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MH 115 11.06% (mh115-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: MH 115 11.06% (mh115-il)
Reynolds number: 200,000
Max Cl/Cd: 90 at α=4.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-mh115-il-200000-n5.txt
Download as CSV file: xf-mh115-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MH 115  11.06%                                  
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.1413   0.08859   0.08503  -0.0769   0.9610   0.0130
  -8.250  -0.1298   0.08545   0.08190  -0.0792   0.9546   0.0128
  -8.000  -0.1165   0.08188   0.07833  -0.0825   0.9490   0.0124
  -7.750  -0.1046   0.07780   0.07426  -0.0864   0.9431   0.0121
  -7.500  -0.0940   0.07371   0.07018  -0.0902   0.9355   0.0117
  -7.250  -0.0838   0.06892   0.06540  -0.0951   0.9278   0.0113
  -7.000  -0.0777   0.05795   0.05442  -0.1082   0.9175   0.0102
  -6.750  -0.0639   0.05017   0.04659  -0.1194   0.9057   0.0101
  -6.500  -0.0444   0.03414   0.03001  -0.1395   0.8936   0.0097
  -6.250  -0.0128   0.02500   0.01971  -0.1493   0.8875   0.0097
  -6.000   0.0136   0.02171   0.01576  -0.1510   0.8795   0.0099
  -5.750   0.0462   0.01955   0.01315  -0.1530   0.8743   0.0104
  -5.500   0.0765   0.01844   0.01184  -0.1541   0.8681   0.0111
  -5.250   0.1062   0.01737   0.01053  -0.1548   0.8613   0.0119
  -4.750   0.1664   0.01594   0.00876  -0.1561   0.8482   0.0161
  -4.500   0.1983   0.01518   0.00788  -0.1571   0.8425   0.0185
  -4.250   0.2267   0.01453   0.00712  -0.1573   0.8349   0.0220
  -4.000   0.2573   0.01404   0.00656  -0.1580   0.8284   0.0286
  -3.750   0.2865   0.01362   0.00605  -0.1583   0.8213   0.0375
  -3.500   0.3160   0.01321   0.00561  -0.1587   0.8141   0.0485
  -3.250   0.3454   0.01286   0.00524  -0.1590   0.8073   0.0621
  -3.000   0.3743   0.01257   0.00491  -0.1593   0.7997   0.0796
  -2.750   0.4038   0.01228   0.00463  -0.1596   0.7930   0.1041
  -2.500   0.4320   0.01206   0.00444  -0.1598   0.7852   0.1345
  -2.250   0.4614   0.01184   0.00427  -0.1601   0.7785   0.1739
  -2.000   0.4891   0.01166   0.00416  -0.1602   0.7705   0.2188
  -1.750   0.5183   0.01149   0.00405  -0.1605   0.7636   0.2682
  -1.500   0.5458   0.01134   0.00401  -0.1605   0.7553   0.3191
  -1.250   0.5745   0.01121   0.00394  -0.1607   0.7483   0.3743
  -1.000   0.6017   0.01110   0.00395  -0.1606   0.7400   0.4319
  -0.750   0.6297   0.01100   0.00394  -0.1606   0.7328   0.4932
  -0.500   0.6562   0.01092   0.00398  -0.1602   0.7244   0.5539
  -0.250   0.6829   0.01084   0.00400  -0.1598   0.7170   0.6152
   0.000   0.7080   0.01078   0.00406  -0.1591   0.7084   0.6754
   0.250   0.7324   0.01072   0.00409  -0.1581   0.7008   0.7368
   0.500   0.7542   0.01065   0.00413  -0.1564   0.6924   0.8019
   0.750   0.7732   0.01053   0.00409  -0.1541   0.6844   0.8859
   1.000   0.8015   0.01050   0.00402  -0.1540   0.6758   1.0000
   1.250   0.8290   0.01062   0.00406  -0.1540   0.6672   1.0000
   1.500   0.8567   0.01076   0.00409  -0.1539   0.6586   1.0000
   1.750   0.8835   0.01090   0.00417  -0.1537   0.6492   1.0000
   2.000   0.9107   0.01105   0.00423  -0.1536   0.6404   1.0000
   2.250   0.9371   0.01120   0.00433  -0.1533   0.6305   1.0000
   2.500   0.9636   0.01135   0.00443  -0.1531   0.6208   1.0000
   2.750   0.9900   0.01153   0.00453  -0.1528   0.6111   1.0000
   3.000   1.0157   0.01169   0.00467  -0.1524   0.6003   1.0000
   3.250   1.0414   0.01187   0.00481  -0.1520   0.5896   1.0000
   3.500   1.0669   0.01207   0.00495  -0.1515   0.5788   1.0000
   3.750   1.0919   0.01227   0.00513  -0.1510   0.5671   1.0000
   4.000   1.1167   0.01248   0.00531  -0.1505   0.5549   1.0000
   4.250   1.1412   0.01271   0.00551  -0.1499   0.5426   1.0000
   4.500   1.1653   0.01295   0.00573  -0.1492   0.5299   1.0000
   4.750   1.1889   0.01321   0.00595  -0.1484   0.5165   1.0000
   5.000   1.2121   0.01349   0.00619  -0.1476   0.5027   1.0000
   5.250   1.2347   0.01379   0.00646  -0.1467   0.4881   1.0000
   5.500   1.2568   0.01411   0.00676  -0.1457   0.4732   1.0000
   5.750   1.2784   0.01445   0.00707  -0.1446   0.4578   1.0000
   6.000   1.2993   0.01481   0.00740  -0.1434   0.4418   1.0000
   6.250   1.3196   0.01520   0.00778  -0.1421   0.4255   1.0000
   6.500   1.3390   0.01562   0.00817  -0.1407   0.4087   1.0000
   6.750   1.3577   0.01608   0.00859  -0.1392   0.3918   1.0000
   7.000   1.3754   0.01656   0.00904  -0.1376   0.3749   1.0000
   7.250   1.3920   0.01707   0.00952  -0.1357   0.3584   1.0000
   7.500   1.4069   0.01760   0.01003  -0.1336   0.3421   1.0000
   7.750   1.4215   0.01816   0.01057  -0.1314   0.3267   1.0000
   8.000   1.4357   0.01875   0.01115  -0.1293   0.3117   1.0000
   8.250   1.4495   0.01938   0.01179  -0.1271   0.2971   1.0000
   8.500   1.4627   0.02006   0.01246  -0.1249   0.2829   1.0000
   8.750   1.4753   0.02078   0.01318  -0.1227   0.2686   1.0000
   9.000   1.4874   0.02155   0.01396  -0.1205   0.2550   1.0000
   9.250   1.4988   0.02238   0.01481  -0.1183   0.2416   1.0000
   9.500   1.5095   0.02328   0.01572  -0.1161   0.2287   1.0000
   9.750   1.5195   0.02425   0.01670  -0.1139   0.2161   1.0000
  10.250   1.5383   0.02639   0.01889  -0.1096   0.1913   1.0000
  10.500   1.5473   0.02755   0.02010  -0.1076   0.1796   1.0000
  10.750   1.5552   0.02883   0.02141  -0.1055   0.1682   1.0000
  11.000   1.5620   0.03023   0.02284  -0.1035   0.1572   1.0000
  11.250   1.5676   0.03178   0.02440  -0.1016   0.1464   1.0000
  11.500   1.5733   0.03339   0.02604  -0.0997   0.1353   1.0000
  11.750   1.5787   0.03508   0.02777  -0.0980   0.1247   1.0000
  12.000   1.5829   0.03694   0.02967  -0.0964   0.1147   1.0000
  12.250   1.5857   0.03898   0.03174  -0.0948   0.1055   1.0000
  12.500   1.5886   0.04110   0.03389  -0.0934   0.0967   1.0000
  12.750   1.5923   0.04320   0.03607  -0.0921   0.0889   1.0000
  13.000   1.5933   0.04564   0.03855  -0.0909   0.0822   1.0000
  13.250   1.5964   0.04796   0.04095  -0.0899   0.0754   1.0000
  13.500   1.5973   0.05059   0.04366  -0.0890   0.0696   1.0000
  13.750   1.5986   0.05326   0.04642  -0.0883   0.0636   1.0000
  14.000   1.5986   0.05617   0.04943  -0.0877   0.0581   1.0000
  14.250   1.5977   0.05929   0.05263  -0.0873   0.0525   1.0000
  14.500   1.5969   0.06250   0.05593  -0.0870   0.0472   1.0000
  14.750   1.5928   0.06622   0.05971  -0.0869   0.0421   1.0000
  15.000   1.5904   0.06984   0.06343  -0.0870   0.0369   1.0000
  15.250   1.5855   0.07392   0.06761  -0.0873   0.0326   1.0000
  15.500   1.5791   0.07834   0.07210  -0.0878   0.0286   1.0000
  15.750   1.5732   0.08281   0.07669  -0.0885   0.0253   1.0000
  16.250   1.5579   0.09268   0.08679  -0.0908   0.0202   1.0000
  16.500   1.5486   0.09808   0.09229  -0.0924   0.0184   1.0000
  16.750   1.5403   0.10343   0.09780  -0.0941   0.0167   1.0000
  17.000   1.5315   0.10897   0.10348  -0.0960   0.0154   1.0000
  17.250   1.5208   0.11500   0.10962  -0.0984   0.0144   1.0000
  17.500   1.5121   0.12074   0.11553  -0.1008   0.0134   1.0000
  17.750   1.5033   0.12659   0.12153  -0.1035   0.0124   1.0000
  18.000   1.4932   0.13278   0.12785  -0.1065   0.0116   1.0000
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