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

NACA 63(4)-221 (naca634221-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: NACA 63(4)-221 (naca634221-il)
Reynolds number: 1,000,000
Max Cl/Cd: 108 at α=7.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-naca634221-il-1000000.txt
Download as CSV file: xf-naca634221-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 63(4)-221                                  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -19.750  -1.1373   0.08608   0.08184  -0.0391   1.0000   0.0281
 -19.500  -1.1369   0.08295   0.07865  -0.0402   1.0000   0.0285
 -19.250  -1.1332   0.08028   0.07593  -0.0411   1.0000   0.0291
 -19.000  -1.1298   0.07759   0.07318  -0.0420   1.0000   0.0297
 -18.750  -1.1251   0.07513   0.07066  -0.0428   1.0000   0.0300
 -18.500  -1.1251   0.07208   0.06756  -0.0437   1.0000   0.0305
 -18.250  -1.1268   0.06893   0.06437  -0.0446   1.0000   0.0310
 -18.000  -1.1266   0.06602   0.06143  -0.0453   1.0000   0.0317
 -17.750  -1.1223   0.06364   0.05901  -0.0459   1.0000   0.0322
 -17.500  -1.1183   0.06120   0.05652  -0.0465   1.0000   0.0328
 -17.250  -1.1118   0.05908   0.05436  -0.0470   1.0000   0.0334
 -17.000  -1.1058   0.05692   0.05215  -0.0474   1.0000   0.0339
 -16.750  -1.0970   0.05508   0.05026  -0.0478   1.0000   0.0344
 -16.500  -1.0942   0.05264   0.04778  -0.0482   1.0000   0.0348
 -16.250  -1.0930   0.05007   0.04517  -0.0485   1.0000   0.0356
 -16.000  -1.0889   0.04783   0.04291  -0.0489   1.0000   0.0363
 -15.750  -1.0826   0.04586   0.04091  -0.0491   1.0000   0.0368
 -15.500  -1.0748   0.04402   0.03904  -0.0492   1.0000   0.0375
 -15.250  -1.0662   0.04230   0.03728  -0.0494   1.0000   0.0382
 -15.000  -1.0570   0.04065   0.03559  -0.0495   1.0000   0.0387
 -14.750  -1.0470   0.03910   0.03400  -0.0495   1.0000   0.0392
 -14.500  -1.0435   0.03700   0.03188  -0.0495   1.0000   0.0400
 -14.250  -1.0100   0.03477   0.02961  -0.0552   0.9506   0.0415
 -14.000  -0.9718   0.03296   0.02762  -0.0612   0.9038   0.0428
 -13.750  -0.9633   0.03181   0.02630  -0.0603   0.8711   0.0437
 -13.500  -0.9544   0.03066   0.02503  -0.0595   0.8523   0.0444
 -13.250  -0.9510   0.02912   0.02342  -0.0585   0.8377   0.0459
 -13.000  -0.9446   0.02781   0.02204  -0.0576   0.8256   0.0469
 -12.750  -0.9363   0.02663   0.02080  -0.0567   0.8144   0.0483
 -12.500  -0.9267   0.02555   0.01964  -0.0558   0.8047   0.0498
 -12.250  -0.9200   0.02429   0.01835  -0.0548   0.7952   0.0519
 -12.000  -0.9122   0.02315   0.01717  -0.0537   0.7868   0.0543
 -11.750  -0.9029   0.02209   0.01608  -0.0526   0.7786   0.0573
 -11.500  -0.8964   0.02094   0.01489  -0.0513   0.7703   0.0608
 -11.250  -0.8875   0.01990   0.01384  -0.0501   0.7633   0.0650
 -11.000  -0.8796   0.01888   0.01280  -0.0487   0.7559   0.0699
 -10.750  -0.8728   0.01786   0.01177  -0.0471   0.7488   0.0762
 -10.500  -0.8654   0.01686   0.01080  -0.0454   0.7425   0.0838
 -10.250  -0.8564   0.01602   0.00995  -0.0438   0.7355   0.0907
 -10.000  -0.8501   0.01515   0.00908  -0.0417   0.7286   0.1003
  -9.750  -0.8440   0.01432   0.00829  -0.0394   0.7228   0.1099
  -9.500  -0.8415   0.01361   0.00759  -0.0362   0.7165   0.1195
  -9.250  -0.8344   0.01313   0.00711  -0.0335   0.7100   0.1303
  -9.000  -0.8189   0.01263   0.00666  -0.0320   0.7051   0.1429
  -8.750  -0.8015   0.01216   0.00624  -0.0308   0.6993   0.1569
  -8.500  -0.7831   0.01169   0.00582  -0.0298   0.6936   0.1737
  -8.250  -0.7637   0.01120   0.00541  -0.0289   0.6885   0.1948
  -8.000  -0.7438   0.01065   0.00498  -0.0281   0.6837   0.2215
  -7.750  -0.7221   0.01017   0.00461  -0.0275   0.6783   0.2489
  -7.500  -0.6995   0.00972   0.00425  -0.0271   0.6727   0.2770
  -7.250  -0.6756   0.00929   0.00393  -0.0269   0.6681   0.3041
  -7.000  -0.6503   0.00893   0.00367  -0.0268   0.6636   0.3315
  -6.750  -0.6243   0.00861   0.00344  -0.0268   0.6587   0.3565
  -6.500  -0.5972   0.00842   0.00327  -0.0269   0.6534   0.3769
  -6.250  -0.5690   0.00826   0.00314  -0.0271   0.6488   0.3922
  -6.000  -0.5400   0.00815   0.00303  -0.0274   0.6442   0.4035
  -5.750  -0.5113   0.00804   0.00293  -0.0277   0.6394   0.4153
  -5.500  -0.4826   0.00796   0.00284  -0.0280   0.6346   0.4267
  -5.250  -0.4530   0.00793   0.00278  -0.0284   0.6303   0.4364
  -5.000  -0.4238   0.00782   0.00270  -0.0287   0.6263   0.4449
  -4.750  -0.3941   0.00778   0.00264  -0.0291   0.6217   0.4517
  -4.500  -0.3646   0.00776   0.00257  -0.0295   0.6169   0.4574
  -4.250  -0.3353   0.00771   0.00251  -0.0299   0.6120   0.4632
  -4.000  -0.3053   0.00767   0.00246  -0.0303   0.6082   0.4681
  -3.750  -0.2752   0.00767   0.00241  -0.0308   0.6039   0.4723
  -3.500  -0.2458   0.00761   0.00236  -0.0311   0.5995   0.4781
  -3.250  -0.2163   0.00761   0.00233  -0.0315   0.5947   0.4841
  -3.000  -0.1860   0.00761   0.00231  -0.0320   0.5913   0.4891
  -2.750  -0.1560   0.00757   0.00227  -0.0325   0.5874   0.4931
  -2.500  -0.1263   0.00753   0.00223  -0.0329   0.5832   0.4976
  -2.250  -0.0966   0.00753   0.00220  -0.0333   0.5786   0.5015
  -2.000  -0.0667   0.00754   0.00218  -0.0337   0.5742   0.5053
  -1.750  -0.0364   0.00754   0.00217  -0.0342   0.5708   0.5086
  -1.500  -0.0064   0.00750   0.00214  -0.0346   0.5669   0.5128
  -1.250   0.0233   0.00749   0.00212  -0.0351   0.5629   0.5172
  -1.000   0.0529   0.00752   0.00213  -0.0355   0.5586   0.5214
  -0.750   0.0830   0.00754   0.00213  -0.0359   0.5550   0.5252
  -0.500   0.1134   0.00755   0.00213  -0.0364   0.5516   0.5282
  -0.250   0.1431   0.00751   0.00212  -0.0368   0.5476   0.5331
   0.000   0.1728   0.00752   0.00213  -0.0373   0.5436   0.5372
   0.250   0.2024   0.00757   0.00216  -0.0376   0.5393   0.5412
   0.500   0.2325   0.00759   0.00218  -0.0381   0.5361   0.5446
   0.750   0.2627   0.00760   0.00219  -0.0386   0.5326   0.5476
   1.000   0.2924   0.00758   0.00221  -0.0390   0.5287   0.5525
   1.250   0.3220   0.00761   0.00224  -0.0394   0.5246   0.5567
   1.500   0.3513   0.00770   0.00229  -0.0398   0.5198   0.5607
   1.750   0.3815   0.00771   0.00232  -0.0403   0.5168   0.5642
   2.000   0.4115   0.00772   0.00235  -0.0407   0.5132   0.5679
   2.250   0.4410   0.00773   0.00239  -0.0411   0.5093   0.5724
   2.500   0.4703   0.00779   0.00244  -0.0414   0.5051   0.5766
   2.750   0.4996   0.00787   0.00251  -0.0418   0.5010   0.5808
   3.000   0.5296   0.00790   0.00256  -0.0423   0.4979   0.5844
   3.250   0.5592   0.00790   0.00262  -0.0427   0.4943   0.5893
   3.500   0.5884   0.00795   0.00268  -0.0430   0.4904   0.5939
   3.750   0.6173   0.00804   0.00277  -0.0433   0.4860   0.5982
   4.000   0.6466   0.00810   0.00284  -0.0437   0.4816   0.6022
   4.250   0.6762   0.00813   0.00289  -0.0440   0.4764   0.6061
   4.500   0.7048   0.00818   0.00297  -0.0443   0.4705   0.6110
   4.750   0.7331   0.00829   0.00308  -0.0445   0.4652   0.6156
   5.000   0.7626   0.00832   0.00316  -0.0449   0.4613   0.6202
   5.250   0.7916   0.00841   0.00325  -0.0452   0.4561   0.6240
   5.500   0.8194   0.00849   0.00335  -0.0453   0.4504   0.6297
   5.750   0.8480   0.00856   0.00347  -0.0456   0.4450   0.6346
   6.000   0.8765   0.00864   0.00357  -0.0458   0.4382   0.6393
   6.250   0.9035   0.00881   0.00370  -0.0458   0.4301   0.6432
   6.500   0.9317   0.00887   0.00381  -0.0460   0.4217   0.6484
   6.750   0.9580   0.00903   0.00397  -0.0459   0.4112   0.6535
   7.000   0.9843   0.00921   0.00412  -0.0458   0.3983   0.6587
   7.250   1.0107   0.00939   0.00429  -0.0457   0.3865   0.6632
   7.500   1.0357   0.00959   0.00449  -0.0454   0.3735   0.6689
   7.750   1.0594   0.00986   0.00473  -0.0450   0.3573   0.6742
   8.000   1.0813   0.01021   0.00501  -0.0442   0.3373   0.6794
   8.250   1.1005   0.01066   0.00536  -0.0431   0.3152   0.6840
   8.500   1.1167   0.01116   0.00579  -0.0415   0.2920   0.6903
   8.750   1.1311   0.01170   0.00625  -0.0396   0.2689   0.6961
   9.000   1.1384   0.01233   0.00676  -0.0365   0.2457   0.7015
   9.250   1.1424   0.01292   0.00729  -0.0329   0.2284   0.7072
   9.500   1.1437   0.01372   0.00804  -0.0293   0.2079   0.7136
   9.750   1.1462   0.01463   0.00888  -0.0262   0.1901   0.7201
  10.000   1.1498   0.01560   0.00980  -0.0235   0.1749   0.7264
  10.250   1.1551   0.01657   0.01076  -0.0212   0.1630   0.7333
  10.500   1.1592   0.01770   0.01185  -0.0189   0.1505   0.7401
  10.750   1.1655   0.01878   0.01292  -0.0171   0.1401   0.7467
  11.000   1.1720   0.01990   0.01405  -0.0154   0.1305   0.7542
  11.250   1.1767   0.02119   0.01532  -0.0137   0.1206   0.7616
  11.500   1.1805   0.02258   0.01670  -0.0120   0.1114   0.7693
  11.750   1.1840   0.02404   0.01815  -0.0104   0.1018   0.7774
  12.000   1.1896   0.02544   0.01956  -0.0091   0.0945   0.7853
  12.250   1.1926   0.02702   0.02116  -0.0077   0.0864   0.7945
  12.500   1.1956   0.02868   0.02281  -0.0065   0.0794   0.8040
  12.750   1.1985   0.03037   0.02452  -0.0053   0.0728   0.8144
  13.000   1.2022   0.03207   0.02626  -0.0043   0.0670   0.8255
  13.250   1.2061   0.03381   0.02804  -0.0034   0.0621   0.8383
  13.500   1.2090   0.03564   0.02991  -0.0025   0.0576   0.8539
  13.750   1.2125   0.03738   0.03175  -0.0015   0.0538   0.8758
  14.000   1.2144   0.03912   0.03367  -0.0003   0.0507   0.9344
  14.250   1.2285   0.04113   0.03574  -0.0020   0.0474   1.0000
  14.500   1.2333   0.04321   0.03783  -0.0018   0.0452   1.0000
  14.750   1.2400   0.04517   0.03982  -0.0017   0.0433   1.0000
  15.000   1.2469   0.04715   0.04182  -0.0017   0.0418   1.0000
  15.250   1.2513   0.04941   0.04410  -0.0018   0.0404   1.0000
  15.500   1.2560   0.05167   0.04638  -0.0018   0.0390   1.0000
  15.750   1.2633   0.05372   0.04848  -0.0020   0.0382   1.0000
  16.000   1.2695   0.05590   0.05069  -0.0022   0.0371   1.0000
  16.250   1.2741   0.05831   0.05313  -0.0026   0.0362   1.0000
  16.500   1.2776   0.06086   0.05571  -0.0029   0.0353   1.0000
  16.750   1.2793   0.06366   0.05855  -0.0034   0.0345   1.0000
  17.000   1.2868   0.06585   0.06079  -0.0038   0.0340   1.0000
  17.250   1.2921   0.06834   0.06334  -0.0044   0.0334   1.0000
  17.500   1.2976   0.07081   0.06585  -0.0050   0.0327   1.0000
  17.750   1.3002   0.07369   0.06878  -0.0057   0.0321   1.0000
  18.000   1.3032   0.07652   0.07165  -0.0065   0.0314   1.0000
  18.250   1.3024   0.07994   0.07511  -0.0075   0.0307   1.0000
  18.500   1.3047   0.08297   0.07820  -0.0084   0.0301   1.0000
  18.750   1.3084   0.08588   0.08117  -0.0094   0.0297   1.0000
  19.000   1.3130   0.08866   0.08401  -0.0103   0.0291   1.0000
  19.250   1.3158   0.09175   0.08716  -0.0115   0.0286   1.0000
<< Back to NACA 63(4)-221 (naca634221-il)

Polar data table (+)

Polar graphs


<< Back to NACA 63(4)-221 (naca634221-il)