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

MH 95 15.86% (mh95-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: MH 95 15.86% (mh95-il)
Reynolds number: 200,000
Max Cl/Cd: 45.57 at α=8.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-mh95-il-200000-n5.txt
Download as CSV file: xf-mh95-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MH 95  15.86%                                   
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -15.500  -0.6662   0.09631   0.09151  -0.0615   1.0000   0.0186
 -15.250  -0.6905   0.08830   0.08336  -0.0659   1.0000   0.0184
 -15.000  -0.7166   0.08067   0.07555  -0.0700   1.0000   0.0184
 -14.750  -0.7405   0.07417   0.06888  -0.0731   1.0000   0.0183
 -14.500  -0.7650   0.06833   0.06283  -0.0752   1.0000   0.0183
 -14.250  -0.7860   0.06360   0.05790  -0.0762   1.0000   0.0184
 -14.000  -0.8028   0.05972   0.05385  -0.0762   1.0000   0.0184
 -13.750  -0.8208   0.05612   0.05005  -0.0756   1.0000   0.0184
 -13.500  -0.8362   0.05304   0.04678  -0.0742   1.0000   0.0185
 -13.250  -0.8477   0.05049   0.04406  -0.0724   1.0000   0.0185
 -13.000  -0.8586   0.04817   0.04157  -0.0701   1.0000   0.0185
 -12.750  -0.8702   0.04597   0.03917  -0.0674   1.0000   0.0186
 -12.500  -0.8766   0.04420   0.03726  -0.0646   1.0000   0.0186
 -12.250  -0.8800   0.04255   0.03553  -0.0618   1.0000   0.0187
 -12.000  -0.8831   0.04109   0.03399  -0.0588   1.0000   0.0188
 -11.750  -0.8856   0.03978   0.03261  -0.0557   1.0000   0.0189
 -11.500  -0.8878   0.03854   0.03127  -0.0523   1.0000   0.0190
 -11.250  -0.8897   0.03741   0.03005  -0.0488   1.0000   0.0191
 -11.000  -0.8915   0.03635   0.02891  -0.0452   1.0000   0.0193
 -10.750  -0.8862   0.03524   0.02771  -0.0428   0.9992   0.0194
 -10.500  -0.8663   0.03391   0.02627  -0.0430   0.9967   0.0197
 -10.250  -0.8449   0.03269   0.02494  -0.0432   0.9941   0.0200
 -10.000  -0.8242   0.03152   0.02366  -0.0432   0.9914   0.0203
  -9.750  -0.8035   0.03041   0.02245  -0.0430   0.9882   0.0207
  -9.500  -0.7805   0.02937   0.02131  -0.0432   0.9853   0.0211
  -9.250  -0.7557   0.02838   0.02021  -0.0436   0.9829   0.0215
  -9.000  -0.7355   0.02750   0.01923  -0.0431   0.9792   0.0220
  -8.750  -0.7171   0.02662   0.01838  -0.0424   0.9748   0.0226
  -8.500  -0.6929   0.02588   0.01763  -0.0427   0.9715   0.0233
  -8.250  -0.6656   0.02507   0.01677  -0.0435   0.9692   0.0242
  -8.000  -0.6511   0.02440   0.01605  -0.0415   0.9629   0.0249
  -7.750  -0.6274   0.02364   0.01523  -0.0414   0.9590   0.0257
  -7.500  -0.6013   0.02281   0.01440  -0.0420   0.9561   0.0265
  -7.250  -0.5843   0.02218   0.01375  -0.0404   0.9503   0.0273
  -7.000  -0.5626   0.02155   0.01308  -0.0398   0.9453   0.0284
  -6.750  -0.5347   0.02090   0.01238  -0.0403   0.9422   0.0298
  -6.500  -0.5043   0.02022   0.01169  -0.0414   0.9399   0.0318
  -6.250  -0.4925   0.01981   0.01123  -0.0385   0.9315   0.0340
  -6.000  -0.4653   0.01920   0.01064  -0.0387   0.9277   0.0382
  -5.750  -0.4347   0.01857   0.01004  -0.0396   0.9251   0.0452
  -5.500  -0.4193   0.01808   0.00959  -0.0375   0.9177   0.0543
  -5.250  -0.3956   0.01741   0.00906  -0.0370   0.9127   0.0771
  -4.750  -0.3516   0.01584   0.00806  -0.0357   0.9028   0.1824
  -4.500  -0.3318   0.01513   0.00764  -0.0346   0.8966   0.2428
  -4.250  -0.3054   0.01430   0.00716  -0.0348   0.8931   0.3195
  -4.000  -0.2904   0.01361   0.00684  -0.0326   0.8857   0.3957
  -3.750  -0.2716   0.01286   0.00654  -0.0309   0.8792   0.4849
  -3.500  -0.2429   0.01231   0.00639  -0.0309   0.8757   0.5694
  -3.250  -0.2240   0.01216   0.00644  -0.0287   0.8673   0.6214
  -3.000  -0.1938   0.01205   0.00639  -0.0287   0.8617   0.6553
  -2.750  -0.1563   0.01191   0.00622  -0.0302   0.8580   0.6755
  -2.500  -0.1348   0.01189   0.00618  -0.0286   0.8482   0.6901
  -2.250  -0.0995   0.01177   0.00602  -0.0297   0.8425   0.7032
  -2.000  -0.0718   0.01170   0.00589  -0.0295   0.8336   0.7158
  -1.750  -0.0376   0.01164   0.00581  -0.0303   0.8258   0.7254
  -1.500  -0.0084   0.01159   0.00570  -0.0303   0.8157   0.7360
  -1.250   0.0278   0.01153   0.00560  -0.0315   0.8067   0.7451
  -1.000   0.0557   0.01150   0.00551  -0.0313   0.7940   0.7539
  -0.750   0.0878   0.01149   0.00546  -0.0317   0.7814   0.7609
  -0.500   0.1197   0.01144   0.00530  -0.0323   0.7676   0.7690
  -0.250   0.1514   0.01146   0.00526  -0.0327   0.7527   0.7743
   0.000   0.1798   0.01151   0.00524  -0.0324   0.7360   0.7805
   0.250   0.2070   0.01152   0.00514  -0.0322   0.7188   0.7883
   0.500   0.2344   0.01162   0.00519  -0.0317   0.7012   0.7929
   0.750   0.2608   0.01171   0.00520  -0.0311   0.6829   0.7985
   1.000   0.2858   0.01178   0.00516  -0.0305   0.6644   0.8050
   1.250   0.3105   0.01188   0.00518  -0.0296   0.6451   0.8095
   1.500   0.3343   0.01200   0.00524  -0.0285   0.6254   0.8139
   1.750   0.3573   0.01212   0.00526  -0.0274   0.6048   0.8191
   2.000   0.3797   0.01221   0.00525  -0.0264   0.5838   0.8250
   2.250   0.4015   0.01236   0.00532  -0.0250   0.5622   0.8285
   2.500   0.4226   0.01252   0.00539  -0.0235   0.5402   0.8326
   2.750   0.4432   0.01268   0.00545  -0.0220   0.5186   0.8374
   3.000   0.4636   0.01283   0.00549  -0.0206   0.4954   0.8428
   3.250   0.4826   0.01303   0.00559  -0.0188   0.4713   0.8465
   3.500   0.5004   0.01325   0.00570  -0.0167   0.4467   0.8507
   3.750   0.5184   0.01347   0.00581  -0.0149   0.4213   0.8556
   4.000   0.5366   0.01369   0.00591  -0.0131   0.3978   0.8612
   4.500   0.5703   0.01415   0.00621  -0.0089   0.3571   0.8697
   4.750   0.5877   0.01436   0.00636  -0.0070   0.3396   0.8752
   5.000   0.6051   0.01459   0.00652  -0.0052   0.3231   0.8805
   5.250   0.6223   0.01481   0.00671  -0.0032   0.3079   0.8849
   5.500   0.6400   0.01506   0.00691  -0.0014   0.2929   0.8905
   5.750   0.6581   0.01533   0.00714   0.0002   0.2788   0.8967
   6.000   0.6750   0.01560   0.00738   0.0022   0.2662   0.9017
   6.250   0.6921   0.01590   0.00763   0.0040   0.2541   0.9078
   6.500   0.7104   0.01617   0.00789   0.0055   0.2419   0.9142
   6.750   0.7279   0.01646   0.00818   0.0072   0.2301   0.9206
   7.000   0.7454   0.01680   0.00848   0.0088   0.2191   0.9282
   7.250   0.7648   0.01714   0.00880   0.0100   0.2073   0.9347
   7.500   0.7840   0.01748   0.00915   0.0112   0.1968   0.9429
   7.750   0.8058   0.01789   0.00955   0.0118   0.1864   0.9504
   8.000   0.8287   0.01834   0.00997   0.0120   0.1756   0.9589
   8.250   0.8549   0.01882   0.01046   0.0115   0.1648   0.9668
   8.500   0.8814   0.01938   0.01099   0.0108   0.1553   0.9752
   8.750   0.9083   0.01993   0.01153   0.0099   0.1468   0.9860
   9.000   0.9296   0.02046   0.01207   0.0101   0.1405   1.0000
   9.250   0.9438   0.02097   0.01256   0.0116   0.1350   1.0000
   9.500   0.9572   0.02160   0.01315   0.0132   0.1303   1.0000
   9.750   0.9737   0.02214   0.01374   0.0144   0.1260   1.0000
  10.000   0.9887   0.02278   0.01438   0.0156   0.1217   1.0000
  10.250   1.0019   0.02353   0.01510   0.0171   0.1184   1.0000
  10.500   1.0167   0.02423   0.01584   0.0183   0.1156   1.0000
  10.750   1.0318   0.02493   0.01660   0.0194   0.1129   1.0000
  11.000   1.0457   0.02571   0.01741   0.0207   0.1102   1.0000
  11.250   1.0582   0.02657   0.01828   0.0220   0.1078   1.0000
  11.500   1.0687   0.02758   0.01928   0.0234   0.1055   1.0000
  11.750   1.0828   0.02843   0.02020   0.0244   0.1035   1.0000
  12.000   1.0962   0.02932   0.02117   0.0254   0.1015   1.0000
  12.250   1.1088   0.03028   0.02219   0.0265   0.0997   1.0000
  12.500   1.1204   0.03131   0.02328   0.0275   0.0980   1.0000
  12.750   1.1311   0.03243   0.02444   0.0285   0.0965   1.0000
  13.000   1.1407   0.03368   0.02569   0.0296   0.0949   1.0000
  13.250   1.1508   0.03493   0.02697   0.0305   0.0934   1.0000
  13.500   1.1620   0.03611   0.02826   0.0313   0.0920   1.0000
  13.750   1.1725   0.03736   0.02962   0.0320   0.0905   1.0000
  14.000   1.1823   0.03871   0.03105   0.0327   0.0892   1.0000
  14.250   1.1912   0.04013   0.03255   0.0333   0.0879   1.0000
  14.500   1.1998   0.04161   0.03411   0.0339   0.0867   1.0000
  14.750   1.2072   0.04322   0.03577   0.0344   0.0854   1.0000
  15.000   1.2146   0.04487   0.03745   0.0348   0.0843   1.0000
  15.250   1.2229   0.04654   0.03915   0.0352   0.0831   1.0000
  15.500   1.2288   0.04842   0.04118   0.0354   0.0821   1.0000
  15.750   1.2342   0.05040   0.04330   0.0355   0.0811   1.0000
  16.000   1.2390   0.05250   0.04552   0.0356   0.0800   1.0000
  16.250   1.2427   0.05473   0.04788   0.0354   0.0788   1.0000
  16.500   1.2460   0.05706   0.05031   0.0352   0.0777   1.0000
  16.750   1.2489   0.05948   0.05281   0.0348   0.0767   1.0000
  17.000   1.2516   0.06198   0.05539   0.0343   0.0757   1.0000
  17.250   1.2549   0.06444   0.05790   0.0338   0.0747   1.0000
  17.500   1.2596   0.06679   0.06027   0.0334   0.0738   1.0000
  17.750   1.2547   0.07046   0.06416   0.0322   0.0729   1.0000
  18.000   1.2494   0.07431   0.06819   0.0308   0.0720   1.0000
  18.250   1.2435   0.07837   0.07243   0.0291   0.0710   1.0000
  18.500   1.2374   0.08254   0.07676   0.0273   0.0701   1.0000
  18.750   1.2310   0.08685   0.08121   0.0253   0.0692   1.0000
  19.000   1.2248   0.09122   0.08570   0.0232   0.0682   1.0000
<< Back to MH 95 15.86% (mh95-il)

Polar data table (+)

Polar graphs


<< Back to MH 95 15.86% (mh95-il)