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MH 30 7.84% (mh30-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: MH 30 7.84% (mh30-il)
Reynolds number: 1,000,000
Max Cl/Cd: 84.49 at α=4°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-mh30-il-1000000-n5.txt
Download as CSV file: xf-mh30-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MH 30  7.84%                                    
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.4936   0.09564   0.09402  -0.0146   1.0000   0.0049
  -9.250  -0.4881   0.09258   0.09097  -0.0161   1.0000   0.0060
  -9.000  -0.4884   0.08829   0.08670  -0.0181   1.0000   0.0059
  -8.750  -0.4869   0.08436   0.08279  -0.0200   1.0000   0.0062
  -8.250  -0.4734   0.07813   0.07659  -0.0233   1.0000   0.0073
  -6.250  -0.4356   0.02163   0.01827  -0.0538   0.9569   0.0032
  -6.000  -0.4172   0.01839   0.01458  -0.0527   0.9466   0.0030
  -5.750  -0.3962   0.01609   0.01191  -0.0515   0.9375   0.0029
  -5.500  -0.3738   0.01427   0.00979  -0.0504   0.9291   0.0029
  -5.250  -0.3499   0.01282   0.00807  -0.0496   0.9218   0.0028
  -5.000  -0.3257   0.01165   0.00670  -0.0487   0.9150   0.0027
  -4.750  -0.3008   0.01065   0.00553  -0.0481   0.9081   0.0027
  -4.250  -0.2498   0.00925   0.00386  -0.0469   0.8940   0.0027
  -4.000  -0.2237   0.00875   0.00323  -0.0464   0.8867   0.0027
  -3.750  -0.1971   0.00836   0.00274  -0.0460   0.8784   0.0027
  -3.500  -0.1703   0.00806   0.00233  -0.0456   0.8703   0.0027
  -3.250  -0.1433   0.00783   0.00201  -0.0453   0.8616   0.0029
  -3.000  -0.1160   0.00765   0.00173  -0.0451   0.8528   0.0030
  -2.750  -0.0886   0.00751   0.00152  -0.0449   0.8439   0.0035
  -2.250  -0.0346   0.00708   0.00118  -0.0445   0.8237   0.0402
  -2.000  -0.0079   0.00679   0.00104  -0.0443   0.8125   0.0885
  -1.750   0.0178   0.00633   0.00091  -0.0441   0.7991   0.1908
  -1.500   0.0440   0.00606   0.00081  -0.0439   0.7823   0.2647
  -1.000   0.0970   0.00575   0.00068  -0.0434   0.7420   0.3736
  -0.750   0.1234   0.00563   0.00064  -0.0431   0.7192   0.4306
  -0.500   0.1498   0.00554   0.00060  -0.0429   0.6937   0.4828
  -0.250   0.1760   0.00550   0.00059  -0.0426   0.6660   0.5330
   0.000   0.2022   0.00546   0.00060  -0.0423   0.6369   0.5840
   0.250   0.2282   0.00544   0.00062  -0.0419   0.6076   0.6349
   0.500   0.2541   0.00543   0.00065  -0.0416   0.5797   0.6854
   0.750   0.2797   0.00542   0.00070  -0.0411   0.5513   0.7381
   1.000   0.3050   0.00541   0.00075  -0.0406   0.5235   0.7897
   1.250   0.3298   0.00542   0.00082  -0.0399   0.4941   0.8383
   1.500   0.3539   0.00546   0.00089  -0.0390   0.4637   0.8873
   1.750   0.3802   0.00553   0.00097  -0.0385   0.4336   0.9384
   2.000   0.4189   0.00571   0.00105  -0.0410   0.3998   0.9733
   2.250   0.4552   0.00592   0.00113  -0.0430   0.3661   0.9915
   2.500   0.4876   0.00615   0.00123  -0.0442   0.3339   1.0000
   2.750   0.5127   0.00637   0.00135  -0.0437   0.3052   1.0000
   3.000   0.5379   0.00659   0.00147  -0.0432   0.2777   1.0000
   3.250   0.5633   0.00682   0.00160  -0.0428   0.2524   1.0000
   3.500   0.5885   0.00708   0.00175  -0.0424   0.2237   1.0000
   3.750   0.6139   0.00734   0.00190  -0.0420   0.1987   1.0000
   4.000   0.6396   0.00757   0.00208  -0.0416   0.1789   1.0000
   4.250   0.6647   0.00788   0.00227  -0.0412   0.1516   1.0000
   4.500   0.6894   0.00826   0.00250  -0.0408   0.1182   1.0000
   4.750   0.7143   0.00862   0.00274  -0.0404   0.0924   1.0000
   5.000   0.7382   0.00911   0.00304  -0.0398   0.0576   1.0000
   5.250   0.7626   0.00956   0.00336  -0.0393   0.0339   1.0000
   5.500   0.7877   0.00989   0.00364  -0.0389   0.0231   1.0000
   6.000   0.8381   0.01054   0.00429  -0.0382   0.0113   1.0000
   6.250   0.8628   0.01093   0.00465  -0.0377   0.0054   1.0000
   6.500   0.8869   0.01143   0.00513  -0.0371   0.0016   1.0000
   6.750   0.9117   0.01182   0.00557  -0.0366   0.0013   1.0000
   7.000   0.9363   0.01222   0.00604  -0.0361   0.0012   1.0000
   7.250   0.9607   0.01264   0.00653  -0.0356   0.0012   1.0000
   7.500   0.9844   0.01317   0.00714  -0.0349   0.0011   1.0000
   7.750   1.0078   0.01372   0.00777  -0.0343   0.0011   1.0000
   8.000   1.0304   0.01438   0.00854  -0.0335   0.0011   1.0000
   8.250   1.0525   0.01510   0.00940  -0.0326   0.0011   1.0000
   8.500   1.0736   0.01591   0.01034  -0.0316   0.0010   1.0000
   8.750   1.0941   0.01680   0.01136  -0.0306   0.0010   1.0000
   9.000   1.1134   0.01780   0.01250  -0.0294   0.0010   1.0000
   9.250   1.1314   0.01895   0.01381  -0.0280   0.0010   1.0000
   9.500   1.1481   0.02022   0.01525  -0.0265   0.0010   1.0000
   9.750   1.1632   0.02165   0.01687  -0.0248   0.0010   1.0000
  10.000   1.1763   0.02327   0.01870  -0.0229   0.0010   1.0000
  10.250   1.1871   0.02509   0.02074  -0.0208   0.0010   1.0000
  10.500   1.1952   0.02705   0.02293  -0.0184   0.0010   1.0000
  10.750   1.2008   0.02905   0.02516  -0.0159   0.0010   1.0000
  11.000   1.1990   0.03126   0.02763  -0.0124   0.0010   1.0000
  11.250   1.1915   0.03345   0.03003  -0.0084   0.0011   1.0000
  11.500   1.1797   0.03613   0.03294  -0.0049   0.0011   1.0000
  11.750   1.1651   0.03932   0.03634  -0.0023   0.0011   1.0000
  12.000   1.1568   0.04216   0.03934  -0.0011   0.0011   1.0000
  12.250   1.1432   0.04599   0.04336  -0.0008   0.0011   1.0000
  12.500   1.1258   0.05096   0.04851  -0.0021   0.0011   1.0000
  12.750   1.1105   0.05652   0.05424  -0.0048   0.0011   1.0000
  13.000   1.0860   0.06490   0.06281  -0.0101   0.0011   1.0000
  13.250   1.0697   0.07296   0.07100  -0.0157   0.0011   1.0000
  13.500   1.0461   0.08359   0.08178  -0.0228   0.0011   1.0000
  13.750   1.0341   0.09168   0.08995  -0.0278   0.0011   1.0000
  14.000   1.0110   0.10274   0.10108  -0.0340   0.0011   1.0000
  14.250   0.9852   0.11461   0.11302  -0.0402   0.0011   1.0000
  14.500   0.9616   0.12615   0.12462  -0.0460   0.0011   1.0000
  14.750   0.9352   0.13913   0.13764  -0.0523   0.0011   1.0000
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