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MH 24 9.01% (mh24-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: MH 24 9.01% (mh24-il)
Reynolds number: 500,000
Max Cl/Cd: 79.5 at α=3.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-mh24-il-500000.txt
Download as CSV file: xf-mh24-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MH 24  9.01%                                    
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.4776   0.08597   0.08382  -0.0351   1.0000   0.0151
  -8.750  -0.4894   0.08263   0.08051  -0.0352   1.0000   0.0151
  -8.500  -0.5054   0.07905   0.07697  -0.0362   1.0000   0.0151
  -8.250  -0.5259   0.07610   0.07402  -0.0350   1.0000   0.0150
  -8.000  -0.5484   0.07421   0.07212  -0.0312   1.0000   0.0150
  -7.750  -0.5639   0.07139   0.06926  -0.0285   1.0000   0.0150
  -7.500  -0.5718   0.06786   0.06566  -0.0271   0.9996   0.0151
  -7.250  -0.5622   0.06274   0.06039  -0.0296   0.9970   0.0151
  -7.000  -0.5509   0.05773   0.05519  -0.0315   0.9945   0.0151
  -6.750  -0.5413   0.05349   0.05075  -0.0319   0.9916   0.0152
  -6.500  -0.5304   0.04940   0.04642  -0.0318   0.9882   0.0152
  -6.250  -0.5335   0.04018   0.03676  -0.0316   0.9843   0.0160
  -6.000  -0.5157   0.03642   0.03280  -0.0323   0.9825   0.0169
  -5.750  -0.4992   0.03411   0.03035  -0.0315   0.9795   0.0177
  -5.500  -0.4823   0.03188   0.02792  -0.0304   0.9757   0.0188
  -5.250  -0.4593   0.02952   0.02530  -0.0301   0.9731   0.0203
  -5.000  -0.4313   0.02732   0.02275  -0.0301   0.9712   0.0228
  -4.750  -0.3942   0.02821   0.02333  -0.0309   0.9698   0.0252
  -4.000  -0.3275   0.01708   0.01113  -0.0260   0.9611   0.0125
  -3.750  -0.2965   0.01507   0.00889  -0.0260   0.9596   0.0104
  -3.500  -0.2644   0.01375   0.00742  -0.0265   0.9581   0.0094
  -3.250  -0.2303   0.01295   0.00652  -0.0277   0.9567   0.0089
  -3.000  -0.2059   0.01236   0.00584  -0.0268   0.9528   0.0090
  -2.750  -0.1788   0.01193   0.00529  -0.0265   0.9488   0.0090
  -2.500  -0.1439   0.01149   0.00471  -0.0278   0.9467   0.0114
  -2.250  -0.1128   0.01026   0.00426  -0.0290   0.9448   0.2028
  -2.000  -0.0926   0.00841   0.00401  -0.0284   0.9426   0.6108
  -1.750  -0.0869   0.00769   0.00416  -0.0230   0.9350   0.8271
  -1.500  -0.0540   0.00804   0.00467  -0.0226   0.9333   0.9212
  -1.250  -0.0154   0.00813   0.00467  -0.0244   0.9317   0.9320
  -1.000   0.0241   0.00822   0.00469  -0.0264   0.9303   0.9410
  -0.750   0.0739   0.00830   0.00472  -0.0307   0.9296   0.9450
  -0.500   0.1369   0.00844   0.00480  -0.0379   0.9298   0.9498
  -0.250   0.1711   0.00849   0.00483  -0.0389   0.9248   0.9567
   0.000   0.2182   0.00842   0.00473  -0.0429   0.9217   0.9588
   0.250   0.2605   0.00828   0.00458  -0.0458   0.9181   0.9612
   0.500   0.2953   0.00818   0.00448  -0.0471   0.9127   0.9654
   0.750   0.3261   0.00806   0.00435  -0.0476   0.9053   0.9701
   1.000   0.3669   0.00789   0.00418  -0.0502   0.8985   0.9726
   1.250   0.4032   0.00770   0.00400  -0.0519   0.8900   0.9757
   1.500   0.4323   0.00759   0.00390  -0.0521   0.8775   0.9800
   1.750   0.4637   0.00741   0.00373  -0.0528   0.8622   0.9830
   2.000   0.4980   0.00719   0.00350  -0.0541   0.8377   0.9851
   2.250   0.5304   0.00705   0.00325  -0.0549   0.7986   0.9874
   2.500   0.5592   0.00712   0.00312  -0.0550   0.7425   0.9900
   2.750   0.5841   0.00740   0.00310  -0.0544   0.6749   0.9928
   3.000   0.6102   0.00771   0.00312  -0.0543   0.6047   0.9950
   3.250   0.6376   0.00802   0.00317  -0.0545   0.5365   0.9971
   3.500   0.6644   0.00840   0.00329  -0.0548   0.4654   0.9991
   3.750   0.6871   0.00881   0.00344  -0.0541   0.4012   1.0000
   4.000   0.7055   0.00923   0.00363  -0.0525   0.3457   1.0000
   4.250   0.7241   0.00963   0.00384  -0.0510   0.2958   1.0000
   4.500   0.7418   0.01012   0.00408  -0.0494   0.2374   1.0000
   4.750   0.7596   0.01062   0.00434  -0.0477   0.1857   1.0000
   5.000   0.7778   0.01106   0.00462  -0.0461   0.1466   1.0000
   5.250   0.7962   0.01148   0.00497  -0.0446   0.1149   1.0000
   5.500   0.8138   0.01195   0.00531  -0.0428   0.0849   1.0000
   5.750   0.8308   0.01247   0.00570  -0.0410   0.0584   1.0000
   6.000   0.8476   0.01298   0.00611  -0.0391   0.0386   1.0000
   6.250   0.8636   0.01355   0.00668  -0.0369   0.0274   1.0000
   6.500   0.8804   0.01399   0.00713  -0.0350   0.0214   1.0000
   6.750   0.8975   0.01437   0.00754  -0.0330   0.0176   1.0000
   7.000   0.9104   0.01510   0.00835  -0.0303   0.0134   1.0000
   7.250   0.9197   0.01616   0.00950  -0.0267   0.0065   1.0000
   7.500   0.9303   0.01700   0.01047  -0.0234   0.0059   1.0000
   7.750   0.9391   0.01793   0.01154  -0.0198   0.0054   1.0000
   8.000   0.9471   0.01895   0.01270  -0.0161   0.0050   1.0000
   8.250   0.9540   0.02014   0.01404  -0.0122   0.0049   1.0000
   8.500   0.9615   0.02141   0.01553  -0.0085   0.0048   1.0000
   8.750   0.9685   0.02306   0.01740  -0.0048   0.0048   1.0000
   9.000   0.9754   0.02501   0.01959  -0.0012   0.0048   1.0000
   9.250   0.9796   0.02759   0.02250   0.0028   0.0049   1.0000
   9.500   0.9797   0.03064   0.02592   0.0071   0.0051   1.0000
   9.750   0.9738   0.03407   0.02974   0.0120   0.0053   1.0000
  10.000   0.9647   0.03691   0.03288   0.0171   0.0055   1.0000
  10.250   0.9493   0.03987   0.03611   0.0225   0.0057   1.0000
  10.500   0.9290   0.04337   0.03989   0.0275   0.0059   1.0000
  10.750   0.9142   0.04628   0.04300   0.0308   0.0060   1.0000
  11.000   0.8913   0.05026   0.04720   0.0335   0.0061   1.0000
  11.250   0.8743   0.05388   0.05099   0.0346   0.0062   1.0000
  11.500   0.8515   0.05886   0.05614   0.0341   0.0063   1.0000
  11.750   0.8362   0.06365   0.06108   0.0320   0.0063   1.0000
  12.000   0.8153   0.07062   0.06820   0.0275   0.0063   1.0000
  12.250   0.7967   0.07911   0.07681   0.0211   0.0063   1.0000
  12.500   0.7814   0.08856   0.08636   0.0143   0.0062   1.0000
  12.750   0.7571   0.10202   0.09987   0.0070   0.0063   1.0000
  13.000   0.7341   0.11375   0.11152   0.0021   0.0065   1.0000
  13.250   0.7203   0.12235   0.12008  -0.0017   0.0067   1.0000
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