Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

MH 26 10.99% (mh26-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: MH 26 10.99% (mh26-il)
Reynolds number: 100,000
Max Cl/Cd: 47.54 at α=4.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-mh26-il-100000-n5.txt
Download as CSV file: xf-mh26-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MH 26  10.99%                                   
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.5091   0.09358   0.08879  -0.0373   1.0000   0.0146
  -9.250  -0.5198   0.08923   0.08450  -0.0383   1.0000   0.0144
  -9.000  -0.5325   0.08478   0.08009  -0.0399   1.0000   0.0143
  -8.750  -0.5499   0.08044   0.07577  -0.0408   1.0000   0.0141
  -8.500  -0.5698   0.07716   0.07248  -0.0392   1.0000   0.0140
  -8.250  -0.5922   0.07459   0.06990  -0.0358   1.0000   0.0138
  -8.000  -0.6142   0.07159   0.06685  -0.0318   1.0000   0.0138
  -7.750  -0.6275   0.06877   0.06395  -0.0286   1.0000   0.0136
  -7.500  -0.6421   0.06511   0.06017  -0.0250   1.0000   0.0135
  -7.250  -0.6509   0.06198   0.05691  -0.0216   1.0000   0.0132
  -7.000  -0.6590   0.05840   0.05314  -0.0180   1.0000   0.0130
  -6.750  -0.6639   0.05493   0.04944  -0.0144   1.0000   0.0128
  -6.500  -0.6660   0.05154   0.04579  -0.0108   1.0000   0.0126
  -6.250  -0.6646   0.04789   0.04180  -0.0074   0.9995   0.0125
  -6.000  -0.6513   0.04393   0.03738  -0.0061   0.9963   0.0123
  -5.750  -0.6354   0.04040   0.03335  -0.0046   0.9934   0.0121
  -5.500  -0.6183   0.03719   0.02962  -0.0029   0.9902   0.0122
  -5.250  -0.5975   0.03445   0.02637  -0.0016   0.9874   0.0121
  -5.000  -0.5731   0.03225   0.02364  -0.0010   0.9849   0.0130
  -4.750  -0.5454   0.03065   0.02153  -0.0006   0.9826   0.0151
  -4.500  -0.5211   0.02896   0.01949   0.0002   0.9796   0.0162
  -4.250  -0.4956   0.02705   0.01739   0.0007   0.9770   0.0173
  -4.000  -0.4685   0.02573   0.01593   0.0008   0.9743   0.0185
  -3.750  -0.4401   0.02463   0.01471   0.0007   0.9717   0.0204
  -3.500  -0.4157   0.02371   0.01360   0.0015   0.9683   0.0236
  -3.250  -0.3931   0.02288   0.01273   0.0022   0.9641   0.0299
  -3.000  -0.3671   0.02197   0.01173   0.0027   0.9606   0.0488
  -2.750  -0.3421   0.02057   0.01115   0.0027   0.9578   0.1787
  -2.500  -0.3285   0.01879   0.01091   0.0048   0.9535   0.4888
  -2.250  -0.2233   0.01983   0.01310  -0.0072   0.9629   0.9181
  -2.000  -0.1609   0.02065   0.01355  -0.0136   0.9636   0.9487
  -1.750  -0.0834   0.02128   0.01386  -0.0236   0.9668   0.9745
  -1.500  -0.0263   0.02139   0.01375  -0.0302   0.9662   0.9863
  -1.250   0.0233   0.02142   0.01358  -0.0353   0.9643   0.9943
  -1.000   0.0710   0.02138   0.01340  -0.0402   0.9619   1.0000
  -0.750   0.1067   0.02141   0.01332  -0.0425   0.9578   1.0000
  -0.500   0.1310   0.02131   0.01313  -0.0424   0.9501   1.0000
   0.000   0.1921   0.02120   0.01291  -0.0445   0.9372   1.0000
   0.250   0.2284   0.02114   0.01281  -0.0467   0.9319   1.0000
   0.500   0.2530   0.02102   0.01269  -0.0465   0.9231   1.0000
   0.750   0.2916   0.02090   0.01256  -0.0490   0.9179   1.0000
   1.000   0.3147   0.02075   0.01242  -0.0483   0.9078   1.0000
   1.250   0.3438   0.02057   0.01228  -0.0487   0.8992   1.0000
   1.500   0.3789   0.02033   0.01207  -0.0503   0.8918   1.0000
   1.750   0.4020   0.02010   0.01189  -0.0495   0.8804   1.0000
   2.000   0.4266   0.01985   0.01169  -0.0488   0.8689   1.0000
   2.250   0.4514   0.01957   0.01147  -0.0481   0.8570   1.0000
   2.500   0.4758   0.01926   0.01127  -0.0473   0.8441   1.0000
   2.750   0.4991   0.01893   0.01102  -0.0462   0.8301   1.0000
   3.000   0.5222   0.01856   0.01074  -0.0449   0.8151   1.0000
   3.250   0.5487   0.01815   0.01042  -0.0442   0.7990   1.0000
   3.500   0.5749   0.01778   0.01018  -0.0435   0.7790   1.0000
   3.750   0.6143   0.01721   0.00971  -0.0451   0.7565   1.0000
   4.000   0.6641   0.01664   0.00921  -0.0487   0.7208   1.0000
   4.250   0.7276   0.01610   0.00864  -0.0550   0.6602   1.0000
   4.500   0.7651   0.01617   0.00849  -0.0565   0.5906   1.0000
   4.750   0.7868   0.01655   0.00863  -0.0551   0.5268   1.0000
   5.000   0.8019   0.01706   0.00890  -0.0525   0.4686   1.0000
   5.250   0.8138   0.01763   0.00925  -0.0495   0.4137   1.0000
   5.500   0.8244   0.01823   0.00966  -0.0463   0.3630   1.0000
   5.750   0.8340   0.01887   0.01011  -0.0429   0.3153   1.0000
   6.000   0.8436   0.01952   0.01066  -0.0397   0.2713   1.0000
   6.250   0.8527   0.02020   0.01119  -0.0364   0.2292   1.0000
   6.500   0.8615   0.02093   0.01176  -0.0331   0.1908   1.0000
   6.750   0.8707   0.02166   0.01237  -0.0299   0.1565   1.0000
   7.000   0.8786   0.02247   0.01304  -0.0265   0.1255   1.0000
   7.250   0.8869   0.02328   0.01377  -0.0231   0.1013   1.0000
   7.500   0.8939   0.02413   0.01456  -0.0196   0.0818   1.0000
   7.750   0.8998   0.02496   0.01536  -0.0158   0.0670   1.0000
   8.000   0.9030   0.02588   0.01628  -0.0115   0.0587   1.0000
   8.250   0.9073   0.02677   0.01728  -0.0073   0.0517   1.0000
   8.500   0.9100   0.02782   0.01836  -0.0031   0.0457   1.0000
   8.750   0.9162   0.02870   0.01934   0.0004   0.0397   1.0000
   9.000   0.9176   0.03002   0.02074   0.0045   0.0364   1.0000
   9.250   0.9256   0.03129   0.02224   0.0078   0.0337   1.0000
   9.500   0.9342   0.03270   0.02381   0.0108   0.0309   1.0000
   9.750   0.9390   0.03390   0.02509   0.0140   0.0276   1.0000
  10.000   0.9452   0.03573   0.02706   0.0169   0.0247   1.0000
  10.250   0.9548   0.03768   0.02931   0.0196   0.0225   1.0000
  10.500   0.9591   0.03922   0.03106   0.0226   0.0204   1.0000
  10.750   0.9590   0.04065   0.03260   0.0259   0.0185   1.0000
  11.000   0.9556   0.04341   0.03547   0.0291   0.0168   1.0000
  11.250   0.9549   0.04582   0.03822   0.0322   0.0162   1.0000
  11.500   0.9506   0.04853   0.04126   0.0354   0.0158   1.0000
  11.750   0.9415   0.05146   0.04453   0.0386   0.0152   1.0000
  12.000   0.9306   0.05447   0.04782   0.0412   0.0149   1.0000
  12.250   0.9157   0.05787   0.05151   0.0435   0.0143   1.0000
  12.500   0.9002   0.06165   0.05552   0.0449   0.0145   1.0000
  12.750   0.8838   0.06550   0.05960   0.0454   0.0139   1.0000
  13.000   0.8639   0.07056   0.06488   0.0450   0.0146   1.0000
  13.250   0.8430   0.07610   0.07062   0.0432   0.0144   1.0000
  13.500   0.8215   0.08258   0.07727   0.0400   0.0144   1.0000
  13.750   0.8012   0.08972   0.08454   0.0362   0.0152   1.0000
<< Back to MH 26 10.99% (mh26-il)

Polar data table (+)

Polar graphs


<< Back to MH 26 10.99% (mh26-il)