Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

NACA 66(4)-221 (naca664221-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: NACA 66(4)-221 (naca664221-il)
Reynolds number: 200,000
Max Cl/Cd: 29.56 at α=9.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-naca664221-il-200000.txt
Download as CSV file: xf-naca664221-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 66(4)-221                                  
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -15.750  -0.6801   0.06776   0.06237  -0.1265   0.9287   0.0482
 -15.500  -0.6830   0.06428   0.05877  -0.1262   0.9229   0.0477
 -15.250  -0.6937   0.06094   0.05525  -0.1252   0.9177   0.0471
 -15.000  -0.7061   0.05783   0.05190  -0.1237   0.9131   0.0466
 -14.750  -0.7181   0.05478   0.04861  -0.1218   0.9079   0.0461
 -14.500  -0.7277   0.05200   0.04556  -0.1197   0.9031   0.0456
 -14.250  -0.7353   0.04937   0.04262  -0.1174   0.8991   0.0452
 -14.000  -0.7365   0.04715   0.04015  -0.1154   0.8954   0.0451
 -13.750  -0.7321   0.04504   0.03779  -0.1140   0.8915   0.0449
 -13.500  -0.7214   0.04318   0.03571  -0.1129   0.8879   0.0451
 -13.250  -0.7068   0.04158   0.03390  -0.1120   0.8846   0.0453
 -13.000  -0.6907   0.04026   0.03240  -0.1113   0.8818   0.0460
 -12.750  -0.6744   0.03909   0.03105  -0.1105   0.8792   0.0468
 -12.500  -0.6540   0.03791   0.02970  -0.1103   0.8764   0.0476
 -12.250  -0.6305   0.03686   0.02847  -0.1103   0.8738   0.0482
 -12.000  -0.6007   0.03589   0.02735  -0.1109   0.8716   0.0489
 -11.750  -0.5548   0.03510   0.02667  -0.1131   0.8700   0.0503
 -11.500  -0.5274   0.03451   0.02609  -0.1134   0.8679   0.0517
 -11.250  -0.5017   0.03397   0.02551  -0.1134   0.8660   0.0533
 -11.000  -0.4791   0.03347   0.02492  -0.1130   0.8641   0.0549
 -10.750  -0.4561   0.03291   0.02443  -0.1127   0.8625   0.0574
 -10.500  -0.4383   0.03241   0.02395  -0.1121   0.8607   0.0600
 -10.250  -0.4202   0.03191   0.02342  -0.1116   0.8587   0.0623
 -10.000  -0.4061   0.03121   0.02280  -0.1107   0.8567   0.0651
  -9.750  -0.3931   0.03059   0.02220  -0.1096   0.8546   0.0685
  -9.500  -0.3815   0.02993   0.02154  -0.1083   0.8526   0.0727
  -9.250  -0.3723   0.02922   0.02087  -0.1068   0.8506   0.0781
  -9.000  -0.3654   0.02841   0.02011  -0.1048   0.8486   0.0866
  -8.750  -0.3608   0.02754   0.01933  -0.1024   0.8466   0.1024
  -8.500  -0.3670   0.02627   0.01845  -0.0988   0.8447   0.1506
  -8.250  -0.3844   0.02486   0.01760  -0.0936   0.8429   0.2411
  -8.000  -0.4028   0.02387   0.01708  -0.0885   0.8404   0.3155
  -7.750  -0.4228   0.02329   0.01688  -0.0826   0.8376   0.3762
  -7.500  -0.4438   0.02310   0.01703  -0.0759   0.8348   0.4311
  -7.250  -0.4557   0.02342   0.01783  -0.0696   0.8326   0.5004
  -6.000  -0.6677   0.02714   0.02104  -0.0123   0.8263   0.4468
  -5.750  -0.7122   0.02908   0.02249  -0.0009   0.8335   0.3728
  -5.500  -0.7390   0.02861   0.02240   0.0076   0.8398   0.4399
  -5.250  -0.7183   0.03003   0.02504   0.0107   0.8423   0.6430
  -5.000  -0.1676   0.03817   0.03248  -0.0661   0.8254   0.6844
  -4.750  -0.1236   0.03882   0.03304  -0.0685   0.8249   0.6873
  -4.500  -0.0722   0.03946   0.03359  -0.0721   0.8246   0.6891
  -4.250  -0.0605   0.04095   0.03509  -0.0695   0.8232   0.6930
  -4.000  -0.4647   0.04184   0.03649   0.0003   0.8239   0.7234
  -3.750  -0.3903   0.04539   0.04000  -0.0054   0.8221   0.7252
  -3.500  -0.6915   0.03528   0.03001   0.0395   0.8515   0.7286
  -3.250  -0.6642   0.03673   0.03139   0.0403   0.8482   0.7412
  -3.000  -0.5729   0.04433   0.03911   0.0358   0.8476   0.7525
  -2.750  -0.5181   0.04680   0.04151   0.0323   0.8459   0.7614
  -2.500  -0.4409   0.04917   0.04377   0.0241   0.8450   0.7629
  -2.250  -0.5129   0.04703   0.04165   0.0405   0.8347   0.7786
  -2.000  -0.4572   0.04848   0.04303   0.0359   0.8312   0.7801
  -1.750  -0.3942   0.04983   0.04430   0.0295   0.8288   0.7814
  -1.500  -0.3299   0.05089   0.04528   0.0224   0.8268   0.7826
  -1.250  -0.4272   0.04830   0.04270   0.0435   0.8154   0.7980
  -1.000  -0.3812   0.04893   0.04326   0.0400   0.8109   0.7992
  -0.750  -0.3219   0.04982   0.04408   0.0341   0.8080   0.8002
  -0.500  -0.3083   0.04985   0.04409   0.0359   0.7981   0.8025
   0.000  -0.1339   0.04926   0.04331   0.0163   0.7714   0.8036
   0.250  -0.0694   0.04939   0.04340   0.0097   0.7695   0.8054
   0.500  -0.0089   0.04945   0.04342   0.0038   0.7682   0.8077
   0.750  -0.1741   0.04678   0.04074   0.0365   0.7527   0.8192
   1.000  -0.1670   0.04658   0.04053   0.0394   0.7443   0.8211
   1.250  -0.1524   0.04626   0.04020   0.0410   0.7382   0.8232
   1.500  -0.1251   0.04586   0.03977   0.0406   0.7353   0.8248
   1.750  -0.0926   0.04548   0.03935   0.0395   0.7334   0.8262
   2.000  -0.0542   0.04522   0.03906   0.0374   0.7321   0.8276
   2.250  -0.1053   0.04356   0.03736   0.0484   0.7177   0.8316
   2.500  -0.0708   0.04308   0.03686   0.0467   0.7159   0.8323
   2.750  -0.0327   0.04268   0.03643   0.0443   0.7146   0.8336
   3.000  -0.0492   0.04215   0.03589   0.0493   0.7010   0.8350
   3.250  -0.0114   0.04179   0.03552   0.0474   0.6990   0.8354
   3.500   0.0281   0.04148   0.03522   0.0452   0.6977   0.8357
   3.750   0.0207   0.04155   0.03531   0.0496   0.6848   0.8371
   4.000   0.0574   0.04119   0.03497   0.0479   0.6826   0.8378
   4.250   0.0958   0.04081   0.03461   0.0460   0.6811   0.8382
   4.500   0.1369   0.04037   0.03420   0.0437   0.6800   0.8386
   4.750   0.1316   0.04053   0.03437   0.0473   0.6663   0.8397
   5.000   0.1700   0.04005   0.03393   0.0454   0.6647   0.8403
   5.250   0.2102   0.03950   0.03342   0.0433   0.6635   0.8408
   5.500   0.2113   0.03973   0.03367   0.0459   0.6504   0.8421
   5.750   0.2497   0.03912   0.03312   0.0442   0.6487   0.8428
   6.000   0.2905   0.03839   0.03244   0.0423   0.6474   0.8438
   6.250   0.2954   0.03866   0.03275   0.0444   0.6348   0.8456
   6.500   0.3361   0.03779   0.03194   0.0425   0.6330   0.8464
   6.750   0.3786   0.03679   0.03101   0.0404   0.6316   0.8472
   7.000   0.3875   0.03703   0.03129   0.0419   0.6195   0.8486
   7.250   0.4292   0.03594   0.03028   0.0400   0.6175   0.8496
   7.500   0.4732   0.03465   0.02908   0.0379   0.6161   0.8505
   7.750   0.4890   0.03446   0.02895   0.0389   0.6038   0.8519
   8.000   0.5507   0.03102   0.02559   0.0361   0.6006   0.8526
   8.250   0.5696   0.03006   0.02470   0.0377   0.5861   0.8539
   8.500   0.5908   0.02944   0.02415   0.0388   0.5716   0.8553
   8.750   0.6218   0.02845   0.02322   0.0387   0.5568   0.8565
   9.000   0.6720   0.02638   0.02114   0.0368   0.5357   0.8576
   9.250   0.7157   0.02483   0.01939   0.0357   0.4910   0.8588
   9.500   0.7328   0.02479   0.01901   0.0372   0.4338   0.8606
   9.750   0.7313   0.02584   0.01976   0.0405   0.3819   0.8632
  10.000   0.7249   0.02729   0.02090   0.0439   0.3302   0.8660
  10.250   0.7156   0.02908   0.02235   0.0472   0.2731   0.8685
  10.500   0.7048   0.03116   0.02401   0.0503   0.2086   0.8707
  10.750   0.6908   0.03335   0.02574   0.0539   0.1394   0.8728
  11.000   0.6824   0.03545   0.02746   0.0569   0.0935   0.8750
  11.250   0.6833   0.03708   0.02896   0.0588   0.0783   0.8774
  11.500   0.6881   0.03855   0.03039   0.0603   0.0691   0.8800
  11.750   0.6963   0.03985   0.03172   0.0613   0.0636   0.8827
  12.000   0.7029   0.04135   0.03316   0.0623   0.0593   0.8855
  12.250   0.7149   0.04251   0.03437   0.0628   0.0561   0.8881
  12.500   0.7219   0.04379   0.03561   0.0641   0.0530   0.8907
  12.750   0.7336   0.04482   0.03672   0.0650   0.0508   0.8937
  13.000   0.7460   0.04589   0.03780   0.0657   0.0483   0.8969
  13.250   0.7618   0.04680   0.03861   0.0662   0.0463   0.9002
  13.500   0.7808   0.04760   0.03949   0.0664   0.0452   0.9036
  13.750   0.7986   0.04830   0.04026   0.0669   0.0440   0.9070
  14.000   0.8170   0.04901   0.04101   0.0675   0.0424   0.9111
  14.250   0.8414   0.04950   0.04143   0.0675   0.0411   0.9154
  14.500   0.8701   0.05009   0.04204   0.0672   0.0400   0.9197
  14.750   0.8858   0.05111   0.04325   0.0678   0.0392   0.9244
  15.000   0.9034   0.05224   0.04452   0.0681   0.0384   0.9298
  15.250   0.9215   0.05342   0.04582   0.0682   0.0375   0.9354
  15.500   0.9420   0.05462   0.04714   0.0681   0.0370   0.9414
  15.750   0.9627   0.05597   0.04860   0.0678   0.0366   0.9483
  16.000   0.9836   0.05764   0.05041   0.0672   0.0362   0.9554
  16.250   1.0054   0.05971   0.05265   0.0659   0.0359   0.9629
  16.500   1.0324   0.06231   0.05539   0.0640   0.0355   0.9701
  16.750   1.0423   0.06533   0.05868   0.0626   0.0355   0.9811
  17.000   1.0339   0.06836   0.06199   0.0629   0.0358   1.0000
  17.250   1.0265   0.07205   0.06595   0.0628   0.0359   1.0000
  17.500   0.9946   0.07752   0.07186   0.0630   0.0363   1.0000
  17.750   0.9546   0.08466   0.07947   0.0623   0.0369   1.0000
  18.000   0.9195   0.09217   0.08735   0.0606   0.0378   1.0000
  18.250   0.8909   0.09947   0.09492   0.0580   0.0384   1.0000
  18.500   0.8609   0.10746   0.10314   0.0544   0.0389   1.0000
  18.750   0.8347   0.11545   0.11131   0.0504   0.0395   1.0000
  19.000   0.8171   0.12267   0.11865   0.0465   0.0400   1.0000
<< Back to NACA 66(4)-221 (naca664221-il)

Polar data table (+)

Polar graphs


<< Back to NACA 66(4)-221 (naca664221-il)