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MH 150 23.89% (mh150-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
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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