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MH 64 8.59% (mh64-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: MH 64 8.59% (mh64-il)
Reynolds number: 100,000
Max Cl/Cd: 44.81 at α=5.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-mh64-il-100000.txt
Download as CSV file: xf-mh64-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MH 64  8.59%                                    
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.4681   0.11689   0.11261   0.0140   1.0000   0.0864
  -9.750  -0.4746   0.11318   0.10893   0.0110   1.0000   0.0900
  -9.500  -0.4949   0.10971   0.10554   0.0053   1.0000   0.0915
  -9.250  -0.4743   0.10410   0.09993   0.0076   1.0000   0.0939
  -9.000  -0.4637   0.10021   0.09604   0.0078   1.0000   0.0972
  -8.750  -0.4646   0.09608   0.09195   0.0059   1.0000   0.1014
  -8.500  -0.4931   0.09206   0.08803  -0.0014   1.0000   0.1047
  -8.250  -0.4755   0.08669   0.08267   0.0006   1.0000   0.1070
  -8.000  -0.4647   0.08284   0.07884   0.0011   1.0000   0.1107
  -7.750  -0.5642   0.08545   0.08128  -0.0038   1.0000   0.1067
  -7.500  -0.5495   0.08225   0.07809  -0.0020   1.0000   0.1103
  -7.250  -0.4776   0.06932   0.06550  -0.0056   1.0000   0.1226
  -7.000  -0.5508   0.07245   0.06833  -0.0123   1.0000   0.1211
  -6.750  -0.5398   0.06876   0.06464  -0.0132   1.0000   0.1257
  -6.500  -0.5361   0.06366   0.05946  -0.0179   1.0000   0.1348
  -6.250  -0.5288   0.05925   0.05490  -0.0215   1.0000   0.1468
  -6.000  -0.5139   0.04010   0.03426  -0.0283   1.0000   0.0473
  -5.750  -0.4925   0.03554   0.02873  -0.0275   1.0000   0.0394
  -5.500  -0.4728   0.03149   0.02433  -0.0271   1.0000   0.0378
  -5.250  -0.4505   0.02840   0.02079  -0.0264   1.0000   0.0371
  -5.000  -0.4265   0.02637   0.01828  -0.0255   1.0000   0.0391
  -4.750  -0.4037   0.02386   0.01542  -0.0246   1.0000   0.0413
  -4.500  -0.3819   0.02168   0.01317  -0.0236   1.0000   0.0436
  -4.250  -0.3617   0.02002   0.01144  -0.0219   1.0000   0.0470
  -4.000  -0.3438   0.01873   0.00999  -0.0198   1.0000   0.0516
  -3.750  -0.3287   0.01740   0.00872  -0.0177   1.0000   0.0663
  -3.500  -0.3166   0.01497   0.00708  -0.0152   1.0000   0.1617
  -3.250  -0.3041   0.01373   0.00680  -0.0131   1.0000   0.3649
  -3.000  -0.2888   0.01335   0.00670  -0.0111   1.0000   0.4534
  -2.750  -0.2730   0.01298   0.00663  -0.0091   1.0000   0.5368
  -2.500  -0.2565   0.01261   0.00656  -0.0069   1.0000   0.6233
  -2.250  -0.2402   0.01224   0.00655  -0.0042   1.0000   0.7278
  -2.000  -0.1713   0.01188   0.00645  -0.0102   1.0000   0.9476
  -1.750  -0.1143   0.01197   0.00614  -0.0171   0.9972   1.0000
  -1.500  -0.0608   0.01215   0.00601  -0.0231   0.9857   1.0000
  -1.250  -0.0073   0.01231   0.00590  -0.0288   0.9746   1.0000
  -1.000   0.0487   0.01242   0.00581  -0.0348   0.9642   1.0000
  -0.750   0.1050   0.01246   0.00570  -0.0406   0.9538   1.0000
  -0.500   0.1534   0.01249   0.00559  -0.0447   0.9410   1.0000
  -0.250   0.1916   0.01257   0.00559  -0.0466   0.9254   1.0000
   0.000   0.2223   0.01270   0.00565  -0.0469   0.9086   1.0000
   0.250   0.2480   0.01286   0.00574  -0.0461   0.8916   1.0000
   0.500   0.2701   0.01303   0.00583  -0.0443   0.8751   1.0000
   0.750   0.2898   0.01321   0.00596  -0.0422   0.8576   1.0000
   1.000   0.3094   0.01338   0.00607  -0.0400   0.8399   1.0000
   1.250   0.3291   0.01351   0.00615  -0.0377   0.8230   1.0000
   1.500   0.3489   0.01362   0.00622  -0.0353   0.8067   1.0000
   1.750   0.3698   0.01374   0.00631  -0.0334   0.7884   1.0000
   2.000   0.3910   0.01382   0.00635  -0.0314   0.7702   1.0000
   2.250   0.4124   0.01386   0.00634  -0.0293   0.7528   1.0000
   2.500   0.4348   0.01393   0.00639  -0.0276   0.7329   1.0000
   2.750   0.4575   0.01395   0.00643  -0.0258   0.7132   1.0000
   3.000   0.4807   0.01400   0.00646  -0.0243   0.6921   1.0000
   3.250   0.5041   0.01401   0.00643  -0.0226   0.6708   1.0000
   3.500   0.5280   0.01407   0.00648  -0.0213   0.6464   1.0000
   3.750   0.5522   0.01414   0.00656  -0.0200   0.6212   1.0000
   4.000   0.5765   0.01424   0.00662  -0.0187   0.5945   1.0000
   4.250   0.6009   0.01438   0.00673  -0.0175   0.5661   1.0000
   4.500   0.6254   0.01458   0.00687  -0.0164   0.5365   1.0000
   4.750   0.6498   0.01486   0.00706  -0.0154   0.5062   1.0000
   5.000   0.6742   0.01521   0.00744  -0.0145   0.4725   1.0000
   5.250   0.6983   0.01563   0.00777  -0.0136   0.4393   1.0000
   5.500   0.7224   0.01612   0.00822  -0.0128   0.4041   1.0000
   5.750   0.7460   0.01669   0.00867  -0.0120   0.3698   1.0000
   6.000   0.7694   0.01732   0.00927  -0.0113   0.3331   1.0000
   6.250   0.7924   0.01804   0.00991  -0.0106   0.2979   1.0000
   6.500   0.8149   0.01883   0.01061  -0.0098   0.2634   1.0000
   6.750   0.8370   0.01971   0.01153  -0.0091   0.2298   1.0000
   7.000   0.8585   0.02069   0.01244  -0.0084   0.1973   1.0000
   7.250   0.8788   0.02182   0.01345  -0.0076   0.1658   1.0000
   7.500   0.8985   0.02312   0.01477  -0.0067   0.1341   1.0000
   7.750   0.9168   0.02472   0.01629  -0.0057   0.1054   1.0000
   8.000   0.9343   0.02647   0.01803  -0.0046   0.0818   1.0000
   8.250   0.9531   0.02877   0.02036  -0.0033   0.0670   1.0000
   8.500   0.9706   0.03089   0.02258  -0.0022   0.0549   1.0000
   8.750   0.9886   0.03420   0.02608  -0.0010   0.0480   1.0000
   9.000   1.0038   0.03636   0.02835   0.0000   0.0406   1.0000
   9.250   1.0153   0.04032   0.03278   0.0014   0.0374   1.0000
   9.500   1.0234   0.04418   0.03718   0.0030   0.0361   1.0000
   9.750   1.0251   0.04833   0.04184   0.0046   0.0355   1.0000
  10.000   1.0208   0.05256   0.04651   0.0060   0.0353   1.0000
  10.250   1.0100   0.05665   0.05096   0.0072   0.0348   1.0000
  10.500   0.9934   0.06052   0.05508   0.0085   0.0353   1.0000
  10.750   0.9749   0.06472   0.05949   0.0082   0.0357   1.0000
  11.000   0.9542   0.06968   0.06464   0.0063   0.0360   1.0000
  11.250   0.9348   0.07537   0.07046   0.0031   0.0367   1.0000
  11.500   0.9128   0.08222   0.07744  -0.0017   0.0370   1.0000
  11.750   0.8945   0.08959   0.08489  -0.0067   0.0378   1.0000
  12.000   0.8759   0.09788   0.09322  -0.0122   0.0384   1.0000
  12.250   0.8632   0.10563   0.10096  -0.0162   0.0391   1.0000
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