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MH 23 8% (mh23-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: MH 23 8% (mh23-il)
Reynolds number: 500,000
Max Cl/Cd: 83.85 at α=2.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-mh23-il-500000.txt
Download as CSV file: xf-mh23-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MH 23  8%                                       
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.4087   0.09355   0.09141  -0.0257   1.0000   0.0106
  -9.750  -0.4090   0.08919   0.08707  -0.0272   1.0000   0.0106
  -9.500  -0.4083   0.08552   0.08341  -0.0279   1.0000   0.0111
  -9.250  -0.4091   0.08138   0.07928  -0.0292   1.0000   0.0113
  -9.000  -0.4106   0.07731   0.07523  -0.0303   1.0000   0.0116
  -8.750  -0.4925   0.08004   0.07791  -0.0331   1.0000   0.0102
  -8.500  -0.4921   0.07653   0.07443  -0.0356   1.0000   0.0100
  -8.250  -0.5083   0.07236   0.07030  -0.0377   1.0000   0.0101
  -8.000  -0.5227   0.07107   0.06902  -0.0344   1.0000   0.0099
  -7.750  -0.5359   0.06887   0.06680  -0.0315   1.0000   0.0098
  -7.500  -0.5582   0.06462   0.06250  -0.0290   1.0000   0.0100
  -7.250  -0.5738   0.06064   0.05844  -0.0266   1.0000   0.0103
  -7.000  -0.5805   0.05725   0.05497  -0.0242   1.0000   0.0104
  -6.750  -0.5825   0.05335   0.05095  -0.0231   0.9994   0.0108
  -6.500  -0.5675   0.04985   0.04732  -0.0248   0.9970   0.0116
  -6.250  -0.5487   0.04582   0.04306  -0.0264   0.9947   0.0122
  -6.000  -0.5305   0.04257   0.03962  -0.0272   0.9923   0.0137
  -5.750  -0.5119   0.03889   0.03570  -0.0272   0.9892   0.0153
  -5.500  -0.4767   0.03845   0.03492  -0.0270   0.9869   0.0196
  -5.250  -0.4526   0.03551   0.03163  -0.0273   0.9844   0.0197
  -5.000  -0.4395   0.02768   0.02329  -0.0274   0.9820   0.0216
  -4.750  -0.4194   0.02575   0.02125  -0.0266   0.9785   0.0230
  -4.500  -0.3950   0.02394   0.01922  -0.0262   0.9752   0.0250
  -4.250  -0.3653   0.02246   0.01747  -0.0263   0.9730   0.0282
  -4.000  -0.3367   0.02002   0.01462  -0.0266   0.9711   0.0334
  -3.750  -0.3014   0.01625   0.01045  -0.0256   0.9702   0.0155
  -3.500  -0.2672   0.01412   0.00804  -0.0259   0.9693   0.0117
  -3.250  -0.2437   0.01339   0.00718  -0.0247   0.9649   0.0106
  -3.000  -0.2133   0.01273   0.00646  -0.0250   0.9618   0.0100
  -2.750  -0.1802   0.01197   0.00563  -0.0260   0.9596   0.0097
  -2.500  -0.1449   0.01113   0.00466  -0.0274   0.9578   0.0098
  -2.250  -0.1058   0.01058   0.00389  -0.0296   0.9566   0.0118
  -2.000  -0.0855   0.00951   0.00354  -0.0283   0.9513   0.1964
  -1.750  -0.0687   0.00795   0.00336  -0.0267   0.9465   0.5637
  -1.500  -0.0191   0.00719   0.00389  -0.0301   0.9483   0.9339
  -1.250   0.0253   0.00729   0.00391  -0.0332   0.9468   0.9475
  -1.000   0.0683   0.00736   0.00390  -0.0361   0.9450   0.9566
  -0.750   0.1192   0.00737   0.00384  -0.0407   0.9438   0.9615
  -0.500   0.1620   0.00743   0.00386  -0.0436   0.9409   0.9700
  -0.250   0.2096   0.00739   0.00379  -0.0477   0.9372   0.9751
   0.000   0.2433   0.00734   0.00372  -0.0487   0.9319   0.9813
   0.250   0.2836   0.00715   0.00352  -0.0512   0.9266   0.9841
   0.500   0.3209   0.00696   0.00332  -0.0532   0.9193   0.9880
   0.750   0.3554   0.00681   0.00317  -0.0545   0.9112   0.9926
   1.000   0.3926   0.00657   0.00292  -0.0564   0.9025   0.9964
   1.250   0.4281   0.00634   0.00271  -0.0580   0.8902   1.0000
   1.500   0.4483   0.00623   0.00259  -0.0563   0.8730   1.0000
   1.750   0.4689   0.00611   0.00246  -0.0546   0.8506   1.0000
   2.000   0.4898   0.00603   0.00232  -0.0530   0.8170   1.0000
   2.250   0.5098   0.00608   0.00215  -0.0511   0.7636   1.0000
   2.500   0.5294   0.00632   0.00212  -0.0492   0.7009   1.0000
   2.750   0.5487   0.00666   0.00222  -0.0475   0.6331   1.0000
   3.000   0.5682   0.00703   0.00233  -0.0459   0.5660   1.0000
   3.250   0.5879   0.00743   0.00246  -0.0444   0.4997   1.0000
   3.500   0.6080   0.00783   0.00262  -0.0431   0.4376   1.0000
   3.750   0.6283   0.00824   0.00280  -0.0418   0.3767   1.0000
   4.000   0.6490   0.00864   0.00303  -0.0406   0.3237   1.0000
   4.250   0.6691   0.00910   0.00325  -0.0394   0.2649   1.0000
   4.500   0.6886   0.00963   0.00351  -0.0381   0.2023   1.0000
   4.750   0.7090   0.01008   0.00378  -0.0369   0.1593   1.0000
   5.000   0.7288   0.01058   0.00409  -0.0356   0.1177   1.0000
   5.250   0.7477   0.01117   0.00445  -0.0341   0.0746   1.0000
   5.500   0.7674   0.01168   0.00483  -0.0328   0.0483   1.0000
   5.750   0.7874   0.01215   0.00526  -0.0314   0.0329   1.0000
   6.000   0.8072   0.01262   0.00571  -0.0300   0.0229   1.0000
   6.250   0.8261   0.01320   0.00630  -0.0284   0.0115   1.0000
   6.500   0.8425   0.01417   0.00741  -0.0260   0.0059   1.0000
   6.750   0.8581   0.01517   0.00855  -0.0236   0.0047   1.0000
   7.000   0.8714   0.01640   0.00996  -0.0208   0.0044   1.0000
   7.250   0.8839   0.01780   0.01154  -0.0178   0.0043   1.0000
   7.500   0.8967   0.01931   0.01323  -0.0151   0.0042   1.0000
   7.750   0.9091   0.02113   0.01528  -0.0122   0.0042   1.0000
   8.000   0.9224   0.02287   0.01725  -0.0096   0.0043   1.0000
   8.250   0.9351   0.02470   0.01931  -0.0069   0.0044   1.0000
   8.500   0.9454   0.02695   0.02189  -0.0038   0.0046   1.0000
   8.750   0.9401   0.03257   0.02820   0.0019   0.0055   1.0000
   9.000   0.9267   0.03797   0.03414   0.0079   0.0064   1.0000
   9.250   0.9102   0.04255   0.03909   0.0132   0.0070   1.0000
   9.500   0.8932   0.04622   0.04302   0.0180   0.0074   1.0000
   9.750   0.8708   0.04930   0.04629   0.0231   0.0077   1.0000
  10.000   0.8499   0.05262   0.04978   0.0264   0.0078   1.0000
  10.250   0.8269   0.05666   0.05398   0.0280   0.0080   1.0000
  10.500   0.8130   0.06034   0.05779   0.0277   0.0079   1.0000
  10.750   0.7933   0.06580   0.06338   0.0249   0.0079   1.0000
  11.000   0.7754   0.07305   0.07076   0.0193   0.0078   1.0000
  11.250   0.7637   0.08219   0.08001   0.0119   0.0075   1.0000
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