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M6 (65%) (m665-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: M6 (65%) (m665-il)
Reynolds number: 200,000
Max Cl/Cd: 55.39 at α=3.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-m665-il-200000-n5.txt
Download as CSV file: xf-m665-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: M6 (65%)                                        
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.5551   0.08771   0.08408  -0.0105   1.0000   0.0165
  -8.750  -0.5593   0.08312   0.07953  -0.0133   1.0000   0.0167
  -8.500  -0.5680   0.07817   0.07463  -0.0170   1.0000   0.0161
  -8.250  -0.5782   0.07371   0.07017  -0.0189   1.0000   0.0165
  -8.000  -0.5844   0.06878   0.06521  -0.0206   1.0000   0.0161
  -7.750  -0.5877   0.06379   0.06015  -0.0218   1.0000   0.0161
  -7.500  -0.5875   0.05911   0.05535  -0.0223   1.0000   0.0164
  -7.250  -0.5863   0.05415   0.05023  -0.0220   1.0000   0.0165
  -7.000  -0.5843   0.04898   0.04483  -0.0210   1.0000   0.0165
  -6.750  -0.5819   0.04358   0.03913  -0.0192   1.0000   0.0161
  -6.500  -0.5788   0.03817   0.03334  -0.0165   1.0000   0.0158
  -6.250  -0.5745   0.03310   0.02777  -0.0133   1.0000   0.0156
  -6.000  -0.5660   0.02921   0.02340  -0.0102   1.0000   0.0157
  -5.750  -0.5537   0.02621   0.01995  -0.0074   1.0000   0.0159
  -5.500  -0.5385   0.02380   0.01713  -0.0050   1.0000   0.0162
  -5.250  -0.5212   0.02180   0.01474  -0.0029   1.0000   0.0169
  -5.000  -0.5024   0.02004   0.01263  -0.0009   1.0000   0.0178
  -4.750  -0.4825   0.01865   0.01094   0.0008   1.0000   0.0189
  -4.500  -0.4635   0.01769   0.00995   0.0024   1.0000   0.0201
  -4.250  -0.4333   0.01693   0.00910   0.0017   0.9958   0.0219
  -4.000  -0.3982   0.01631   0.00832   0.0000   0.9884   0.0246
  -3.750  -0.3646   0.01550   0.00746  -0.0015   0.9801   0.0282
  -3.500  -0.3309   0.01486   0.00679  -0.0029   0.9710   0.0309
  -3.250  -0.2968   0.01412   0.00598  -0.0042   0.9613   0.0328
  -3.000  -0.2625   0.01346   0.00522  -0.0055   0.9504   0.0347
  -2.750  -0.2292   0.01284   0.00454  -0.0067   0.9375   0.0374
  -2.500  -0.1952   0.01233   0.00399  -0.0080   0.9235   0.0424
  -2.250  -0.1609   0.01195   0.00355  -0.0093   0.9084   0.0498
  -2.000  -0.1287   0.01157   0.00321  -0.0101   0.8912   0.0659
  -1.750  -0.0998   0.01112   0.00294  -0.0104   0.8723   0.1168
  -1.500  -0.0736   0.01061   0.00272  -0.0102   0.8534   0.2052
  -1.250  -0.0531   0.00982   0.00250  -0.0089   0.8349   0.3755
  -1.000   0.0303   0.00847   0.00299  -0.0194   0.8256   0.9224
  -0.750   0.0841   0.00894   0.00331  -0.0240   0.8086   0.9593
  -0.500   0.1382   0.00921   0.00341  -0.0292   0.7909   0.9788
  -0.250   0.1943   0.00924   0.00329  -0.0351   0.7724   0.9922
   0.000   0.2345   0.00918   0.00310  -0.0378   0.7540   0.9983
   0.250   0.2626   0.00919   0.00299  -0.0379   0.7363   1.0000
   0.500   0.2853   0.00922   0.00293  -0.0369   0.7201   1.0000
   0.750   0.3080   0.00925   0.00289  -0.0358   0.7043   1.0000
   1.000   0.3310   0.00930   0.00286  -0.0349   0.6892   1.0000
   1.250   0.3541   0.00935   0.00285  -0.0339   0.6745   1.0000
   1.500   0.3772   0.00940   0.00287  -0.0329   0.6595   1.0000
   1.750   0.4002   0.00947   0.00288  -0.0319   0.6425   1.0000
   2.000   0.4231   0.00954   0.00290  -0.0309   0.6236   1.0000
   2.250   0.4462   0.00962   0.00295  -0.0298   0.6053   1.0000
   2.500   0.4694   0.00971   0.00301  -0.0289   0.5885   1.0000
   2.750   0.4925   0.00981   0.00309  -0.0279   0.5704   1.0000
   3.000   0.5157   0.00991   0.00318  -0.0269   0.5500   1.0000
   3.250   0.5384   0.01005   0.00327  -0.0258   0.5251   1.0000
   3.500   0.5607   0.01022   0.00339  -0.0247   0.4927   1.0000
   3.750   0.5816   0.01050   0.00348  -0.0233   0.4417   1.0000
   4.000   0.6012   0.01094   0.00362  -0.0218   0.3708   1.0000
   4.250   0.6194   0.01163   0.00387  -0.0203   0.2773   1.0000
   4.500   0.6355   0.01270   0.00433  -0.0186   0.1583   1.0000
   4.750   0.6527   0.01370   0.00490  -0.0172   0.0769   1.0000
   5.000   0.6725   0.01437   0.00544  -0.0158   0.0480   1.0000
   5.250   0.6925   0.01500   0.00603  -0.0145   0.0357   1.0000
   5.500   0.7131   0.01555   0.00668  -0.0131   0.0311   1.0000
   5.750   0.7332   0.01614   0.00734  -0.0117   0.0283   1.0000
   6.000   0.7520   0.01688   0.00814  -0.0102   0.0262   1.0000
   6.250   0.7699   0.01770   0.00903  -0.0085   0.0245   1.0000
   6.500   0.7893   0.01832   0.00976  -0.0071   0.0231   1.0000
   6.750   0.8074   0.01912   0.01064  -0.0055   0.0221   1.0000
   7.000   0.8252   0.01999   0.01160  -0.0038   0.0215   1.0000
   7.250   0.8428   0.02093   0.01262  -0.0021   0.0208   1.0000
   7.500   0.8604   0.02193   0.01371  -0.0005   0.0203   1.0000
   7.750   0.8780   0.02301   0.01490   0.0012   0.0198   1.0000
   8.000   0.8955   0.02417   0.01616   0.0027   0.0193   1.0000
   8.250   0.9128   0.02547   0.01757   0.0043   0.0189   1.0000
   8.500   0.9297   0.02692   0.01916   0.0059   0.0186   1.0000
   8.750   0.9459   0.02858   0.02099   0.0074   0.0183   1.0000
   9.000   0.9609   0.03047   0.02310   0.0091   0.0181   1.0000
   9.250   0.9738   0.03273   0.02561   0.0109   0.0179   1.0000
   9.500   0.9847   0.03509   0.02825   0.0129   0.0178   1.0000
   9.750   0.9919   0.03778   0.03125   0.0152   0.0177   1.0000
  10.000   0.9940   0.04059   0.03439   0.0178   0.0174   1.0000
  10.250   0.9972   0.04228   0.03641   0.0205   0.0169   1.0000
  10.500   0.9962   0.04435   0.03880   0.0233   0.0163   1.0000
  10.750   0.9898   0.04668   0.04140   0.0264   0.0157   1.0000
  11.000   0.9756   0.04934   0.04429   0.0299   0.0156   1.0000
  11.250   0.9628   0.05203   0.04719   0.0319   0.0151   1.0000
  11.500   0.9461   0.05572   0.05109   0.0325   0.0150   1.0000
  11.750   0.9260   0.06048   0.05605   0.0314   0.0152   1.0000
  12.000   0.9056   0.06598   0.06174   0.0288   0.0152   1.0000
  12.250   0.8829   0.07281   0.06873   0.0246   0.0154   1.0000
  12.500   0.8567   0.08151   0.07758   0.0186   0.0157   1.0000
  12.750   0.8307   0.09151   0.08766   0.0119   0.0165   1.0000
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