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M6 (85%) (m685-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: M6 (85%) (m685-il)
Reynolds number: 500,000
Max Cl/Cd: 84.84 at α=4.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-m685-il-500000.txt
Download as CSV file: xf-m685-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: M6 (85%)                                        
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.4167   0.08553   0.08329  -0.0280   1.0000   0.0259
 -10.000  -0.4239   0.07986   0.07763  -0.0301   1.0000   0.0259
  -9.750  -0.4329   0.07387   0.07166  -0.0326   1.0000   0.0259
  -9.500  -0.6411   0.05525   0.05275  -0.0416   1.0000   0.0175
  -9.250  -0.6443   0.05504   0.05253  -0.0384   1.0000   0.0174
  -9.000  -0.6726   0.04836   0.04564  -0.0351   1.0000   0.0172
  -8.750  -0.7082   0.04059   0.03746  -0.0295   1.0000   0.0169
  -8.500  -0.7473   0.03227   0.02839  -0.0212   1.0000   0.0169
  -8.250  -0.7624   0.02722   0.02266  -0.0146   1.0000   0.0172
  -8.000  -0.7625   0.02434   0.01932  -0.0099   1.0000   0.0179
  -7.750  -0.7486   0.02363   0.01858  -0.0076   1.0000   0.0183
  -7.500  -0.7355   0.02291   0.01777  -0.0050   1.0000   0.0187
  -7.250  -0.7226   0.02235   0.01715  -0.0024   1.0000   0.0192
  -7.000  -0.6906   0.02127   0.01583  -0.0036   0.9971   0.0206
  -6.750  -0.6563   0.02013   0.01436  -0.0052   0.9930   0.0214
  -6.500  -0.6230   0.01885   0.01304  -0.0069   0.9884   0.0223
  -6.250  -0.5874   0.01780   0.01187  -0.0088   0.9844   0.0227
  -6.000  -0.5537   0.01698   0.01095  -0.0102   0.9780   0.0232
  -5.750  -0.5184   0.01614   0.01000  -0.0119   0.9724   0.0236
  -5.500  -0.4839   0.01534   0.00912  -0.0134   0.9648   0.0241
  -5.250  -0.4475   0.01468   0.00838  -0.0152   0.9562   0.0248
  -5.000  -0.4085   0.01389   0.00750  -0.0177   0.9478   0.0252
  -4.750  -0.3709   0.01319   0.00672  -0.0197   0.9341   0.0255
  -4.500  -0.3343   0.01260   0.00605  -0.0216   0.9171   0.0258
  -4.250  -0.3047   0.01191   0.00526  -0.0219   0.8956   0.0264
  -4.000  -0.2793   0.01140   0.00466  -0.0213   0.8731   0.0270
  -3.750  -0.2549   0.01108   0.00425  -0.0205   0.8527   0.0280
  -3.500  -0.2309   0.01087   0.00398  -0.0195   0.8334   0.0298
  -3.250  -0.2069   0.01068   0.00368  -0.0185   0.8159   0.0317
  -3.000  -0.1847   0.01028   0.00323  -0.0172   0.7999   0.0370
  -2.750  -0.1610   0.01005   0.00292  -0.0162   0.7851   0.0416
  -2.500  -0.1370   0.00988   0.00270  -0.0153   0.7713   0.0475
  -2.250  -0.1134   0.00966   0.00251  -0.0143   0.7582   0.0618
  -2.000  -0.0901   0.00940   0.00235  -0.0133   0.7456   0.0950
  -1.750  -0.0669   0.00916   0.00224  -0.0123   0.7339   0.1403
  -1.500  -0.0437   0.00895   0.00212  -0.0113   0.7230   0.1827
  -1.250  -0.0211   0.00868   0.00203  -0.0103   0.7119   0.2459
  -1.000  -0.0036   0.00806   0.00191  -0.0083   0.7018   0.3936
  -0.750  -0.0080   0.00670   0.00175  -0.0015   0.6930   0.7259
  -0.500   0.0632   0.00648   0.00207  -0.0103   0.6824   0.9060
  -0.250   0.1070   0.00671   0.00223  -0.0135   0.6726   0.9239
   0.000   0.1456   0.00705   0.00248  -0.0153   0.6628   0.9364
   0.250   0.1929   0.00751   0.00288  -0.0190   0.6527   0.9463
   0.500   0.2557   0.00829   0.00357  -0.0256   0.6423   0.9628
   0.750   0.3103   0.00856   0.00376  -0.0311   0.6315   0.9690
   1.000   0.3462   0.00873   0.00389  -0.0327   0.6214   0.9757
   1.250   0.3912   0.00873   0.00382  -0.0363   0.6099   0.9786
   1.750   0.4563   0.00880   0.00379  -0.0384   0.5839   0.9857
   2.000   0.4900   0.00872   0.00368  -0.0397   0.5724   0.9872
   2.250   0.5226   0.00869   0.00361  -0.0409   0.5621   0.9891
   2.500   0.5540   0.00867   0.00356  -0.0417   0.5504   0.9913
   2.750   0.5843   0.00868   0.00354  -0.0424   0.5367   0.9937
   3.000   0.6161   0.00865   0.00349  -0.0433   0.5231   0.9955
   3.250   0.6483   0.00860   0.00342  -0.0444   0.5094   0.9974
   3.500   0.6799   0.00859   0.00337  -0.0453   0.4932   0.9992
   3.750   0.7066   0.00863   0.00339  -0.0453   0.4764   1.0000
   4.000   0.7276   0.00877   0.00342  -0.0440   0.4474   1.0000
   4.250   0.7493   0.00889   0.00349  -0.0429   0.4279   1.0000
   4.500   0.7702   0.00908   0.00359  -0.0416   0.3987   1.0000
   4.750   0.7907   0.00932   0.00370  -0.0403   0.3662   1.0000
   5.000   0.8106   0.00961   0.00385  -0.0389   0.3312   1.0000
   5.250   0.8301   0.00996   0.00405  -0.0374   0.2909   1.0000
   5.500   0.8489   0.01038   0.00429  -0.0359   0.2489   1.0000
   5.750   0.8666   0.01091   0.00459  -0.0343   0.2039   1.0000
   6.000   0.8841   0.01145   0.00495  -0.0325   0.1629   1.0000
   6.250   0.8989   0.01223   0.00541  -0.0305   0.1041   1.0000
   6.500   0.9143   0.01293   0.00592  -0.0284   0.0711   1.0000
   6.750   0.9302   0.01357   0.00642  -0.0264   0.0465   1.0000
   7.000   0.9457   0.01424   0.00701  -0.0242   0.0341   1.0000
   7.250   0.9625   0.01478   0.00759  -0.0222   0.0301   1.0000
   7.500   0.9785   0.01535   0.00817  -0.0202   0.0273   1.0000
   7.750   0.9920   0.01609   0.00897  -0.0177   0.0256   1.0000
   8.000   1.0082   0.01659   0.00953  -0.0157   0.0244   1.0000
   8.250   1.0234   0.01715   0.01014  -0.0135   0.0237   1.0000
   8.500   1.0374   0.01776   0.01081  -0.0112   0.0232   1.0000
   8.750   1.0503   0.01842   0.01153  -0.0086   0.0227   1.0000
   9.000   1.0626   0.01910   0.01225  -0.0061   0.0223   1.0000
   9.250   1.0729   0.01987   0.01307  -0.0032   0.0219   1.0000
   9.500   1.0817   0.02070   0.01394  -0.0002   0.0214   1.0000
   9.750   1.0896   0.02156   0.01486   0.0030   0.0213   1.0000
  10.000   1.0950   0.02254   0.01590   0.0065   0.0210   1.0000
  10.250   1.0970   0.02343   0.01684   0.0107   0.0209   1.0000
  10.500   1.0969   0.02459   0.01807   0.0149   0.0207   1.0000
  10.750   1.0997   0.02618   0.01973   0.0184   0.0204   1.0000
  11.000   1.1078   0.02727   0.02089   0.0210   0.0203   1.0000
  11.250   1.1162   0.02835   0.02206   0.0234   0.0203   1.0000
  11.500   1.1246   0.02949   0.02330   0.0256   0.0202   1.0000
  11.750   1.1326   0.03070   0.02461   0.0278   0.0200   1.0000
  12.000   1.1410   0.03209   0.02611   0.0297   0.0200   1.0000
  12.250   1.1478   0.03355   0.02769   0.0316   0.0198   1.0000
  12.500   1.1550   0.03527   0.02954   0.0333   0.0198   1.0000
  12.750   1.1599   0.03712   0.03154   0.0350   0.0198   1.0000
  13.000   1.1629   0.03913   0.03370   0.0367   0.0198   1.0000
  13.250   1.1635   0.04137   0.03611   0.0382   0.0197   1.0000
  13.500   1.1629   0.04393   0.03883   0.0395   0.0198   1.0000
  13.750   1.1588   0.04671   0.04179   0.0406   0.0198   1.0000
  14.000   1.1522   0.04993   0.04519   0.0415   0.0199   1.0000
  14.250   1.1420   0.05358   0.04903   0.0419   0.0200   1.0000
  14.500   1.1321   0.05703   0.05265   0.0419   0.0199   1.0000
  14.750   1.1177   0.06177   0.05756   0.0416   0.0202   1.0000
  15.000   1.1089   0.06630   0.06223   0.0414   0.0205   1.0000
  15.250   1.0860   0.07103   0.06717   0.0388   0.0201   1.0000
  15.500   1.0711   0.07581   0.07209   0.0367   0.0200   1.0000
  15.750   1.0537   0.08210   0.07852   0.0353   0.0205   1.0000
  16.000   1.0316   0.08872   0.08529   0.0318   0.0204   1.0000
  16.250   1.0307   0.09214   0.08880   0.0297   0.0207   1.0000
  16.500   1.0020   0.10083   0.09765   0.0247   0.0206   1.0000
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