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NACA 66(1)-212 (naca661212-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: NACA 66(1)-212 (naca661212-il)
Reynolds number: 200,000
Max Cl/Cd: 47.64 at α=4.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-naca661212-il-200000.txt
Download as CSV file: xf-naca661212-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 66(1)-212                                  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.3907   0.09039   0.08709  -0.0502   1.0000   0.0582
 -10.500  -0.4024   0.08609   0.08284  -0.0511   1.0000   0.0597
 -10.250  -0.4226   0.08243   0.07926  -0.0506   1.0000   0.0606
 -10.000  -0.4454   0.07998   0.07688  -0.0481   1.0000   0.0603
  -9.750  -0.4687   0.07677   0.07373  -0.0466   1.0000   0.0596
  -9.500  -0.6619   0.08048   0.07692  -0.0456   0.9993   0.0507
  -9.250  -0.6671   0.07642   0.07253  -0.0485   0.9920   0.0509
  -9.000  -0.6584   0.06708   0.06338  -0.0509   0.9902   0.0527
  -8.750  -0.6413   0.06379   0.06010  -0.0524   0.9869   0.0545
  -8.500  -0.6284   0.06015   0.05632  -0.0546   0.9834   0.0570
  -8.250  -0.6253   0.05694   0.05281  -0.0546   0.9763   0.0606
  -8.000  -0.6230   0.05221   0.04752  -0.0555   0.9711   0.0654
  -7.750  -0.6058   0.04964   0.04509  -0.0557   0.9668   0.0686
  -7.250  -0.5772   0.04382   0.03870  -0.0559   0.9586   0.0810
  -7.000  -0.5586   0.04186   0.03659  -0.0557   0.9551   0.0869
  -6.750  -0.5524   0.03959   0.03406  -0.0535   0.9490   0.0950
  -6.500  -0.5323   0.03768   0.03186  -0.0537   0.9459   0.1080
  -6.250  -0.4928   0.03087   0.02349  -0.0506   0.9441   0.0513
  -6.000  -0.4594   0.02705   0.01947  -0.0520   0.9432   0.0485
  -5.750  -0.4500   0.02570   0.01793  -0.0485   0.9371   0.0478
  -5.500  -0.4222   0.02412   0.01614  -0.0485   0.9347   0.0475
  -5.250  -0.3907   0.02288   0.01473  -0.0492   0.9329   0.0487
  -5.000  -0.3579   0.02227   0.01393  -0.0502   0.9313   0.0508
  -4.750  -0.3247   0.02051   0.01218  -0.0514   0.9303   0.0524
  -4.500  -0.2946   0.01944   0.01117  -0.0522   0.9290   0.0553
  -4.250  -0.2939   0.01930   0.01102  -0.0473   0.9220   0.0569
  -4.000  -0.2712   0.01889   0.01057  -0.0466   0.9190   0.0616
  -3.750  -0.2466   0.01821   0.00989  -0.0465   0.9169   0.0664
  -3.500  -0.2189   0.01770   0.00937  -0.0469   0.9153   0.0744
  -3.250  -0.2116   0.01756   0.00925  -0.0433   0.9107   0.0859
  -3.000  -0.2069   0.01686   0.00899  -0.0395   0.9054   0.1654
  -2.750  -0.2151   0.01475   0.00927  -0.0330   0.9019   0.7112
  -2.500  -0.1909   0.01543   0.01003  -0.0309   0.9004   0.7774
  -2.000  -0.1830   0.01689   0.01151  -0.0197   0.8913   0.8291
  -1.750  -0.1687   0.01783   0.01249  -0.0148   0.8886   0.8523
  -1.500  -0.1467   0.01848   0.01310  -0.0121   0.8866   0.8714
  -1.250  -0.1165   0.01906   0.01363  -0.0112   0.8854   0.8861
  -1.000  -0.1126   0.01945   0.01401  -0.0062   0.8802   0.8970
  -0.750  -0.0940   0.01968   0.01419  -0.0043   0.8763   0.9069
  -0.500  -0.0623   0.01976   0.01421  -0.0053   0.8740   0.9115
  -0.250  -0.0346   0.01970   0.01409  -0.0058   0.8717   0.9163
   0.000   0.0047   0.01971   0.01405  -0.0083   0.8703   0.9185
   0.250   0.0048   0.01990   0.01424  -0.0037   0.8634   0.9247
   0.500   0.0269   0.01986   0.01417  -0.0032   0.8595   0.9286
   0.750   0.0586   0.01977   0.01406  -0.0043   0.8570   0.9315
   1.000   0.1020   0.01975   0.01403  -0.0077   0.8555   0.9323
   1.250   0.1057   0.01995   0.01425  -0.0039   0.8476   0.9375
   1.500   0.1379   0.01994   0.01425  -0.0052   0.8442   0.9401
   1.750   0.1780   0.01988   0.01421  -0.0078   0.8420   0.9418
   2.000   0.2228   0.01979   0.01416  -0.0113   0.8406   0.9427
   2.250   0.2252   0.02000   0.01440  -0.0073   0.8309   0.9487
   2.500   0.2700   0.01987   0.01433  -0.0107   0.8283   0.9493
   2.750   0.3222   0.01957   0.01412  -0.0152   0.8265   0.9489
   3.000   0.3512   0.01935   0.01398  -0.0155   0.8170   0.9518
   3.250   0.4393   0.01700   0.01172  -0.0235   0.8110   0.9463
   3.500   0.4880   0.01524   0.01001  -0.0250   0.7926   0.9461
   3.750   0.5329   0.01355   0.00831  -0.0259   0.7657   0.9464
   4.000   0.5639   0.01282   0.00763  -0.0255   0.7368   0.9486
   4.250   0.5841   0.01226   0.00705  -0.0232   0.6716   0.9526
   4.500   0.5715   0.01312   0.00652  -0.0148   0.4091   0.9602
   4.750   0.5550   0.01559   0.00741  -0.0084   0.1177   0.9691
   5.000   0.5747   0.01673   0.00824  -0.0078   0.0727   0.9737
   5.250   0.6036   0.01753   0.00909  -0.0088   0.0633   0.9771
   5.500   0.6248   0.01859   0.01012  -0.0086   0.0570   0.9821
   5.750   0.6545   0.01933   0.01092  -0.0096   0.0521   0.9854
   6.000   0.6849   0.02036   0.01196  -0.0109   0.0488   0.9883
   6.250   0.7168   0.02193   0.01347  -0.0122   0.0464   0.9904
   6.500   0.7517   0.02333   0.01496  -0.0138   0.0439   0.9922
   6.750   0.7869   0.02467   0.01643  -0.0154   0.0421   0.9943
   7.000   0.8245   0.02651   0.01846  -0.0172   0.0415   0.9957
   7.250   0.8608   0.02887   0.02110  -0.0187   0.0416   0.9976
   7.500   0.8941   0.03175   0.02432  -0.0199   0.0425   1.0000
   7.750   0.9015   0.03355   0.02636  -0.0164   0.0426   1.0000
   8.000   0.9036   0.03527   0.02830  -0.0122   0.0427   1.0000
   8.250   0.9203   0.03875   0.03188  -0.0105   0.0464   1.0000
  10.000   0.8596   0.06053   0.05637   0.0153   0.0697   1.0000
  10.250   0.8317   0.06189   0.05799   0.0204   0.0691   1.0000
  10.500   0.8002   0.06447   0.06076   0.0242   0.0688   1.0000
  10.750   0.7708   0.06825   0.06469   0.0261   0.0686   1.0000
  11.000   0.7433   0.07302   0.06959   0.0266   0.0686   1.0000
  11.250   0.7169   0.07854   0.07521   0.0260   0.0688   1.0000
  11.500   0.6909   0.08473   0.08148   0.0242   0.0689   1.0000
  11.750   0.6641   0.09170   0.08851   0.0212   0.0690   1.0000
  12.000   0.6354   0.09990   0.09677   0.0162   0.0691   1.0000
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