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RAF 26 AIRFOIL (raf26-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: RAF 26 AIRFOIL (raf26-il)
Reynolds number: 1,000,000
Max Cl/Cd: 76.76 at α=3.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-raf26-il-1000000-n5.txt
Download as CSV file: xf-raf26-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: RAF 26 AIRFOIL                                  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.5125   0.08550   0.08394  -0.0179   1.0000   0.0028
  -8.250  -0.5167   0.08171   0.08018  -0.0190   1.0000   0.0028
  -8.000  -0.5259   0.07813   0.07664  -0.0194   1.0000   0.0027
  -7.750  -0.5326   0.07409   0.07263  -0.0212   1.0000   0.0027
  -6.750  -0.5051   0.01737   0.01369  -0.0571   0.9886   0.0022
  -6.500  -0.4768   0.01536   0.01132  -0.0579   0.9873   0.0024
  -6.250  -0.4539   0.01372   0.00938  -0.0571   0.9838   0.0025
  -6.000  -0.4265   0.01255   0.00799  -0.0573   0.9810   0.0027
  -5.750  -0.3971   0.01165   0.00691  -0.0578   0.9789   0.0030
  -5.500  -0.3724   0.01107   0.00621  -0.0572   0.9744   0.0032
  -5.250  -0.3462   0.01016   0.00511  -0.0570   0.9693   0.0034
  -4.750  -0.2951   0.00930   0.00416  -0.0561   0.9484   0.0043
  -4.500  -0.2607   0.00881   0.00360  -0.0576   0.9409   0.0049
  -4.250  -0.2214   0.00835   0.00304  -0.0602   0.9340   0.0054
  -3.750  -0.1318   0.00750   0.00201  -0.0681   0.9200   0.0085
  -3.500  -0.0925   0.00722   0.00165  -0.0708   0.9096   0.0126
  -3.250  -0.0583   0.00704   0.00141  -0.0723   0.8922   0.0228
  -3.000  -0.0300   0.00695   0.00125  -0.0724   0.8704   0.0348
  -2.750  -0.0040   0.00684   0.00112  -0.0720   0.8553   0.0491
  -2.500   0.0216   0.00668   0.00100  -0.0715   0.8422   0.0757
  -2.250   0.0470   0.00654   0.00089  -0.0710   0.8293   0.1038
  -2.000   0.0721   0.00640   0.00080  -0.0704   0.8143   0.1366
  -1.750   0.0967   0.00628   0.00072  -0.0697   0.7948   0.1755
  -1.500   0.1209   0.00620   0.00064  -0.0689   0.7718   0.2140
  -1.250   0.1449   0.00606   0.00058  -0.0682   0.7499   0.2680
  -1.000   0.1687   0.00594   0.00056  -0.0673   0.7262   0.3311
  -0.750   0.1917   0.00586   0.00054  -0.0664   0.6947   0.3986
  -0.500   0.2153   0.00591   0.00054  -0.0655   0.6616   0.4313
  -0.250   0.2396   0.00596   0.00055  -0.0647   0.6317   0.4592
   0.000   0.2634   0.00595   0.00057  -0.0639   0.6016   0.5086
   0.250   0.2855   0.00589   0.00062  -0.0628   0.5594   0.5947
   0.500   0.3033   0.00606   0.00071  -0.0608   0.4594   0.6928
   0.750   0.3237   0.00614   0.00081  -0.0592   0.4097   0.7634
   1.000   0.3448   0.00604   0.00089  -0.0577   0.3866   0.8468
   1.250   0.4234   0.00666   0.00115  -0.0699   0.2266   0.9901
   1.500   0.4563   0.00706   0.00131  -0.0714   0.1666   1.0000
   1.750   0.4795   0.00732   0.00143  -0.0704   0.1298   1.0000
   2.000   0.5020   0.00764   0.00158  -0.0694   0.0860   1.0000
   2.250   0.5266   0.00777   0.00170  -0.0687   0.0807   1.0000
   2.500   0.5513   0.00790   0.00184  -0.0680   0.0780   1.0000
   2.750   0.5757   0.00808   0.00199  -0.0673   0.0730   1.0000
   3.000   0.6003   0.00822   0.00214  -0.0666   0.0689   1.0000
   3.250   0.6253   0.00834   0.00228  -0.0660   0.0653   1.0000
   3.500   0.6495   0.00854   0.00245  -0.0652   0.0559   1.0000
   3.750   0.6732   0.00877   0.00260  -0.0644   0.0381   1.0000
   4.000   0.6951   0.00921   0.00289  -0.0632   0.0127   1.0000
   4.250   0.7187   0.00949   0.00318  -0.0623   0.0082   1.0000
   4.500   0.7424   0.00975   0.00350  -0.0614   0.0069   1.0000
   4.750   0.7654   0.01008   0.00386  -0.0605   0.0058   1.0000
   5.000   0.7880   0.01048   0.00430  -0.0594   0.0048   1.0000
   5.250   0.8113   0.01079   0.00465  -0.0584   0.0042   1.0000
   5.500   0.8341   0.01116   0.00506  -0.0574   0.0038   1.0000
   5.750   0.8562   0.01162   0.00555  -0.0563   0.0033   1.0000
   6.000   0.8765   0.01230   0.00635  -0.0548   0.0031   1.0000
   6.250   0.8985   0.01279   0.00691  -0.0537   0.0029   1.0000
   6.500   0.9196   0.01340   0.00762  -0.0523   0.0026   1.0000
   6.750   0.9400   0.01414   0.00846  -0.0509   0.0025   1.0000
   7.000   0.9600   0.01495   0.00938  -0.0494   0.0023   1.0000
   7.250   0.9796   0.01588   0.01043  -0.0479   0.0022   1.0000
   7.500   1.0011   0.01646   0.01108  -0.0468   0.0021   1.0000
   7.750   1.0232   0.01692   0.01158  -0.0460   0.0019   1.0000
   8.000   1.0415   0.01805   0.01285  -0.0444   0.0018   1.0000
   8.250   1.0566   0.01982   0.01487  -0.0422   0.0017   1.0000
   8.500   1.0743   0.02114   0.01642  -0.0406   0.0016   1.0000
   8.750   1.0905   0.02269   0.01822  -0.0387   0.0016   1.0000
   9.000   1.1042   0.02464   0.02045  -0.0365   0.0015   1.0000
   9.250   1.1148   0.02702   0.02316  -0.0339   0.0015   1.0000
   9.500   1.1202   0.03010   0.02661  -0.0308   0.0014   1.0000
   9.750   1.1030   0.03671   0.03388  -0.0250   0.0014   1.0000
  10.000   1.0421   0.05056   0.04845  -0.0159   0.0014   1.0000
  10.250   1.0079   0.05655   0.05466  -0.0106   0.0014   1.0000
  10.500   0.9774   0.06217   0.06041  -0.0084   0.0013   1.0000
  10.750   0.9562   0.06718   0.06553  -0.0092   0.0014   1.0000
  11.000   0.9349   0.07368   0.07215  -0.0128   0.0014   1.0000
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