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MH 113 14.62% (mh113-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: MH 113 14.62% (mh113-il)
Reynolds number: 50,000
Max Cl/Cd: 20.31 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-mh113-il-50000-n5.txt
Download as CSV file: xf-mh113-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MH 113  14.62%                                  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.0876   0.12015   0.11346  -0.0754   0.9225   0.1167
  -8.250  -0.0796   0.11739   0.11070  -0.0780   0.9173   0.1184
  -8.000  -0.0770   0.11506   0.10840  -0.0797   0.9112   0.1196
  -7.750  -0.0702   0.11213   0.10549  -0.0798   0.9044   0.1168
  -7.500  -0.0723   0.10502   0.09829  -0.0855   0.8991   0.0696
  -7.250  -0.0767   0.10303   0.09635  -0.0840   0.8905   0.0673
  -7.000  -0.0885   0.09896   0.09230  -0.0871   0.8832   0.0622
  -6.750  -0.0911   0.09731   0.09068  -0.0853   0.8751   0.0614
  -6.500  -0.0908   0.09475   0.08815  -0.0856   0.8682   0.0607
  -6.250  -0.0879   0.09161   0.08503  -0.0874   0.8620   0.0603
  -6.000  -0.0950   0.08926   0.08274  -0.0870   0.8526   0.0600
  -5.750  -0.0831   0.08482   0.07827  -0.0919   0.8478   0.0596
  -5.500  -0.0941   0.08253   0.07603  -0.0913   0.8374   0.0593
  -5.250  -0.0798   0.07717   0.07059  -0.0978   0.8321   0.0592
  -5.000  -0.0777   0.07298   0.06635  -0.1011   0.8237   0.0586
  -4.750  -0.0595   0.06673   0.05987  -0.1087   0.8176   0.0583
  -4.500  -0.0223   0.05913   0.05176  -0.1198   0.8142   0.0577
  -4.250  -0.0001   0.05474   0.04691  -0.1246   0.8070   0.0578
  -4.000   0.0356   0.05065   0.04222  -0.1301   0.8021   0.0587
  -3.750   0.0804   0.04695   0.03773  -0.1358   0.7988   0.0616
  -3.500   0.1217   0.04497   0.03546  -0.1392   0.7961   0.0656
  -3.250   0.1361   0.04433   0.03458  -0.1383   0.7872   0.0680
  -3.000   0.1733   0.04260   0.03230  -0.1404   0.7830   0.0720
  -2.750   0.2113   0.04148   0.03109  -0.1424   0.7798   0.0793
  -2.500   0.2274   0.04127   0.03076  -0.1412   0.7715   0.0848
  -2.250   0.2579   0.04057   0.02991  -0.1419   0.7663   0.0958
  -2.000   0.2959   0.03968   0.02899  -0.1436   0.7630   0.1139
  -1.750   0.3123   0.03982   0.02912  -0.1426   0.7544   0.1319
  -1.500   0.3449   0.03934   0.02865  -0.1437   0.7492   0.1666
  -1.250   0.3851   0.03860   0.02802  -0.1458   0.7459   0.2205
  -1.000   0.4001   0.03907   0.02860  -0.1447   0.7366   0.2633
  -0.750   0.4328   0.03879   0.02851  -0.1456   0.7316   0.3314
  -0.500   0.4707   0.03829   0.02818  -0.1468   0.7284   0.4133
  -0.250   0.4796   0.03915   0.02920  -0.1446   0.7178   0.4639
   0.000   0.5105   0.03889   0.02908  -0.1445   0.7134   0.5421
   0.250   0.5420   0.03841   0.02873  -0.1440   0.7101   0.6221
   0.500   0.5444   0.03942   0.02988  -0.1405   0.6987   0.6763
   0.750   0.5674   0.03879   0.02940  -0.1381   0.6949   0.7702
   1.000   0.5614   0.03935   0.03017  -0.1330   0.6833   0.9589
   1.250   0.6008   0.03934   0.02979  -0.1349   0.6790   1.0000
   1.750   0.6485   0.04067   0.03067  -0.1350   0.6637   1.0000
   2.000   0.6871   0.04043   0.03018  -0.1362   0.6605   1.0000
   2.250   0.6938   0.04204   0.03169  -0.1346   0.6484   1.0000
   2.500   0.7299   0.04186   0.03130  -0.1354   0.6447   1.0000
   3.000   0.7713   0.04335   0.03255  -0.1343   0.6289   1.0000
   3.250   0.8097   0.04285   0.03189  -0.1351   0.6262   1.0000
   3.500   0.8112   0.04494   0.03396  -0.1331   0.6131   1.0000
   3.750   0.8485   0.04442   0.03330  -0.1337   0.6101   1.0000
   4.000   0.8503   0.04658   0.03544  -0.1318   0.5974   1.0000
   4.250   0.8859   0.04611   0.03488  -0.1321   0.5940   1.0000
   4.750   0.9221   0.04791   0.03658  -0.1305   0.5779   1.0000
   5.250   0.9571   0.04981   0.03843  -0.1288   0.5617   1.0000
   5.500   0.9951   0.04899   0.03755  -0.1291   0.5592   1.0000
   5.750   0.9902   0.05191   0.04050  -0.1271   0.5456   1.0000
   6.000   1.0276   0.05105   0.03961  -0.1273   0.5428   1.0000
   6.250   1.0218   0.05417   0.04276  -0.1254   0.5294   1.0000
   6.500   1.0580   0.05335   0.04191  -0.1254   0.5264   1.0000
   7.000   1.0867   0.05583   0.04444  -0.1234   0.5100   1.0000
   7.500   1.1136   0.05854   0.04721  -0.1215   0.4936   1.0000
   8.000   1.1377   0.06161   0.05037  -0.1197   0.4771   1.0000
   8.500   1.1598   0.06495   0.05380  -0.1179   0.4606   1.0000
   8.750   1.1963   0.06373   0.05259  -0.1175   0.4579   1.0000
   9.250   1.2126   0.06769   0.05670  -0.1156   0.4408   1.0000
   9.750   1.2275   0.07193   0.06108  -0.1139   0.4239   1.0000
  10.250   1.2399   0.07660   0.06591  -0.1124   0.4072   1.0000
  10.750   1.2515   0.08147   0.07094  -0.1111   0.3906   1.0000
  11.250   1.2614   0.08666   0.07632  -0.1101   0.3742   1.0000
  11.750   1.2687   0.09236   0.08220  -0.1094   0.3580   1.0000
  12.250   1.2784   0.09776   0.08779  -0.1089   0.3424   1.0000
  12.750   1.2791   0.10472   0.09495  -0.1090   0.3257   1.0000
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