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MH 121 8.76% (mh121-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: MH 121 8.76% (mh121-il)
Reynolds number: 100,000
Max Cl/Cd: 53.56 at α=5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-mh121-il-100000.txt
Download as CSV file: xf-mh121-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MH 121  8.76%                                   
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.4282   0.10718   0.10242  -0.0378   1.0000   0.0762
  -8.750  -0.4396   0.10509   0.10043  -0.0387   1.0000   0.0770
  -8.500  -0.4545   0.10319   0.09866  -0.0391   1.0000   0.0774
  -8.250  -0.4446   0.09865   0.09414  -0.0359   1.0000   0.0806
  -8.000  -0.4448   0.09626   0.09179  -0.0337   1.0000   0.0835
  -7.750  -0.4544   0.09417   0.08979  -0.0322   1.0000   0.0858
  -7.500  -0.4712   0.09236   0.08808  -0.0305   1.0000   0.0878
  -7.250  -0.4910   0.09081   0.08663  -0.0287   1.0000   0.0888
  -7.000  -0.5095   0.08805   0.08397  -0.0313   1.0000   0.0900
  -6.750  -0.5230   0.08366   0.07956  -0.0379   1.0000   0.0906
  -6.500  -0.5181   0.08084   0.07686  -0.0309   1.0000   0.0940
  -6.250  -0.5174   0.07802   0.07406  -0.0299   1.0000   0.0981
  -6.000  -0.5261   0.07202   0.06759  -0.0451   1.0000   0.1044
  -5.750  -0.5173   0.06887   0.06484  -0.0366   1.0000   0.1082
  -5.500  -0.5107   0.06367   0.05937  -0.0432   1.0000   0.1188
  -5.250  -0.5014   0.06109   0.05691  -0.0402   1.0000   0.1262
  -5.000  -0.4893   0.05717   0.05289  -0.0421   1.0000   0.1392
  -4.750  -0.4744   0.05308   0.04864  -0.0450   1.0000   0.1601
  -4.000  -0.3477   0.03303   0.02547  -0.0579   1.0000   0.0535
  -3.750  -0.3189   0.03012   0.02224  -0.0581   1.0000   0.0477
  -3.500  -0.2884   0.02738   0.01898  -0.0582   1.0000   0.0438
  -3.250  -0.2592   0.02532   0.01647  -0.0578   1.0000   0.0420
  -3.000  -0.2319   0.02366   0.01462  -0.0573   1.0000   0.0424
  -2.750  -0.2053   0.02233   0.01323  -0.0569   1.0000   0.0448
  -2.500  -0.1787   0.02126   0.01219  -0.0569   1.0000   0.0590
  -2.250  -0.1385   0.01753   0.01084  -0.0596   1.0000   0.5497
  -2.000  -0.1256   0.01785   0.01137  -0.0555   1.0000   0.6679
  -1.750  -0.1094   0.01803   0.01150  -0.0527   1.0000   0.7150
  -1.500  -0.0958   0.01814   0.01162  -0.0493   1.0000   0.7584
  -1.250  -0.0847   0.01817   0.01170  -0.0454   1.0000   0.8025
  -1.000  -0.0716   0.01813   0.01156  -0.0422   1.0000   0.8416
  -0.750  -0.0546   0.01805   0.01144  -0.0403   1.0000   0.8766
  -0.500  -0.0320   0.01776   0.01117  -0.0399   1.0000   0.9446
  -0.250   0.0000   0.01776   0.01095  -0.0429   1.0000   1.0000
   0.000   0.0328   0.01814   0.01109  -0.0456   1.0000   1.0000
   0.250   0.0616   0.01856   0.01129  -0.0472   1.0000   1.0000
   0.500   0.0877   0.01900   0.01149  -0.0481   1.0000   1.0000
   0.750   0.1123   0.01946   0.01181  -0.0487   1.0000   1.0000
   1.000   0.1436   0.02009   0.01234  -0.0505   0.9968   1.0000
   1.250   0.1836   0.02090   0.01305  -0.0540   0.9893   1.0000
   1.500   0.2250   0.02180   0.01389  -0.0576   0.9825   1.0000
   1.750   0.2601   0.02237   0.01445  -0.0600   0.9740   1.0000
   2.000   0.2983   0.02307   0.01513  -0.0629   0.9660   1.0000
   2.250   0.3376   0.02373   0.01580  -0.0660   0.9577   1.0000
   2.500   0.3713   0.02421   0.01633  -0.0679   0.9478   1.0000
   2.750   0.4077   0.02474   0.01697  -0.0702   0.9379   1.0000
   3.000   0.4481   0.02526   0.01759  -0.0732   0.9283   1.0000
   3.250   0.4917   0.02570   0.01814  -0.0765   0.9184   1.0000
   3.500   0.5300   0.02596   0.01855  -0.0787   0.9061   1.0000
   3.750   0.5728   0.02607   0.01885  -0.0814   0.8931   1.0000
   4.000   0.6256   0.02578   0.01893  -0.0852   0.8789   1.0000
   4.250   0.6744   0.02485   0.01831  -0.0875   0.8570   1.0000
   4.500   0.7558   0.02191   0.01589  -0.0927   0.8305   1.0000
   4.750   0.8391   0.01728   0.01185  -0.0957   0.7821   1.0000
   5.000   0.8715   0.01627   0.00915  -0.0900   0.3626   1.0000
   5.250   0.8613   0.02024   0.01116  -0.0837   0.1208   1.0000
   5.500   0.8680   0.02311   0.01341  -0.0801   0.0505   1.0000
   5.750   0.8885   0.02636   0.01648  -0.0784   0.0368   1.0000
   6.000   0.9144   0.02770   0.01804  -0.0775   0.0288   1.0000
   6.250   0.9467   0.03130   0.02174  -0.0781   0.0243   1.0000
   6.500   0.9776   0.03462   0.02546  -0.0778   0.0239   1.0000
   6.750   1.0025   0.03834   0.02963  -0.0766   0.0241   1.0000
   7.000   1.0214   0.04280   0.03453  -0.0749   0.0246   1.0000
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