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MH 20 9.01% (mh20-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: MH 20 9.01% (mh20-il)
Reynolds number: 100,000
Max Cl/Cd: 50.15 at α=5.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-mh20-il-100000-n5.txt
Download as CSV file: xf-mh20-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MH 20  9.01%                                    
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.5234   0.12261   0.11791   0.0103   1.0000   0.0237
 -10.250  -0.5178   0.11855   0.11387   0.0092   1.0000   0.0219
 -10.000  -0.5141   0.11442   0.10977   0.0073   1.0000   0.0207
  -9.750  -0.5114   0.11007   0.10546   0.0052   1.0000   0.0195
  -9.500  -0.5105   0.10527   0.10071   0.0027   1.0000   0.0183
  -9.250  -0.5114   0.09996   0.09547  -0.0004   1.0000   0.0171
  -9.000  -0.5125   0.09399   0.08958  -0.0045   1.0000   0.0159
  -8.500  -0.5067   0.08562   0.08126  -0.0094   1.0000   0.0150
  -8.250  -0.5084   0.08099   0.07670  -0.0124   1.0000   0.0148
  -8.000  -0.5121   0.07602   0.07181  -0.0165   1.0000   0.0146
  -7.750  -0.5153   0.07108   0.06688  -0.0201   1.0000   0.0145
  -7.500  -0.5149   0.06588   0.06166  -0.0236   1.0000   0.0142
  -7.250  -0.5131   0.06049   0.05619  -0.0264   1.0000   0.0140
  -7.000  -0.5091   0.05520   0.05076  -0.0284   1.0000   0.0138
  -6.750  -0.5030   0.05025   0.04560  -0.0297   1.0000   0.0136
  -6.500  -0.4953   0.04547   0.04054  -0.0303   1.0000   0.0134
  -6.250  -0.4862   0.04116   0.03590  -0.0302   0.9994   0.0132
  -6.000  -0.4629   0.03614   0.03027  -0.0320   0.9644   0.0131
  -5.750  -0.4381   0.03218   0.02569  -0.0329   0.9457   0.0129
  -5.500  -0.4136   0.02887   0.02177  -0.0329   0.9305   0.0130
  -5.250  -0.3893   0.02625   0.01850  -0.0322   0.9170   0.0132
  -5.000  -0.3651   0.02412   0.01593  -0.0313   0.9047   0.0135
  -4.750  -0.3409   0.02243   0.01389  -0.0302   0.8934   0.0141
  -4.500  -0.3174   0.02105   0.01226  -0.0292   0.8831   0.0160
  -4.250  -0.2948   0.01993   0.01100  -0.0282   0.8738   0.0200
  -4.000  -0.2714   0.01892   0.00977  -0.0270   0.8642   0.0238
  -3.750  -0.2487   0.01775   0.00847  -0.0257   0.8554   0.0334
  -3.500  -0.2271   0.01655   0.00762  -0.0245   0.8478   0.0923
  -3.250  -0.2036   0.01581   0.00711  -0.0238   0.8393   0.1596
  -3.000  -0.1800   0.01523   0.00671  -0.0231   0.8321   0.2273
  -2.750  -0.1565   0.01463   0.00628  -0.0223   0.8246   0.3119
  -2.500  -0.1336   0.01394   0.00600  -0.0214   0.8177   0.4330
  -2.250  -0.1110   0.01309   0.00582  -0.0200   0.8109   0.6189
  -2.000  -0.0451   0.01249   0.00576  -0.0257   0.8075   0.8713
  -1.750   0.0118   0.01258   0.00562  -0.0310   0.8012   0.9433
  -1.500   0.0557   0.01267   0.00541  -0.0340   0.7952   0.9796
  -1.250   0.1053   0.01260   0.00512  -0.0386   0.7880   1.0000
  -1.000   0.1277   0.01262   0.00496  -0.0376   0.7809   1.0000
  -0.750   0.1518   0.01266   0.00486  -0.0371   0.7723   1.0000
  -0.500   0.1751   0.01270   0.00473  -0.0362   0.7650   1.0000
  -0.250   0.1989   0.01276   0.00468  -0.0355   0.7570   1.0000
   0.000   0.2229   0.01282   0.00464  -0.0348   0.7490   1.0000
   0.250   0.2465   0.01289   0.00460  -0.0339   0.7417   1.0000
   0.500   0.2710   0.01297   0.00463  -0.0334   0.7332   1.0000
   0.750   0.2949   0.01304   0.00461  -0.0325   0.7260   1.0000
   1.000   0.3194   0.01313   0.00466  -0.0319   0.7172   1.0000
   1.250   0.3439   0.01323   0.00472  -0.0312   0.7090   1.0000
   1.500   0.3680   0.01330   0.00475  -0.0304   0.7011   1.0000
   1.750   0.3928   0.01341   0.00487  -0.0298   0.6916   1.0000
   2.000   0.4173   0.01350   0.00495  -0.0291   0.6828   1.0000
   2.250   0.4417   0.01358   0.00501  -0.0283   0.6740   1.0000
   2.500   0.4664   0.01369   0.00515  -0.0277   0.6634   1.0000
   2.750   0.4911   0.01380   0.00528  -0.0270   0.6529   1.0000
   3.000   0.5156   0.01389   0.00546  -0.0263   0.6423   1.0000
   3.250   0.5402   0.01398   0.00558  -0.0255   0.6311   1.0000
   3.500   0.5648   0.01407   0.00572  -0.0247   0.6190   1.0000
   3.750   0.5894   0.01417   0.00589  -0.0240   0.6055   1.0000
   4.000   0.6141   0.01427   0.00609  -0.0233   0.5902   1.0000
   4.250   0.6386   0.01439   0.00636  -0.0226   0.5734   1.0000
   4.500   0.6630   0.01448   0.00654  -0.0217   0.5552   1.0000
   4.750   0.6872   0.01461   0.00675  -0.0209   0.5343   1.0000
   5.000   0.7111   0.01474   0.00694  -0.0200   0.5113   1.0000
   5.250   0.7347   0.01493   0.00716  -0.0190   0.4855   1.0000
   5.500   0.7577   0.01520   0.00745  -0.0180   0.4568   1.0000
   5.750   0.7803   0.01556   0.00791  -0.0170   0.4257   1.0000
   6.000   0.8019   0.01602   0.00834  -0.0159   0.3917   1.0000
   6.250   0.8226   0.01660   0.00886  -0.0148   0.3509   1.0000
   6.500   0.8417   0.01733   0.00946  -0.0136   0.2992   1.0000
   6.750   0.8584   0.01833   0.01019  -0.0124   0.2325   1.0000
   7.000   0.8722   0.01972   0.01114  -0.0110   0.1525   1.0000
   7.250   0.8836   0.02149   0.01243  -0.0094   0.0803   1.0000
   7.500   0.8935   0.02347   0.01411  -0.0073   0.0425   1.0000
   7.750   0.9034   0.02533   0.01596  -0.0052   0.0286   1.0000
   8.000   0.9147   0.02689   0.01764  -0.0033   0.0212   1.0000
   8.250   0.9213   0.02883   0.01967  -0.0010   0.0172   1.0000
   8.500   0.9286   0.03074   0.02173   0.0014   0.0159   1.0000
   8.750   0.9391   0.03252   0.02370   0.0035   0.0142   1.0000
   9.000   0.9502   0.03414   0.02550   0.0052   0.0122   1.0000
   9.250   0.9597   0.03584   0.02734   0.0069   0.0109   1.0000
   9.500   0.9645   0.03767   0.02942   0.0089   0.0098   1.0000
   9.750   0.9704   0.03990   0.03183   0.0107   0.0094   1.0000
  10.000   0.9729   0.04318   0.03535   0.0126   0.0089   1.0000
  10.250   0.9733   0.04662   0.03904   0.0142   0.0087   1.0000
  10.500   0.9721   0.04947   0.04217   0.0156   0.0086   1.0000
  10.750   0.9679   0.05264   0.04561   0.0166   0.0085   1.0000
  11.000   0.9619   0.05604   0.04925   0.0170   0.0086   1.0000
  11.250   0.9525   0.05984   0.05330   0.0170   0.0085   1.0000
  11.500   0.9408   0.06408   0.05779   0.0163   0.0084   1.0000
  11.750   0.9289   0.06858   0.06250   0.0149   0.0085   1.0000
  12.000   0.9144   0.07377   0.06789   0.0128   0.0085   1.0000
  12.250   0.9011   0.07914   0.07342   0.0102   0.0086   1.0000
  12.500   0.8850   0.08544   0.07989   0.0067   0.0086   1.0000
  12.750   0.8697   0.09217   0.08676   0.0027   0.0087   1.0000
  13.000   0.8535   0.09975   0.09447  -0.0020   0.0087   1.0000
  13.500   0.7249   0.10979   0.10509  -0.0040   0.0096   1.0000
  13.750   0.6892   0.12262   0.11798  -0.0108   0.0110   1.0000
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