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MH 44 9.66% (mh44-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: MH 44 9.66% (mh44-il)
Reynolds number: 1,000,000
Max Cl/Cd: 87.33 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-mh44-il-1000000-n5.txt
Download as CSV file: xf-mh44-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MH 44  9.66%                                    
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.7188   0.07434   0.07281  -0.0098   1.0000   0.0021
 -10.750  -0.7173   0.07044   0.06895  -0.0124   1.0000   0.0022
 -10.250  -0.7962   0.04367   0.04181  -0.0307   1.0000   0.0019
 -10.000  -0.8174   0.03927   0.03719  -0.0291   1.0000   0.0019
  -9.750  -0.8613   0.02958   0.02669  -0.0261   1.0000   0.0020
  -9.500  -0.8551   0.02647   0.02324  -0.0246   1.0000   0.0021
  -9.250  -0.8404   0.02454   0.02109  -0.0236   0.9989   0.0022
  -9.000  -0.8143   0.02294   0.01926  -0.0245   0.9556   0.0023
  -8.750  -0.7969   0.02165   0.01774  -0.0232   0.9322   0.0023
  -8.500  -0.7772   0.02088   0.01681  -0.0220   0.9170   0.0024
  -8.250  -0.7588   0.01955   0.01525  -0.0207   0.9048   0.0025
  -8.000  -0.7382   0.01850   0.01401  -0.0196   0.8948   0.0025
  -7.750  -0.7164   0.01763   0.01297  -0.0186   0.8858   0.0026
  -7.500  -0.6941   0.01671   0.01188  -0.0178   0.8774   0.0027
  -7.250  -0.6716   0.01579   0.01079  -0.0169   0.8698   0.0028
  -7.000  -0.6484   0.01494   0.00977  -0.0161   0.8621   0.0028
  -6.750  -0.6244   0.01425   0.00896  -0.0154   0.8550   0.0029
  -6.500  -0.6003   0.01356   0.00814  -0.0147   0.8477   0.0030
  -6.250  -0.5760   0.01292   0.00738  -0.0140   0.8411   0.0030
  -6.000  -0.5512   0.01232   0.00668  -0.0134   0.8339   0.0031
  -5.750  -0.5257   0.01188   0.00616  -0.0129   0.8273   0.0032
  -5.500  -0.4997   0.01152   0.00572  -0.0125   0.8201   0.0034
  -5.250  -0.4739   0.01112   0.00524  -0.0120   0.8135   0.0035
  -5.000  -0.4478   0.01075   0.00480  -0.0116   0.8058   0.0036
  -4.750  -0.4218   0.01035   0.00433  -0.0112   0.7985   0.0037
  -4.500  -0.3960   0.00989   0.00377  -0.0106   0.7900   0.0037
  -4.250  -0.3698   0.00950   0.00330  -0.0102   0.7813   0.0039
  -4.000  -0.3432   0.00921   0.00292  -0.0098   0.7718   0.0041
  -3.750  -0.3164   0.00897   0.00262  -0.0095   0.7608   0.0046
  -3.500  -0.2893   0.00877   0.00236  -0.0092   0.7490   0.0054
  -3.250  -0.2624   0.00857   0.00212  -0.0089   0.7363   0.0084
  -3.000  -0.2357   0.00834   0.00190  -0.0086   0.7226   0.0210
  -2.750  -0.2091   0.00811   0.00170  -0.0083   0.7084   0.0410
  -2.500  -0.1842   0.00764   0.00146  -0.0078   0.6938   0.1104
  -2.250  -0.1588   0.00728   0.00131  -0.0074   0.6786   0.1766
  -2.000  -0.1323   0.00709   0.00120  -0.0071   0.6632   0.2166
  -1.750  -0.1056   0.00695   0.00111  -0.0069   0.6476   0.2521
  -1.250  -0.0523   0.00667   0.00097  -0.0063   0.6159   0.3312
  -1.000  -0.0253   0.00659   0.00092  -0.0061   0.5993   0.3601
  -0.750   0.0018   0.00653   0.00087  -0.0059   0.5826   0.3897
  -0.500   0.0287   0.00647   0.00084  -0.0057   0.5656   0.4203
  -0.250   0.0556   0.00642   0.00082  -0.0055   0.5480   0.4532
   0.000   0.0823   0.00637   0.00080  -0.0053   0.5302   0.4882
   0.250   0.1089   0.00631   0.00080  -0.0050   0.5127   0.5260
   0.500   0.1353   0.00626   0.00080  -0.0047   0.4948   0.5660
   0.750   0.1614   0.00620   0.00081  -0.0043   0.4775   0.6102
   1.000   0.1869   0.00612   0.00083  -0.0038   0.4612   0.6601
   1.250   0.2118   0.00602   0.00086  -0.0032   0.4453   0.7160
   1.500   0.2356   0.00589   0.00090  -0.0022   0.4294   0.7806
   1.750   0.2590   0.00574   0.00095  -0.0011   0.4134   0.8547
   2.000   0.3049   0.00570   0.00106  -0.0050   0.3931   0.9348
   2.250   0.3648   0.00588   0.00115  -0.0123   0.3680   0.9590
   2.500   0.4017   0.00606   0.00126  -0.0143   0.3489   0.9718
   2.750   0.4319   0.00624   0.00136  -0.0148   0.3310   0.9822
   3.000   0.4643   0.00641   0.00146  -0.0158   0.3113   0.9888
   3.250   0.4967   0.00662   0.00158  -0.0169   0.2911   0.9933
   3.500   0.5317   0.00680   0.00169  -0.0186   0.2720   0.9962
   3.750   0.5669   0.00702   0.00180  -0.0204   0.2488   0.9986
   4.000   0.6003   0.00722   0.00193  -0.0217   0.2277   1.0000
   4.250   0.6256   0.00742   0.00207  -0.0213   0.2115   1.0000
   4.500   0.6507   0.00765   0.00222  -0.0208   0.1940   1.0000
   4.750   0.6759   0.00787   0.00238  -0.0204   0.1777   1.0000
   5.000   0.7010   0.00812   0.00256  -0.0199   0.1603   1.0000
   5.250   0.7261   0.00835   0.00275  -0.0195   0.1472   1.0000
   5.500   0.7510   0.00860   0.00295  -0.0190   0.1334   1.0000
   5.750   0.7757   0.00889   0.00318  -0.0185   0.1180   1.0000
   6.000   0.8002   0.00919   0.00342  -0.0180   0.1031   1.0000
   6.250   0.8249   0.00946   0.00367  -0.0175   0.0924   1.0000
   6.500   0.8492   0.00980   0.00394  -0.0169   0.0788   1.0000
   6.750   0.8732   0.01015   0.00423  -0.0164   0.0663   1.0000
   7.000   0.8975   0.01046   0.00452  -0.0158   0.0582   1.0000
   7.250   0.9215   0.01081   0.00484  -0.0152   0.0498   1.0000
   7.500   0.9451   0.01119   0.00520  -0.0146   0.0413   1.0000
   7.750   0.9684   0.01160   0.00557  -0.0140   0.0326   1.0000
   8.000   0.9918   0.01198   0.00594  -0.0133   0.0271   1.0000
   8.250   1.0145   0.01243   0.00636  -0.0126   0.0208   1.0000
   8.500   1.0369   0.01289   0.00680  -0.0119   0.0161   1.0000
   8.750   1.0598   0.01329   0.00721  -0.0112   0.0135   1.0000
   9.000   1.0819   0.01375   0.00768  -0.0104   0.0110   1.0000
   9.250   1.1043   0.01418   0.00815  -0.0096   0.0096   1.0000
   9.500   1.1259   0.01465   0.00863  -0.0088   0.0078   1.0000
   9.750   1.1472   0.01515   0.00915  -0.0080   0.0067   1.0000
  10.000   1.1687   0.01561   0.00966  -0.0071   0.0059   1.0000
  10.250   1.1897   0.01609   0.01018  -0.0063   0.0053   1.0000
  10.500   1.2096   0.01665   0.01078  -0.0053   0.0044   1.0000
  10.750   1.2293   0.01721   0.01138  -0.0042   0.0035   1.0000
  11.250   1.2655   0.01854   0.01280  -0.0019   0.0018   1.0000
  11.500   1.2813   0.01935   0.01366  -0.0005   0.0011   1.0000
  11.750   1.2981   0.02001   0.01439   0.0008   0.0011   1.0000
  12.000   1.3124   0.02082   0.01529   0.0024   0.0008   1.0000
  12.250   1.3241   0.02177   0.01632   0.0043   0.0006   1.0000
  12.500   1.3315   0.02272   0.01736   0.0069   0.0005   1.0000
  12.750   1.3365   0.02376   0.01851   0.0095   0.0005   1.0000
  13.000   1.3435   0.02484   0.01968   0.0114   0.0005   1.0000
  13.250   1.3502   0.02607   0.02101   0.0130   0.0005   1.0000
  13.500   1.3563   0.02746   0.02250   0.0143   0.0004   1.0000
  13.750   1.3601   0.02916   0.02432   0.0154   0.0004   1.0000
  14.000   1.3652   0.03084   0.02610   0.0162   0.0004   1.0000
  14.250   1.3689   0.03278   0.02814   0.0167   0.0004   1.0000
  14.500   1.3681   0.03532   0.03082   0.0169   0.0004   1.0000
  14.750   1.3670   0.03809   0.03372   0.0167   0.0004   1.0000
  15.000   1.3638   0.04129   0.03704   0.0161   0.0004   1.0000
  15.250   1.3626   0.04441   0.04027   0.0151   0.0004   1.0000
  15.500   1.3530   0.04886   0.04487   0.0135   0.0004   1.0000
  15.750   1.3441   0.05342   0.04956   0.0116   0.0004   1.0000
  16.000   1.3310   0.05881   0.05509   0.0091   0.0004   1.0000
  16.250   1.3184   0.06431   0.06072   0.0065   0.0004   1.0000
  16.500   1.3010   0.07078   0.06733   0.0034   0.0004   1.0000
  16.750   1.2806   0.07800   0.07469  -0.0002   0.0004   1.0000
  17.000   1.2488   0.08746   0.08432  -0.0050   0.0004   1.0000
  17.250   1.2316   0.09447   0.09144  -0.0084   0.0004   1.0000
  17.500   1.1972   0.10492   0.10205  -0.0136   0.0004   1.0000
  17.750   1.1682   0.11459   0.11185  -0.0183   0.0004   1.0000
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