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RG-12 (rg12-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: RG-12 (rg12-il)
Reynolds number: 200,000
Max Cl/Cd: 58.92 at α=4.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-rg12-il-200000-n5.txt
Download as CSV file: xf-rg12-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: RG-12                                           
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.5373   0.08416   0.08059  -0.0285   1.0000   0.0124
  -9.500  -0.5455   0.07838   0.07486  -0.0316   1.0000   0.0123
  -9.250  -0.5551   0.07220   0.06874  -0.0355   1.0000   0.0121
  -9.000  -0.5734   0.06368   0.06022  -0.0425   1.0000   0.0119
  -8.750  -0.5967   0.05843   0.05491  -0.0434   1.0000   0.0118
  -8.500  -0.6132   0.05357   0.04992  -0.0430   1.0000   0.0117
  -8.250  -0.6256   0.04884   0.04498  -0.0418   1.0000   0.0115
  -8.000  -0.6344   0.04413   0.03999  -0.0400   1.0000   0.0114
  -7.750  -0.6388   0.03955   0.03504  -0.0379   1.0000   0.0113
  -7.500  -0.6378   0.03543   0.03049  -0.0356   1.0000   0.0112
  -7.250  -0.6316   0.03185   0.02647  -0.0334   1.0000   0.0112
  -7.000  -0.6215   0.02872   0.02288  -0.0313   1.0000   0.0113
  -6.750  -0.6077   0.02613   0.01985  -0.0294   1.0000   0.0114
  -6.500  -0.5913   0.02401   0.01736  -0.0277   1.0000   0.0117
  -6.250  -0.5732   0.02224   0.01527  -0.0262   1.0000   0.0120
  -6.000  -0.5539   0.02079   0.01356  -0.0247   1.0000   0.0124
  -5.750  -0.5341   0.01960   0.01217  -0.0233   1.0000   0.0128
  -5.500  -0.5150   0.01818   0.01062  -0.0220   1.0000   0.0134
  -5.250  -0.4846   0.01741   0.00981  -0.0231   0.9975   0.0155
  -5.000  -0.4508   0.01661   0.00890  -0.0246   0.9942   0.0174
  -4.750  -0.4187   0.01572   0.00783  -0.0257   0.9902   0.0188
  -4.500  -0.3857   0.01480   0.00682  -0.0271   0.9861   0.0216
  -4.250  -0.3505   0.01418   0.00611  -0.0288   0.9827   0.0282
  -4.000  -0.3200   0.01354   0.00552  -0.0296   0.9768   0.0433
  -3.750  -0.2865   0.01298   0.00514  -0.0312   0.9721   0.0784
  -3.500  -0.2544   0.01242   0.00477  -0.0324   0.9669   0.1208
  -3.250  -0.2227   0.01189   0.00440  -0.0336   0.9606   0.1752
  -3.000  -0.1877   0.01133   0.00410  -0.0355   0.9563   0.2464
  -2.750  -0.1594   0.01072   0.00383  -0.0360   0.9481   0.3384
  -2.500  -0.1264   0.00996   0.00359  -0.0375   0.9433   0.4693
  -2.250  -0.1009   0.00933   0.00352  -0.0369   0.9344   0.6104
  -2.000  -0.0692   0.00912   0.00357  -0.0371   0.9281   0.7076
  -1.750  -0.0392   0.00904   0.00351  -0.0372   0.9187   0.7487
  -1.500  -0.0082   0.00898   0.00345  -0.0374   0.9093   0.7772
  -1.250   0.0248   0.00892   0.00335  -0.0381   0.9004   0.7992
  -1.000   0.0559   0.00887   0.00326  -0.0384   0.8891   0.8174
  -0.750   0.0860   0.00883   0.00320  -0.0384   0.8766   0.8331
  -0.500   0.1160   0.00879   0.00312  -0.0384   0.8631   0.8473
  -0.250   0.1456   0.00876   0.00305  -0.0384   0.8482   0.8601
   0.000   0.1741   0.00875   0.00299  -0.0381   0.8322   0.8728
   0.250   0.2008   0.00875   0.00295  -0.0374   0.8143   0.8848
   0.500   0.2276   0.00877   0.00292  -0.0367   0.7955   0.8959
   0.750   0.2548   0.00879   0.00287  -0.0362   0.7761   0.9060
   1.000   0.2814   0.00883   0.00285  -0.0356   0.7551   0.9157
   1.250   0.3094   0.00889   0.00283  -0.0354   0.7336   0.9236
   1.500   0.3374   0.00895   0.00283  -0.0352   0.7104   0.9313
   1.750   0.3661   0.00904   0.00283  -0.0353   0.6868   0.9385
   2.000   0.3954   0.00914   0.00285  -0.0355   0.6619   0.9452
   2.250   0.4253   0.00927   0.00291  -0.0359   0.6361   0.9521
   2.500   0.4556   0.00941   0.00296  -0.0364   0.6087   0.9589
   2.750   0.4865   0.00958   0.00304  -0.0371   0.5798   0.9662
   3.000   0.5179   0.00976   0.00313  -0.0379   0.5491   0.9735
   3.250   0.5490   0.00997   0.00328  -0.0388   0.5179   0.9818
   3.500   0.5813   0.01021   0.00342  -0.0399   0.4851   0.9902
   3.750   0.6119   0.01048   0.00358  -0.0408   0.4516   1.0000
   4.000   0.6304   0.01075   0.00375  -0.0392   0.4216   1.0000
   4.250   0.6507   0.01106   0.00396  -0.0379   0.3897   1.0000
   4.500   0.6720   0.01141   0.00422  -0.0368   0.3571   1.0000
   4.750   0.6941   0.01178   0.00449  -0.0359   0.3243   1.0000
   5.000   0.7163   0.01219   0.00479  -0.0350   0.2906   1.0000
   5.250   0.7387   0.01263   0.00513  -0.0342   0.2569   1.0000
   5.500   0.7611   0.01311   0.00550  -0.0334   0.2237   1.0000
   5.750   0.7831   0.01364   0.00591  -0.0327   0.1897   1.0000
   6.000   0.8051   0.01422   0.00640  -0.0319   0.1565   1.0000
   6.250   0.8266   0.01486   0.00691  -0.0311   0.1253   1.0000
   6.500   0.8481   0.01553   0.00746  -0.0303   0.0982   1.0000
   6.750   0.8697   0.01619   0.00805  -0.0294   0.0754   1.0000
   7.000   0.8909   0.01690   0.00871  -0.0286   0.0584   1.0000
   7.250   0.9121   0.01762   0.00944  -0.0276   0.0461   1.0000
   7.500   0.9321   0.01846   0.01032  -0.0266   0.0365   1.0000
   7.750   0.9524   0.01926   0.01117  -0.0256   0.0288   1.0000
   8.000   0.9715   0.02018   0.01219  -0.0243   0.0241   1.0000
   8.250   0.9910   0.02102   0.01310  -0.0232   0.0199   1.0000
   8.500   1.0073   0.02221   0.01438  -0.0217   0.0169   1.0000
   8.750   1.0243   0.02328   0.01561  -0.0202   0.0152   1.0000
   9.000   1.0405   0.02441   0.01686  -0.0187   0.0136   1.0000
   9.250   1.0527   0.02589   0.01842  -0.0169   0.0122   1.0000
   9.500   1.0676   0.02713   0.01987  -0.0153   0.0111   1.0000
   9.750   1.0819   0.02835   0.02126  -0.0137   0.0101   1.0000
  10.000   1.0939   0.02972   0.02278  -0.0119   0.0094   1.0000
  10.250   1.1027   0.03119   0.02439  -0.0097   0.0089   1.0000
  10.500   1.1093   0.03275   0.02610  -0.0073   0.0086   1.0000
  10.750   1.1133   0.03456   0.02805  -0.0049   0.0083   1.0000
  11.000   1.1122   0.03699   0.03067  -0.0023   0.0079   1.0000
  11.250   1.1109   0.03953   0.03341  -0.0001   0.0078   1.0000
  11.500   1.1094   0.04201   0.03615   0.0018   0.0077   1.0000
  11.750   1.1051   0.04483   0.03922   0.0032   0.0076   1.0000
  12.000   1.0986   0.04799   0.04263   0.0041   0.0075   1.0000
  12.250   1.0894   0.05166   0.04656   0.0043   0.0074   1.0000
  12.500   1.0781   0.05588   0.05101   0.0036   0.0074   1.0000
  12.750   1.0655   0.06066   0.05602   0.0020   0.0074   1.0000
  13.000   1.0520   0.06602   0.06158  -0.0005   0.0074   1.0000
  13.250   1.0340   0.07270   0.06849  -0.0043   0.0074   1.0000
  13.500   1.0184   0.07952   0.07549  -0.0085   0.0074   1.0000
  13.750   1.0003   0.08748   0.08362  -0.0137   0.0074   1.0000
  14.000   0.9817   0.09608   0.09237  -0.0193   0.0075   1.0000
  14.250   0.9609   0.10587   0.10230  -0.0255   0.0076   1.0000
  14.500   0.9406   0.11613   0.11267  -0.0318   0.0077   1.0000
  14.750   0.9208   0.12669   0.12330  -0.0379   0.0078   1.0000
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