3.000 0.2236 0.03945 0.03200 -0.1289 0.6501 0.4440
-2.750 0.2524 0.03942 0.03197 -0.1268 0.6472 0.4478
-2.500 0.2871 0.03916 0.03166 -0.1260 0.6449 0.4527
-2.250 0.2716 0.04105 0.03364 -0.1243 0.6311 0.4579
-2.000 0.3240 0.03944 0.03182 -0.1297 0.6284 0.4679
-1.750 0.3551 0.03921 0.03157 -0.1285 0.6259 0.4723
-1.500 0.3272 0.04243 0.03495 -0.1248 0.6123 0.4752
-1.250 0.3901 0.04070 0.03293 -0.1323 0.6095 0.4878
-1.000 0.4207 0.04022 0.03247 -0.1308 0.6070 0.4920
-0.750 0.4576 0.03961 0.03181 -0.1306 0.6049 0.4977
-0.500 0.5224 0.03799 0.02989 -0.1378 0.6032 0.5105
0.000 0.4421 0.04706 0.03937 -0.1284 0.5764 0.5137
0.250 0.5019 0.04451 0.03677 -0.1287 0.5783 0.5214
0.500 0.5879 0.04140 0.03340 -0.1355 0.5799 0.5350
0.750 0.4154 0.05852 0.05102 -0.1269 0.5484 0.5262
1.000 0.4590 0.05789 0.05028 -0.1294 0.5457 0.5359
1.250 0.4909 0.05718 0.04960 -0.1280 0.5439 0.5421
1.500 0.5414 0.05571 0.04802 -0.1300 0.5429 0.5543
1.750 0.5811 0.05423 0.04653 -0.1292 0.5421 0.5620
2.000 0.6224 0.05264 0.04492 -0.1286 0.5416 0.5708
2.250 0.6751 0.05090 0.04307 -0.1306 0.5411 0.5828
2.500 0.4613 0.07630 0.06897 -0.1276 0.5111 0.5674
2.750 0.4781 0.07849 0.07113 -0.1290 0.5076 0.5764
3.000 0.5080 0.07875 0.07139 -0.1289 0.5049 0.5845
3.250 0.5443 0.07803 0.07067 -0.1279 0.5029 0.5940
3.500 0.5938 0.07668 0.06925 -0.1286 0.5015 0.6069
3.750 0.4966 0.09096 0.08372 -0.1306 0.4942 0.6035
4.000 0.4518 0.10022 0.09316 -0.1323 0.5090 0.6036
4.250 0.4749 0.10091 0.09393 -0.1305 0.5052 0.6103
4.500 0.5012 0.10250 0.09552 -0.1306 0.5034 0.6204
4.750 0.5282 0.10454 0.09756 -0.1315 0.5023 0.6303
5.000 0.5465 0.10681 0.09988 -0.1308 0.5016 0.6378
5.250 0.5734 0.10991 0.10294 -0.1329 0.5011 0.6505
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Polar data table (+)
Polar graphs
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