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MH 117 9.8% (mh117-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: MH 117 9.8% (mh117-il)
Reynolds number: 1,000,000
Max Cl/Cd: 120.13 at α=3.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-mh117-il-1000000.txt
Download as CSV file: xf-mh117-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MH 117  9.8%                                    
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.6277   0.06356   0.06177  -0.0423   1.0000   0.0037
 -10.500  -0.6394   0.05719   0.05537  -0.0462   1.0000   0.0037
 -10.250  -0.6575   0.04851   0.04662  -0.0526   1.0000   0.0036
 -10.000  -0.6788   0.03932   0.03724  -0.0627   1.0000   0.0036
  -9.750  -0.6878   0.03551   0.03323  -0.0633   1.0000   0.0036
  -9.500  -0.6885   0.03284   0.03036  -0.0624   1.0000   0.0036
  -9.250  -0.6862   0.03056   0.02790  -0.0608   1.0000   0.0036
  -9.000  -0.6754   0.02850   0.02565  -0.0602   0.9995   0.0035
  -8.750  -0.6489   0.02484   0.02159  -0.0636   0.9964   0.0035
  -8.500  -0.6227   0.02091   0.01721  -0.0665   0.9933   0.0035
  -8.250  -0.5940   0.01909   0.01513  -0.0679   0.9895   0.0035
  -8.000  -0.5674   0.01540   0.01096  -0.0697   0.9853   0.0037
  -7.750  -0.5343   0.01402   0.00941  -0.0715   0.9830   0.0040
  -7.500  -0.5034   0.01331   0.00863  -0.0725   0.9785   0.0043
  -7.250  -0.4721   0.01267   0.00791  -0.0735   0.9729   0.0047
  -7.000  -0.4395   0.01202   0.00716  -0.0747   0.9675   0.0051
  -6.750  -0.4096   0.01144   0.00649  -0.0752   0.9583   0.0054
  -6.500  -0.3795   0.01097   0.00594  -0.0757   0.9481   0.0056
  -6.250  -0.3515   0.01029   0.00513  -0.0758   0.9354   0.0059
  -6.000  -0.3250   0.00969   0.00440  -0.0755   0.9212   0.0065
  -5.750  -0.2985   0.00934   0.00393  -0.0751   0.9068   0.0073
  -5.500  -0.2720   0.00908   0.00359  -0.0747   0.8930   0.0085
  -5.250  -0.2466   0.00844   0.00294  -0.0742   0.8795   0.0216
  -5.000  -0.2206   0.00807   0.00265  -0.0738   0.8666   0.0433
  -4.750  -0.1938   0.00789   0.00245  -0.0736   0.8545   0.0557
  -4.500  -0.1668   0.00772   0.00227  -0.0733   0.8426   0.0670
  -4.250  -0.1397   0.00756   0.00210  -0.0732   0.8311   0.0797
  -4.000  -0.1124   0.00741   0.00196  -0.0730   0.8203   0.0948
  -3.750  -0.0851   0.00727   0.00182  -0.0728   0.8098   0.1109
  -3.250  -0.0303   0.00698   0.00156  -0.0725   0.7892   0.1470
  -3.000  -0.0028   0.00686   0.00146  -0.0724   0.7794   0.1683
  -2.750   0.0246   0.00674   0.00136  -0.0723   0.7698   0.1914
  -2.500   0.0522   0.00661   0.00128  -0.0722   0.7599   0.2173
  -2.250   0.0799   0.00650   0.00120  -0.0721   0.7503   0.2450
  -2.000   0.1074   0.00640   0.00114  -0.0720   0.7406   0.2723
  -1.750   0.1350   0.00629   0.00109  -0.0719   0.7305   0.3041
  -1.500   0.1627   0.00618   0.00104  -0.0719   0.7206   0.3407
  -1.250   0.1902   0.00608   0.00101  -0.0718   0.7111   0.3769
  -1.000   0.2177   0.00597   0.00098  -0.0717   0.7013   0.4221
  -0.750   0.2453   0.00585   0.00097  -0.0716   0.6917   0.4673
  -0.500   0.2726   0.00573   0.00096  -0.0715   0.6823   0.5198
  -0.250   0.2998   0.00561   0.00097  -0.0714   0.6726   0.5775
   0.000   0.3271   0.00547   0.00099  -0.0712   0.6629   0.6372
   0.250   0.3539   0.00535   0.00101  -0.0709   0.6534   0.6985
   0.500   0.3801   0.00524   0.00105  -0.0704   0.6433   0.7612
   0.750   0.4059   0.00513   0.00110  -0.0698   0.6332   0.8220
   1.000   0.4303   0.00503   0.00115  -0.0688   0.6233   0.8809
   1.250   0.4539   0.00499   0.00119  -0.0675   0.6129   0.9374
   1.500   0.4899   0.00501   0.00120  -0.0691   0.6012   0.9792
   1.750   0.5291   0.00507   0.00121  -0.0716   0.5886   1.0000
   2.000   0.5556   0.00515   0.00125  -0.0713   0.5761   1.0000
   2.250   0.5822   0.00525   0.00130  -0.0710   0.5631   1.0000
   2.500   0.6089   0.00535   0.00135  -0.0707   0.5490   1.0000
   2.750   0.6355   0.00547   0.00141  -0.0704   0.5333   1.0000
   3.000   0.6621   0.00561   0.00149  -0.0701   0.5165   1.0000
   3.250   0.6887   0.00576   0.00158  -0.0698   0.4963   1.0000
   3.500   0.7148   0.00595   0.00167  -0.0695   0.4725   1.0000
   3.750   0.7407   0.00617   0.00180  -0.0691   0.4450   1.0000
   4.000   0.7662   0.00645   0.00194  -0.0687   0.4105   1.0000
   4.250   0.7911   0.00678   0.00212  -0.0682   0.3738   1.0000
   4.500   0.8164   0.00709   0.00230  -0.0678   0.3428   1.0000
   4.750   0.8415   0.00742   0.00251  -0.0674   0.3124   1.0000
   5.000   0.8662   0.00778   0.00273  -0.0669   0.2796   1.0000
   5.250   0.8911   0.00813   0.00296  -0.0665   0.2515   1.0000
   5.500   0.9160   0.00847   0.00320  -0.0660   0.2262   1.0000
   5.750   0.9405   0.00885   0.00347  -0.0655   0.1995   1.0000
   6.000   0.9650   0.00923   0.00374  -0.0650   0.1761   1.0000
   6.250   0.9894   0.00961   0.00402  -0.0645   0.1543   1.0000
   6.500   1.0136   0.01000   0.00433  -0.0640   0.1335   1.0000
   6.750   1.0374   0.01042   0.00465  -0.0634   0.1146   1.0000
   7.000   1.0612   0.01084   0.00500  -0.0628   0.0974   1.0000
   7.250   1.0850   0.01124   0.00535  -0.0623   0.0840   1.0000
   7.500   1.1086   0.01166   0.00572  -0.0616   0.0722   1.0000
   7.750   1.1317   0.01210   0.00611  -0.0610   0.0616   1.0000
   8.000   1.1551   0.01251   0.00649  -0.0603   0.0530   1.0000
   8.250   1.1782   0.01292   0.00687  -0.0597   0.0452   1.0000
   8.500   1.2005   0.01340   0.00732  -0.0589   0.0373   1.0000
   8.750   1.2232   0.01383   0.00773  -0.0582   0.0321   1.0000
   9.000   1.2453   0.01429   0.00818  -0.0574   0.0271   1.0000
   9.250   1.2671   0.01476   0.00864  -0.0566   0.0231   1.0000
   9.500   1.2883   0.01526   0.00914  -0.0557   0.0194   1.0000
   9.750   1.3089   0.01578   0.00966  -0.0547   0.0160   1.0000
  10.000   1.3287   0.01635   0.01024  -0.0536   0.0125   1.0000
  10.250   1.3467   0.01704   0.01091  -0.0523   0.0088   1.0000
  10.500   1.3628   0.01784   0.01174  -0.0506   0.0056   1.0000
  10.750   1.3767   0.01877   0.01270  -0.0487   0.0037   1.0000
  11.000   1.3919   0.01952   0.01353  -0.0469   0.0032   1.0000
  11.250   1.4035   0.02029   0.01436  -0.0445   0.0027   1.0000
  11.500   1.4103   0.02131   0.01548  -0.0415   0.0024   1.0000
  11.750   1.4174   0.02234   0.01661  -0.0387   0.0022   1.0000
  12.000   1.4277   0.02317   0.01752  -0.0365   0.0021   1.0000
  12.250   1.4355   0.02421   0.01865  -0.0342   0.0020   1.0000
  12.500   1.4442   0.02522   0.01973  -0.0322   0.0017   1.0000
  12.750   1.4511   0.02641   0.02100  -0.0303   0.0017   1.0000
  13.000   1.4565   0.02778   0.02249  -0.0284   0.0016   1.0000
  13.250   1.4577   0.02958   0.02440  -0.0264   0.0014   1.0000
  13.500   1.4577   0.03158   0.02652  -0.0247   0.0014   1.0000
  13.750   1.4599   0.03352   0.02856  -0.0234   0.0014   1.0000
  14.000   1.4310   0.03866   0.03398  -0.0216   0.0012   1.0000
  14.250   1.4339   0.04088   0.03629  -0.0211   0.0012   1.0000
  14.500   1.4204   0.04509   0.04068  -0.0210   0.0012   1.0000
  14.750   1.4140   0.04872   0.04444  -0.0213   0.0012   1.0000
  15.000   1.4099   0.05227   0.04811  -0.0219   0.0012   1.0000
  15.250   1.4011   0.05665   0.05263  -0.0229   0.0011   1.0000
  15.500   1.3903   0.06156   0.05768  -0.0245   0.0011   1.0000
  15.750   1.3779   0.06707   0.06333  -0.0266   0.0011   1.0000
  16.000   1.3673   0.07261   0.06900  -0.0290   0.0011   1.0000
  16.250   1.3509   0.07951   0.07606  -0.0323   0.0011   1.0000
  16.500   1.3324   0.08716   0.08387  -0.0362   0.0011   1.0000
  16.750   1.3146   0.09512   0.09197  -0.0404   0.0011   1.0000
  17.000   1.2937   0.10401   0.10102  -0.0453   0.0011   1.0000
  17.250   1.2746   0.11282   0.10997  -0.0502   0.0011   1.0000
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