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RAF 6 AIRFOIL (raf6-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: RAF 6 AIRFOIL (raf6-il)
Reynolds number: 500,000
Max Cl/Cd: 84.99 at α=6.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-raf6-il-500000-n5.txt
Download as CSV file: xf-raf6-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: RAF 6 AIRFOIL                                   
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.2107   0.08767   0.08541  -0.0624   0.9812   0.0094
  -8.000  -0.1978   0.08372   0.08146  -0.0666   0.9790   0.0098
  -7.750  -0.1902   0.07994   0.07771  -0.0700   0.9740   0.0102
  -7.500  -0.1732   0.07455   0.07231  -0.0786   0.9695   0.0105
  -7.250  -0.1590   0.06967   0.06741  -0.0851   0.9628   0.0105
  -6.750  -0.1182   0.05941   0.05704  -0.0976   0.9526   0.0106
  -6.250  -0.0485   0.03521   0.03293  -0.1004   0.9264   0.0112
  -5.750  -0.0125   0.02636   0.02383  -0.1064   0.9110   0.0099
  -5.250   0.0055   0.03308   0.02984  -0.1118   0.9135   0.0079
  -5.000   0.0346   0.02856   0.02498  -0.1133   0.9070   0.0080
  -4.750   0.0613   0.02343   0.01939  -0.1135   0.8974   0.0081
  -4.500   0.0923   0.02176   0.01751  -0.1149   0.8889   0.0085
  -4.250   0.1253   0.01992   0.01539  -0.1163   0.8786   0.0091
  -4.000   0.1543   0.01578   0.01063  -0.1160   0.8666   0.0094
  -3.750   0.1836   0.01291   0.00716  -0.1158   0.8541   0.0101
  -3.500   0.2125   0.01179   0.00569  -0.1157   0.8417   0.0106
  -3.000   0.2677   0.01110   0.00479  -0.1156   0.8177   0.0124
  -2.750   0.2938   0.01062   0.00415  -0.1150   0.8040   0.0132
  -2.500   0.3195   0.01022   0.00361  -0.1144   0.7897   0.0141
  -2.250   0.3456   0.01000   0.00334  -0.1140   0.7779   0.0153
  -2.000   0.3722   0.00984   0.00314  -0.1137   0.7689   0.0171
  -1.750   0.3985   0.00958   0.00280  -0.1133   0.7597   0.0187
  -1.500   0.4247   0.00942   0.00261  -0.1129   0.7481   0.0211
  -1.250   0.4506   0.00934   0.00246  -0.1124   0.7335   0.0241
  -1.000   0.4762   0.00918   0.00222  -0.1118   0.7166   0.0284
  -0.750   0.5014   0.00914   0.00210  -0.1112   0.6948   0.0343
  -0.500   0.5251   0.00917   0.00200  -0.1102   0.6642   0.0415
  -0.250   0.5464   0.00933   0.00196  -0.1088   0.6193   0.0530
   0.000   0.5655   0.00960   0.00199  -0.1069   0.5593   0.0803
   0.250   0.5751   0.00809   0.00228  -0.1041   0.5061   0.7932
   0.500   0.6161   0.00829   0.00250  -0.1066   0.4512   1.0000
   0.750   0.6376   0.00856   0.00257  -0.1054   0.4240   1.0000
   1.000   0.6601   0.00880   0.00264  -0.1043   0.4016   1.0000
   1.250   0.6830   0.00903   0.00272  -0.1033   0.3808   1.0000
   1.500   0.7062   0.00927   0.00281  -0.1024   0.3595   1.0000
   1.750   0.7295   0.00951   0.00291  -0.1016   0.3371   1.0000
   2.000   0.7528   0.00976   0.00302  -0.1007   0.3160   1.0000
   2.250   0.7764   0.01001   0.00314  -0.1000   0.2981   1.0000
   2.500   0.8001   0.01024   0.00327  -0.0992   0.2827   1.0000
   2.750   0.8241   0.01047   0.00340  -0.0986   0.2699   1.0000
   3.000   0.8481   0.01070   0.00355  -0.0979   0.2587   1.0000
   3.250   0.8719   0.01094   0.00371  -0.0972   0.2488   1.0000
   3.500   0.8962   0.01115   0.00387  -0.0966   0.2410   1.0000
   3.750   0.9202   0.01138   0.00405  -0.0960   0.2349   1.0000
   4.000   0.9447   0.01157   0.00422  -0.0954   0.2297   1.0000
   4.250   0.9686   0.01181   0.00441  -0.0947   0.2239   1.0000
   4.500   0.9924   0.01203   0.00462  -0.0941   0.2190   1.0000
   4.750   1.0167   0.01223   0.00482  -0.0935   0.2148   1.0000
   5.000   1.0403   0.01247   0.00504  -0.0929   0.2102   1.0000
   5.250   1.0633   0.01274   0.00528  -0.0921   0.2057   1.0000
   5.500   1.0874   0.01293   0.00550  -0.0915   0.2027   1.0000
   5.750   1.1110   0.01315   0.00574  -0.0908   0.1988   1.0000
   6.000   1.1340   0.01339   0.00599  -0.0901   0.1948   1.0000
   6.250   1.1563   0.01367   0.00626  -0.0892   0.1912   1.0000
   6.500   1.1785   0.01391   0.00654  -0.0883   0.1881   1.0000
   6.750   1.2009   0.01413   0.00680  -0.0874   0.1849   1.0000
   7.000   1.2228   0.01439   0.00708  -0.0865   0.1812   1.0000
   7.250   1.2442   0.01467   0.00740  -0.0854   0.1778   1.0000
   7.500   1.2648   0.01501   0.00775  -0.0843   0.1744   1.0000
   7.750   1.2869   0.01525   0.00806  -0.0834   0.1707   1.0000
   8.000   1.3077   0.01558   0.00837  -0.0824   0.1623   1.0000
   8.250   1.3284   0.01591   0.00871  -0.0813   0.1533   1.0000
   8.500   1.3480   0.01632   0.00909  -0.0802   0.1442   1.0000
   8.750   1.3667   0.01679   0.00951  -0.0788   0.1319   1.0000
   9.000   1.3843   0.01734   0.01002  -0.0774   0.1181   1.0000
   9.250   1.4001   0.01801   0.01062  -0.0757   0.1012   1.0000
   9.500   1.4119   0.01899   0.01144  -0.0734   0.0786   1.0000
   9.750   1.4075   0.02121   0.01329  -0.0688   0.0210   1.0000
  10.000   1.4187   0.02222   0.01434  -0.0665   0.0136   1.0000
  10.250   1.4319   0.02307   0.01525  -0.0646   0.0109   1.0000
  10.500   1.4455   0.02389   0.01616  -0.0627   0.0093   1.0000
  10.750   1.4581   0.02478   0.01714  -0.0609   0.0082   1.0000
  11.000   1.4702   0.02570   0.01815  -0.0590   0.0072   1.0000
  11.250   1.4806   0.02677   0.01931  -0.0569   0.0066   1.0000
  11.500   1.4910   0.02783   0.02048  -0.0550   0.0061   1.0000
  11.750   1.4999   0.02902   0.02178  -0.0530   0.0057   1.0000
  12.000   1.5070   0.03037   0.02323  -0.0509   0.0053   1.0000
  12.500   1.5181   0.03343   0.02654  -0.0469   0.0047   1.0000
  12.750   1.5227   0.03509   0.02832  -0.0451   0.0044   1.0000
  13.000   1.5262   0.03691   0.03025  -0.0434   0.0042   1.0000
  13.250   1.5274   0.03901   0.03247  -0.0418   0.0040   1.0000
  13.500   1.5248   0.04154   0.03512  -0.0401   0.0039   1.0000
  13.750   1.5204   0.04438   0.03811  -0.0387   0.0038   1.0000
  14.000   1.5165   0.04733   0.04120  -0.0377   0.0037   1.0000
  14.250   1.5103   0.05070   0.04473  -0.0369   0.0036   1.0000
  14.500   1.5021   0.05455   0.04874  -0.0366   0.0035   1.0000
  14.750   1.4919   0.05895   0.05329  -0.0368   0.0034   1.0000
  15.000   1.4795   0.06396   0.05846  -0.0375   0.0034   1.0000
  15.250   1.4651   0.06964   0.06431  -0.0390   0.0033   1.0000
  15.500   1.4479   0.07619   0.07103  -0.0411   0.0033   1.0000
  15.750   1.4288   0.08338   0.07840  -0.0438   0.0033   1.0000
  16.000   1.4073   0.09112   0.08631  -0.0468   0.0033   1.0000
  16.250   1.3843   0.09918   0.09453  -0.0499   0.0033   1.0000
  16.500   1.3616   0.10717   0.10267  -0.0530   0.0033   1.0000
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