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SD6060-104-88 (sd6060-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: SD6060-104-88 (sd6060-il)
Reynolds number: 50,000
Max Cl/Cd: 33.15 at α=7.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-sd6060-il-50000.txt
Download as CSV file: xf-sd6060-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: SD6060-104-88                                   
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.3452   0.10456   0.09831  -0.0139   1.0000   0.2587
  -9.250  -0.3493   0.10132   0.09513  -0.0145   1.0000   0.2681
  -9.000  -0.3619   0.09911   0.09301  -0.0152   1.0000   0.2796
  -8.750  -0.3439   0.09436   0.08826  -0.0145   1.0000   0.2920
  -8.500  -0.3351   0.09027   0.08420  -0.0142   1.0000   0.3027
  -8.250  -0.3320   0.08666   0.08064  -0.0139   1.0000   0.3169
  -8.000  -0.3302   0.08324   0.07728  -0.0134   1.0000   0.3331
  -7.750  -0.3378   0.08040   0.07454  -0.0128   1.0000   0.3507
  -7.500  -0.3364   0.07679   0.07098  -0.0120   1.0000   0.3669
  -7.250  -0.4106   0.08297   0.07675  -0.0063   1.0000   0.3736
  -6.250  -0.5271   0.05627   0.04943  -0.0333   1.0000   0.1362
  -6.000  -0.5247   0.05172   0.04448  -0.0317   1.0000   0.1219
  -5.750  -0.5170   0.04802   0.04067  -0.0297   1.0000   0.1165
  -5.500  -0.5119   0.04432   0.03617  -0.0275   1.0000   0.1080
  -5.250  -0.5005   0.04113   0.03272  -0.0256   1.0000   0.1059
  -5.000  -0.4874   0.03822   0.02940  -0.0237   1.0000   0.1042
  -4.750  -0.4722   0.03570   0.02640  -0.0218   1.0000   0.1059
  -4.500  -0.4550   0.03346   0.02357  -0.0200   1.0000   0.1097
  -4.250  -0.4359   0.03120   0.02125  -0.0187   1.0000   0.1151
  -4.000  -0.4144   0.02930   0.01890  -0.0171   1.0000   0.1219
  -3.750  -0.3934   0.02759   0.01707  -0.0158   1.0000   0.1377
  -3.500  -0.3715   0.02588   0.01544  -0.0144   1.0000   0.1627
  -3.250  -0.3490   0.02405   0.01393  -0.0131   1.0000   0.2141
  -3.000  -0.0985   0.02117   0.01309  -0.0364   1.0000   1.0000
  -2.750  -0.1126   0.02098   0.01283  -0.0320   1.0000   1.0000
  -2.500  -0.1251   0.02082   0.01257  -0.0275   1.0000   1.0000
  -2.250  -0.1354   0.02069   0.01231  -0.0232   1.0000   1.0000
  -2.000  -0.1427   0.02058   0.01206  -0.0191   1.0000   1.0000
  -1.750  -0.1463   0.02051   0.01183  -0.0155   1.0000   1.0000
  -1.500  -0.1455   0.02051   0.01164  -0.0125   1.0000   1.0000
  -1.250  -0.1411   0.02059   0.01147  -0.0099   1.0000   1.0000
  -1.000  -0.1332   0.02074   0.01141  -0.0079   1.0000   1.0000
  -0.750  -0.1224   0.02095   0.01141  -0.0063   1.0000   1.0000
  -0.500  -0.1097   0.02123   0.01149  -0.0051   1.0000   1.0000
  -0.250  -0.0957   0.02156   0.01164  -0.0041   1.0000   1.0000
   0.000  -0.0808   0.02195   0.01183  -0.0032   1.0000   1.0000
   0.250  -0.0653   0.02238   0.01210  -0.0025   1.0000   1.0000
   0.500  -0.0493   0.02285   0.01244  -0.0020   1.0000   1.0000
   0.750  -0.0101   0.02385   0.01329  -0.0059   0.9905   1.0000
   1.000   0.0329   0.02496   0.01425  -0.0104   0.9783   1.0000
   1.250   0.0743   0.02603   0.01522  -0.0145   0.9655   1.0000
   1.500   0.1143   0.02706   0.01619  -0.0182   0.9523   1.0000
   1.750   0.1530   0.02807   0.01714  -0.0216   0.9384   1.0000
   2.000   0.1902   0.02904   0.01809  -0.0245   0.9242   1.0000
   2.250   0.2264   0.02997   0.01903  -0.0272   0.9093   1.0000
   2.500   0.2616   0.03088   0.01996  -0.0296   0.8938   1.0000
   2.750   0.2969   0.03177   0.02088  -0.0318   0.8779   1.0000
   3.000   0.3334   0.03263   0.02181  -0.0341   0.8616   1.0000
   3.250   0.3734   0.03344   0.02273  -0.0367   0.8449   1.0000
   3.500   0.4093   0.03419   0.02357  -0.0384   0.8276   1.0000
   3.750   0.4358   0.03492   0.02440  -0.0387   0.8088   1.0000
   4.000   0.4738   0.03548   0.02510  -0.0403   0.7900   1.0000
   4.250   0.5267   0.03565   0.02553  -0.0435   0.7718   1.0000
   4.500   0.5455   0.03634   0.02633  -0.0421   0.7501   1.0000
   4.750   0.5978   0.03600   0.02630  -0.0442   0.7305   1.0000
   5.000   0.6256   0.03618   0.02665  -0.0432   0.7081   1.0000
   5.250   0.6750   0.03512   0.02588  -0.0434   0.6878   1.0000
   5.500   0.7035   0.03485   0.02582  -0.0416   0.6638   1.0000
   5.750   0.7473   0.03338   0.02466  -0.0403   0.6408   1.0000
   6.000   0.7898   0.03167   0.02319  -0.0384   0.6155   1.0000
   6.250   0.8231   0.03044   0.02214  -0.0358   0.5860   1.0000
   6.500   0.8484   0.02977   0.02166  -0.0329   0.5515   1.0000
   6.750   0.8800   0.02854   0.02048  -0.0301   0.5135   1.0000
   7.000   0.9042   0.02802   0.01992  -0.0270   0.4702   1.0000
   7.250   0.9243   0.02802   0.01979  -0.0240   0.4227   1.0000
   7.500   0.9425   0.02843   0.01996  -0.0210   0.3724   1.0000
   7.750   0.9554   0.02949   0.02076  -0.0179   0.3211   1.0000
   8.000   0.9647   0.03089   0.02186  -0.0148   0.2690   1.0000
   8.250   0.9707   0.03249   0.02298  -0.0116   0.2186   1.0000
   8.500   0.9777   0.03470   0.02493  -0.0088   0.1752   1.0000
   8.750   0.9903   0.03724   0.02737  -0.0067   0.1433   1.0000
   9.000   1.0150   0.04038   0.03038  -0.0059   0.1242   1.0000
   9.250   1.0321   0.04327   0.03350  -0.0045   0.1122   1.0000
   9.500   1.0447   0.04659   0.03728  -0.0028   0.1047   1.0000
   9.750   1.0593   0.05014   0.04114  -0.0014   0.1002   1.0000
  10.000   1.0768   0.05466   0.04572  -0.0008   0.0968   1.0000
  10.250   1.0732   0.05852   0.05016   0.0017   0.0960   1.0000
  10.500   1.0654   0.06251   0.05461   0.0040   0.0954   1.0000
  10.750   1.0529   0.06652   0.05899   0.0062   0.0951   1.0000
  11.000   1.0375   0.07060   0.06333   0.0082   0.0952   1.0000
  11.250   1.0184   0.07464   0.06757   0.0098   0.0955   1.0000
  11.500   0.9982   0.07919   0.07227   0.0103   0.0959   1.0000
  11.750   0.9813   0.08424   0.07744   0.0099   0.0965   1.0000
  12.000   0.8868   0.09688   0.09027  -0.0001   0.1072   1.0000
  12.250   0.8492   0.10880   0.10216  -0.0085   0.1122   1.0000
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