Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

MH 108 11.98% (mh108-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: MH 108 11.98% (mh108-il)
Reynolds number: 100,000
Max Cl/Cd: 42.15 at α=8.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-mh108-il-100000-n5.txt
Download as CSV file: xf-mh108-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MH 108  11.98%                                  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.500  -0.7964   0.08246   0.07720  -0.0046   1.0000   0.0173
 -12.250  -0.8175   0.07404   0.06865  -0.0107   1.0000   0.0171
 -12.000  -0.8366   0.06675   0.06119  -0.0160   1.0000   0.0170
 -11.750  -0.8553   0.06044   0.05468  -0.0203   1.0000   0.0169
 -11.500  -0.8707   0.05551   0.04952  -0.0229   1.0000   0.0170
 -11.250  -0.8850   0.05135   0.04512  -0.0237   1.0000   0.0170
 -11.000  -0.8964   0.04794   0.04143  -0.0231   1.0000   0.0173
 -10.750  -0.9037   0.04515   0.03845  -0.0215   1.0000   0.0177
 -10.500  -0.9060   0.04308   0.03630  -0.0195   1.0000   0.0182
 -10.250  -0.9040   0.04115   0.03425  -0.0176   1.0000   0.0188
 -10.000  -0.8984   0.03927   0.03219  -0.0159   1.0000   0.0198
  -9.750  -0.8903   0.03725   0.02994  -0.0142   1.0000   0.0209
  -9.500  -0.8801   0.03513   0.02750  -0.0125   1.0000   0.0222
  -9.250  -0.8679   0.03307   0.02518  -0.0108   1.0000   0.0233
  -9.000  -0.8559   0.03130   0.02335  -0.0093   1.0000   0.0246
  -8.750  -0.8408   0.02987   0.02182  -0.0079   1.0000   0.0269
  -8.500  -0.8236   0.02849   0.02020  -0.0065   1.0000   0.0303
  -8.250  -0.8084   0.02705   0.01877  -0.0051   1.0000   0.0338
  -8.000  -0.7902   0.02578   0.01730  -0.0036   1.0000   0.0391
  -7.750  -0.7726   0.02458   0.01613  -0.0024   1.0000   0.0460
  -7.500  -0.7537   0.02347   0.01496  -0.0012   1.0000   0.0548
  -7.250  -0.7337   0.02250   0.01397  -0.0001   1.0000   0.0658
  -7.000  -0.7129   0.02165   0.01311   0.0010   1.0000   0.0785
  -6.750  -0.6917   0.02088   0.01233   0.0019   1.0000   0.0922
  -6.500  -0.6701   0.02017   0.01161   0.0029   1.0000   0.1065
  -6.250  -0.6483   0.01949   0.01093   0.0039   1.0000   0.1212
  -6.000  -0.6263   0.01887   0.01029   0.0048   1.0000   0.1369
  -5.750  -0.6040   0.01829   0.00971   0.0058   1.0000   0.1542
  -5.500  -0.5819   0.01774   0.00919   0.0068   1.0000   0.1717
  -5.250  -0.5601   0.01720   0.00873   0.0078   1.0000   0.1908
  -5.000  -0.5382   0.01672   0.00829   0.0088   1.0000   0.2115
  -4.750  -0.5169   0.01626   0.00790   0.0099   1.0000   0.2337
  -4.500  -0.4959   0.01585   0.00756   0.0110   1.0000   0.2572
  -4.250  -0.4584   0.01538   0.00720   0.0088   0.9649   0.2899
  -4.000  -0.4179   0.01496   0.00686   0.0062   0.9216   0.3274
  -3.750  -0.3805   0.01461   0.00653   0.0045   0.8806   0.3661
  -3.500  -0.3508   0.01435   0.00627   0.0046   0.8415   0.4038
  -3.250  -0.3255   0.01413   0.00605   0.0055   0.8069   0.4405
  -3.000  -0.3016   0.01394   0.00583   0.0068   0.7761   0.4790
  -2.750  -0.2780   0.01374   0.00566   0.0081   0.7481   0.5186
  -2.500  -0.2541   0.01356   0.00552   0.0094   0.7220   0.5607
  -2.250  -0.2296   0.01340   0.00540   0.0106   0.6981   0.6054
  -2.000  -0.2041   0.01327   0.00530   0.0117   0.6758   0.6516
  -1.750  -0.1773   0.01318   0.00525   0.0126   0.6545   0.6984
  -1.500  -0.1488   0.01315   0.00523   0.0132   0.6339   0.7439
  -1.250  -0.1173   0.01319   0.00523   0.0133   0.6145   0.7861
  -1.000  -0.0835   0.01328   0.00527   0.0128   0.5952   0.8233
  -0.750  -0.0472   0.01342   0.00531   0.0118   0.5764   0.8543
  -0.500  -0.0113   0.01359   0.00535   0.0108   0.5588   0.8808
  -0.250   0.0275   0.01378   0.00539   0.0091   0.5417   0.9017
   0.000   0.0648   0.01397   0.00543   0.0076   0.5258   0.9207
   0.250   0.1036   0.01415   0.00547   0.0058   0.5105   0.9367
   0.500   0.1431   0.01432   0.00550   0.0036   0.4957   0.9507
   0.750   0.1832   0.01446   0.00552   0.0013   0.4818   0.9637
   1.000   0.2235   0.01458   0.00552  -0.0013   0.4686   0.9756
   1.250   0.2642   0.01467   0.00552  -0.0040   0.4559   0.9864
   1.500   0.3058   0.01473   0.00549  -0.0069   0.4443   0.9964
   1.750   0.3357   0.01482   0.00546  -0.0076   0.4351   1.0000
   2.000   0.3582   0.01493   0.00555  -0.0068   0.4256   1.0000
   2.250   0.3807   0.01506   0.00562  -0.0060   0.4176   1.0000
   2.500   0.4035   0.01521   0.00573  -0.0051   0.4093   1.0000
   2.750   0.4264   0.01539   0.00587  -0.0043   0.4018   1.0000
   3.000   0.4494   0.01557   0.00602  -0.0035   0.3942   1.0000
   3.250   0.4725   0.01577   0.00621  -0.0027   0.3868   1.0000
   3.500   0.4956   0.01599   0.00640  -0.0018   0.3796   1.0000
   3.750   0.5189   0.01622   0.00664  -0.0010   0.3727   1.0000
   4.000   0.5422   0.01645   0.00688  -0.0002   0.3654   1.0000
   4.250   0.5655   0.01671   0.00714   0.0006   0.3588   1.0000
   4.500   0.5888   0.01697   0.00744   0.0014   0.3514   1.0000
   4.750   0.6121   0.01725   0.00772   0.0022   0.3450   1.0000
   5.000   0.6354   0.01753   0.00806   0.0030   0.3374   1.0000
   5.250   0.6587   0.01782   0.00835   0.0038   0.3311   1.0000
   5.500   0.6819   0.01812   0.00876   0.0046   0.3232   1.0000
   5.750   0.7051   0.01843   0.00906   0.0054   0.3169   1.0000
   6.000   0.7281   0.01875   0.00950   0.0062   0.3088   1.0000
   6.250   0.7511   0.01908   0.00984   0.0071   0.3021   1.0000
   6.500   0.7739   0.01942   0.01032   0.0079   0.2937   1.0000
   6.750   0.7965   0.01976   0.01072   0.0088   0.2864   1.0000
   7.000   0.8190   0.02011   0.01118   0.0096   0.2779   1.0000
   7.250   0.8412   0.02048   0.01165   0.0105   0.2696   1.0000
   7.500   0.8633   0.02082   0.01207   0.0114   0.2613   1.0000
   7.750   0.8849   0.02124   0.01265   0.0124   0.2518   1.0000
   8.000   0.9064   0.02162   0.01311   0.0133   0.2430   1.0000
   8.250   0.9274   0.02203   0.01362   0.0143   0.2332   1.0000
   8.500   0.9480   0.02249   0.01424   0.0153   0.2226   1.0000
   8.750   0.9681   0.02297   0.01485   0.0164   0.2125   1.0000
   9.000   0.9875   0.02347   0.01540   0.0175   0.2021   1.0000
   9.250   1.0063   0.02404   0.01610   0.0186   0.1909   1.0000
   9.500   1.0242   0.02470   0.01687   0.0197   0.1794   1.0000
   9.750   1.0410   0.02544   0.01770   0.0210   0.1681   1.0000
  10.000   1.0563   0.02627   0.01859   0.0223   0.1575   1.0000
  10.250   1.0696   0.02720   0.01955   0.0237   0.1472   1.0000
  10.500   1.0817   0.02823   0.02072   0.0251   0.1369   1.0000
  10.750   1.0920   0.02938   0.02198   0.0266   0.1270   1.0000
  11.000   1.0988   0.03067   0.02332   0.0283   0.1184   1.0000
  11.250   1.1026   0.03208   0.02483   0.0301   0.1102   1.0000
  11.500   1.1016   0.03364   0.02648   0.0323   0.1034   1.0000
  11.750   1.0966   0.03560   0.02852   0.0339   0.0976   1.0000
  12.000   1.0914   0.03805   0.03105   0.0344   0.0923   1.0000
  12.250   1.0854   0.04099   0.03413   0.0340   0.0870   1.0000
  12.500   1.0759   0.04460   0.03776   0.0329   0.0831   1.0000
  12.750   1.0694   0.04823   0.04155   0.0316   0.0786   1.0000
  13.000   1.0597   0.05242   0.04585   0.0298   0.0745   1.0000
  13.250   1.0479   0.05695   0.05040   0.0278   0.0713   1.0000
  13.500   1.0381   0.06142   0.05497   0.0259   0.0678   1.0000
  13.750   1.0274   0.06615   0.05982   0.0238   0.0643   1.0000
  14.000   1.0159   0.07103   0.06476   0.0216   0.0615   1.0000
  14.250   1.0054   0.07569   0.06939   0.0195   0.0589   1.0000
  14.500   0.9955   0.08064   0.07450   0.0173   0.0560   1.0000
  14.750   0.9852   0.08584   0.07981   0.0149   0.0530   1.0000
  15.000   0.9754   0.09108   0.08510   0.0124   0.0504   1.0000
  15.250   0.9688   0.09564   0.08962   0.0103   0.0479   1.0000
  15.500   0.9584   0.10141   0.09557   0.0076   0.0457   1.0000
  15.750   0.9483   0.10722   0.10151   0.0048   0.0435   1.0000
  16.000   0.9390   0.11296   0.10732   0.0020   0.0412   1.0000
  16.250   0.9333   0.11794   0.11229  -0.0005   0.0390   1.0000
  16.500   0.9261   0.12339   0.11778  -0.0031   0.0373   1.0000
  16.750   0.9116   0.13086   0.12543  -0.0069   0.0361   1.0000
  17.000   0.8942   0.13929   0.13400  -0.0112   0.0351   1.0000
  17.250   0.8614   0.15228   0.14711  -0.0179   0.0346   1.0000
<< Back to MH 108 11.98% (mh108-il)

Polar data table (+)

Polar graphs


<< Back to MH 108 11.98% (mh108-il)