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SD6060-104-88 (sd6060-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: SD6060-104-88 (sd6060-il)
Reynolds number: 50,000
Max Cl/Cd: 34.94 at α=6.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-sd6060-il-50000-n5.txt
Download as CSV file: xf-sd6060-il-50000-n5.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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.4910   0.08675   0.08002  -0.0358   1.0000   0.0363
  -9.000  -0.4931   0.08202   0.07534  -0.0385   1.0000   0.0359
  -8.750  -0.5003   0.07736   0.07073  -0.0411   1.0000   0.0357
  -8.500  -0.5098   0.07333   0.06671  -0.0424   1.0000   0.0354
  -8.250  -0.5185   0.06935   0.06270  -0.0432   1.0000   0.0353
  -8.000  -0.5254   0.06539   0.05866  -0.0435   1.0000   0.0351
  -7.750  -0.5307   0.06154   0.05467  -0.0433   1.0000   0.0350
  -7.500  -0.5342   0.05786   0.05080  -0.0426   1.0000   0.0351
  -7.250  -0.5361   0.05436   0.04706  -0.0412   1.0000   0.0353
  -7.000  -0.5370   0.05106   0.04342  -0.0393   1.0000   0.0358
  -6.750  -0.5355   0.04808   0.04005  -0.0369   1.0000   0.0363
  -6.500  -0.5325   0.04500   0.03680  -0.0348   1.0000   0.0372
  -6.250  -0.5264   0.04249   0.03406  -0.0326   1.0000   0.0381
  -6.000  -0.5183   0.04007   0.03131  -0.0303   1.0000   0.0389
  -5.750  -0.5080   0.03767   0.02857  -0.0281   1.0000   0.0396
  -5.500  -0.4954   0.03541   0.02597  -0.0260   1.0000   0.0406
  -5.250  -0.4807   0.03333   0.02356  -0.0240   1.0000   0.0420
  -5.000  -0.4640   0.03139   0.02128  -0.0221   1.0000   0.0439
  -4.750  -0.4460   0.02982   0.01932  -0.0203   1.0000   0.0477
  -4.500  -0.4294   0.02845   0.01790  -0.0188   1.0000   0.0530
  -4.250  -0.4107   0.02717   0.01639  -0.0171   1.0000   0.0595
  -4.000  -0.3766   0.02579   0.01484  -0.0184   0.9932   0.0746
  -3.750  -0.3432   0.02437   0.01346  -0.0199   0.9860   0.1027
  -3.500  -0.3107   0.02283   0.01223  -0.0216   0.9789   0.1614
  -3.250  -0.2820   0.02108   0.01136  -0.0230   0.9715   0.3071
  -3.000  -0.2634   0.01964   0.01133  -0.0210   0.9631   0.5741
  -2.750  -0.2332   0.01967   0.01176  -0.0187   0.9572   0.7717
  -2.500  -0.1929   0.02007   0.01198  -0.0189   0.9514   0.8705
  -2.250  -0.1220   0.02051   0.01195  -0.0255   0.9509   0.9365
  -2.000  -0.0332   0.02055   0.01143  -0.0369   0.9528   0.9768
  -1.750   0.0361   0.02035   0.01085  -0.0458   0.9502   1.0000
  -1.500   0.0731   0.02032   0.01056  -0.0487   0.9406   1.0000
  -1.250   0.1082   0.02031   0.01035  -0.0511   0.9305   1.0000
  -1.000   0.1379   0.02033   0.01022  -0.0524   0.9189   1.0000
  -0.750   0.1670   0.02038   0.01012  -0.0534   0.9078   1.0000
  -0.500   0.1968   0.02044   0.01003  -0.0544   0.8975   1.0000
  -0.250   0.2267   0.02049   0.00998  -0.0553   0.8873   1.0000
   0.000   0.2495   0.02061   0.01001  -0.0549   0.8753   1.0000
   0.250   0.2722   0.02074   0.01008  -0.0543   0.8636   1.0000
   0.500   0.2956   0.02089   0.01015  -0.0538   0.8525   1.0000
   0.750   0.3217   0.02099   0.01020  -0.0537   0.8425   1.0000
   1.000   0.3445   0.02114   0.01032  -0.0529   0.8312   1.0000
   1.250   0.3650   0.02135   0.01050  -0.0518   0.8192   1.0000
   1.500   0.3865   0.02154   0.01068  -0.0507   0.8076   1.0000
   1.750   0.4094   0.02170   0.01082  -0.0498   0.7964   1.0000
   2.000   0.4348   0.02179   0.01092  -0.0491   0.7860   1.0000
   2.250   0.4569   0.02194   0.01111  -0.0479   0.7742   1.0000
   2.500   0.4776   0.02214   0.01133  -0.0466   0.7615   1.0000
   2.750   0.4991   0.02231   0.01154  -0.0452   0.7488   1.0000
   3.000   0.5211   0.02246   0.01174  -0.0439   0.7360   1.0000
   3.250   0.5437   0.02260   0.01196  -0.0427   0.7230   1.0000
   3.500   0.5666   0.02271   0.01214  -0.0414   0.7095   1.0000
   3.750   0.5896   0.02280   0.01231  -0.0401   0.6954   1.0000
   4.000   0.6127   0.02288   0.01248  -0.0388   0.6806   1.0000
   4.250   0.6360   0.02293   0.01267  -0.0374   0.6651   1.0000
   4.500   0.6597   0.02295   0.01279  -0.0360   0.6489   1.0000
   4.750   0.6842   0.02292   0.01286  -0.0347   0.6321   1.0000
   5.000   0.7047   0.02308   0.01315  -0.0330   0.6118   1.0000
   5.250   0.7278   0.02309   0.01332  -0.0315   0.5916   1.0000
   5.500   0.7489   0.02322   0.01357  -0.0298   0.5686   1.0000
   5.750   0.7708   0.02328   0.01374  -0.0281   0.5442   1.0000
   6.000   0.7917   0.02341   0.01397  -0.0264   0.5172   1.0000
   6.250   0.8115   0.02364   0.01428  -0.0245   0.4869   1.0000
   6.500   0.8307   0.02392   0.01467  -0.0226   0.4540   1.0000
   6.750   0.8494   0.02431   0.01503  -0.0207   0.4195   1.0000
   7.000   0.8658   0.02490   0.01560  -0.0187   0.3823   1.0000
   7.250   0.8808   0.02565   0.01628  -0.0167   0.3450   1.0000
   7.500   0.8939   0.02657   0.01709  -0.0145   0.3084   1.0000
   7.750   0.9055   0.02765   0.01811  -0.0124   0.2719   1.0000
   8.000   0.9149   0.02888   0.01921  -0.0102   0.2378   1.0000
   8.250   0.9231   0.03023   0.02051  -0.0081   0.2034   1.0000
   8.500   0.9282   0.03177   0.02196  -0.0059   0.1709   1.0000
   8.750   0.9307   0.03343   0.02347  -0.0036   0.1393   1.0000
   9.000   0.9323   0.03525   0.02512  -0.0013   0.1150   1.0000
   9.250   0.9361   0.03722   0.02708   0.0006   0.0941   1.0000
   9.500   0.9409   0.03934   0.02919   0.0024   0.0810   1.0000
   9.750   0.9484   0.04151   0.03141   0.0041   0.0716   1.0000
  10.000   0.9546   0.04366   0.03352   0.0054   0.0647   1.0000
  10.250   0.9662   0.04574   0.03587   0.0066   0.0574   1.0000
  10.500   0.9754   0.04797   0.03809   0.0077   0.0532   1.0000
  10.750   0.9934   0.05047   0.04095   0.0088   0.0501   1.0000
  11.000   1.0065   0.05338   0.04427   0.0099   0.0475   1.0000
  11.250   1.0128   0.05639   0.04756   0.0108   0.0456   1.0000
  11.500   1.0149   0.05942   0.05080   0.0115   0.0440   1.0000
  11.750   1.0167   0.06245   0.05388   0.0119   0.0420   1.0000
  12.000   1.0086   0.06643   0.05814   0.0121   0.0409   1.0000
  12.250   0.9961   0.07089   0.06293   0.0115   0.0403   1.0000
  12.500   0.9813   0.07593   0.06826   0.0102   0.0400   1.0000
  12.750   0.9643   0.08159   0.07417   0.0080   0.0399   1.0000
  13.000   0.9462   0.08784   0.08063   0.0050   0.0400   1.0000
  13.250   0.9273   0.09476   0.08771   0.0012   0.0403   1.0000
  13.500   0.9069   0.10266   0.09575  -0.0034   0.0406   1.0000
  13.750   0.8880   0.11102   0.10420  -0.0084   0.0410   1.0000
  14.000   0.8710   0.11976   0.11300  -0.0136   0.0414   1.0000
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