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=500,000 Ncrit=9


Details Polar file
Airfoil: NACA 63(4)-221 (naca634221-il)
Reynolds number: 500,000
Max Cl/Cd: 87.99 at α=8.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-naca634221-il-500000.txt
Download as CSV file: xf-naca634221-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -19.250  -1.0542   0.08897   0.08405  -0.0408   1.0000   0.0364
 -19.000  -1.0502   0.08621   0.08124  -0.0419   1.0000   0.0371
 -18.750  -1.0472   0.08331   0.07827  -0.0431   1.0000   0.0379
 -18.500  -1.0433   0.08048   0.07535  -0.0442   1.0000   0.0386
 -18.250  -1.0396   0.07767   0.07244  -0.0453   1.0000   0.0392
 -18.000  -1.0345   0.07547   0.07028  -0.0457   1.0000   0.0402
 -17.750  -1.0295   0.07304   0.06783  -0.0465   1.0000   0.0409
 -17.500  -1.0243   0.07061   0.06536  -0.0473   1.0000   0.0417
 -17.250  -1.0187   0.06824   0.06295  -0.0480   1.0000   0.0426
 -17.000  -1.0120   0.06602   0.06067  -0.0486   1.0000   0.0434
 -16.750  -1.0055   0.06379   0.05837  -0.0492   1.0000   0.0441
 -16.500  -0.9997   0.06167   0.05621  -0.0496   1.0000   0.0449
 -16.250  -0.9954   0.05939   0.05394  -0.0500   1.0000   0.0458
 -16.000  -0.9899   0.05718   0.05171  -0.0504   1.0000   0.0466
 -15.750  -0.9827   0.05518   0.04968  -0.0508   1.0000   0.0476
 -15.500  -0.9758   0.05317   0.04763  -0.0511   1.0000   0.0485
 -15.250  -0.9676   0.05132   0.04572  -0.0514   1.0000   0.0494
 -15.000  -0.9595   0.04947   0.04383  -0.0516   1.0000   0.0503
 -14.750  -0.9573   0.04717   0.04153  -0.0517   1.0000   0.0514
 -14.500  -0.9518   0.04517   0.03953  -0.0519   1.0000   0.0527
 -14.250  -0.9442   0.04336   0.03770  -0.0520   1.0000   0.0540
 -14.000  -0.9361   0.04165   0.03595  -0.0520   1.0000   0.0553
 -13.750  -0.9274   0.04000   0.03426  -0.0520   1.0000   0.0567
 -13.500  -0.9247   0.03788   0.03217  -0.0520   1.0000   0.0585
 -13.250  -0.9185   0.03609   0.03039  -0.0517   0.9892   0.0603
 -13.000  -0.8771   0.03411   0.02830  -0.0587   0.9379   0.0637
 -12.750  -0.8594   0.03208   0.02616  -0.0614   0.9015   0.0673
 -12.500  -0.8518   0.03083   0.02478  -0.0606   0.8780   0.0708
 -12.250  -0.8510   0.02919   0.02309  -0.0594   0.8613   0.0743
 -11.750  -0.8442   0.02631   0.02010  -0.0569   0.8358   0.0840
 -11.500  -0.8398   0.02498   0.01872  -0.0556   0.8255   0.0905
 -11.250  -0.8368   0.02357   0.01731  -0.0542   0.8155   0.0986
 -11.000  -0.8340   0.02221   0.01595  -0.0526   0.8068   0.1077
 -10.750  -0.8301   0.02093   0.01469  -0.0511   0.7978   0.1181
 -10.500  -0.8260   0.01976   0.01350  -0.0493   0.7898   0.1295
 -10.250  -0.8209   0.01862   0.01240  -0.0476   0.7820   0.1414
 -10.000  -0.8158   0.01758   0.01136  -0.0457   0.7744   0.1539
  -9.750  -0.8114   0.01659   0.01037  -0.0436   0.7676   0.1673
  -9.500  -0.8087   0.01560   0.00943  -0.0411   0.7604   0.1822
  -9.000  -0.8059   0.01408   0.00799  -0.0346   0.7471   0.2179
  -8.750  -0.7945   0.01340   0.00742  -0.0327   0.7408   0.2434
  -8.500  -0.7804   0.01276   0.00687  -0.0311   0.7350   0.2701
  -8.250  -0.7631   0.01224   0.00640  -0.0299   0.7295   0.2983
  -8.000  -0.7440   0.01169   0.00599  -0.0291   0.7239   0.3269
  -7.750  -0.7221   0.01128   0.00568  -0.0285   0.7182   0.3539
  -7.500  -0.6980   0.01102   0.00543  -0.0282   0.7129   0.3769
  -7.250  -0.6721   0.01085   0.00526  -0.0280   0.7079   0.3943
  -7.000  -0.6452   0.01069   0.00511  -0.0281   0.7026   0.4077
  -6.750  -0.6175   0.01060   0.00495  -0.0282   0.6972   0.4193
  -6.500  -0.5904   0.01050   0.00483  -0.0282   0.6921   0.4303
  -6.250  -0.5625   0.01043   0.00474  -0.0283   0.6872   0.4419
  -6.000  -0.5341   0.01040   0.00467  -0.0285   0.6822   0.4534
  -5.750  -0.5059   0.01032   0.00459  -0.0287   0.6773   0.4615
  -5.500  -0.4773   0.01033   0.00451  -0.0289   0.6725   0.4691
  -5.250  -0.4485   0.01029   0.00443  -0.0291   0.6677   0.4758
  -5.000  -0.4196   0.01023   0.00439  -0.0294   0.6627   0.4819
  -4.750  -0.3905   0.01021   0.00430  -0.0297   0.6578   0.4875
  -4.500  -0.3614   0.01020   0.00419  -0.0300   0.6534   0.4925
  -4.250  -0.3324   0.01015   0.00416  -0.0302   0.6490   0.4978
  -4.000  -0.3030   0.01015   0.00415  -0.0306   0.6444   0.5040
  -3.500  -0.2446   0.01010   0.00403  -0.0312   0.6353   0.5148
  -3.250  -0.2153   0.01011   0.00400  -0.0315   0.6308   0.5189
  -3.000  -0.1857   0.01008   0.00396  -0.0319   0.6263   0.5231
  -2.750  -0.1560   0.01007   0.00390  -0.0323   0.6219   0.5270
  -2.500  -0.1267   0.01001   0.00381  -0.0326   0.6177   0.5310
  -2.250  -0.0974   0.01003   0.00380  -0.0329   0.6135   0.5349
  -2.000  -0.0677   0.01001   0.00380  -0.0333   0.6096   0.5390
  -1.750  -0.0381   0.01000   0.00377  -0.0337   0.6053   0.5432
  -1.500  -0.0083   0.01002   0.00373  -0.0342   0.6010   0.5469
  -1.250   0.0209   0.00996   0.00368  -0.0345   0.5968   0.5512
  -1.000   0.0503   0.01000   0.00371  -0.0348   0.5928   0.5551
  -0.750   0.0800   0.00999   0.00372  -0.0352   0.5889   0.5590
  -0.500   0.1097   0.01000   0.00371  -0.0356   0.5849   0.5632
  -0.250   0.1394   0.01001   0.00368  -0.0361   0.5811   0.5669
   0.000   0.1687   0.01000   0.00368  -0.0364   0.5773   0.5707
   0.250   0.1981   0.01004   0.00373  -0.0368   0.5734   0.5745
   0.500   0.2277   0.01005   0.00376  -0.0371   0.5694   0.5787
   0.750   0.2574   0.01008   0.00378  -0.0376   0.5656   0.5829
   1.000   0.2869   0.01009   0.00378  -0.0380   0.5619   0.5868
   1.250   0.3161   0.01013   0.00381  -0.0383   0.5580   0.5907
   1.500   0.3454   0.01017   0.00389  -0.0386   0.5544   0.5947
   1.750   0.3749   0.01019   0.00395  -0.0390   0.5505   0.5989
   2.000   0.4044   0.01023   0.00398  -0.0394   0.5464   0.6031
   2.250   0.4335   0.01025   0.00400  -0.0397   0.5426   0.6075
   2.500   0.4627   0.01035   0.00410  -0.0400   0.5385   0.6118
   2.750   0.4918   0.01038   0.00419  -0.0403   0.5350   0.6162
   3.000   0.5210   0.01042   0.00426  -0.0407   0.5310   0.6207
   3.250   0.5502   0.01047   0.00431  -0.0410   0.5271   0.6249
   3.500   0.5790   0.01050   0.00437  -0.0413   0.5232   0.6293
   3.750   0.6080   0.01063   0.00450  -0.0416   0.5193   0.6337
   4.000   0.6367   0.01067   0.00461  -0.0419   0.5156   0.6386
   4.250   0.6656   0.01074   0.00470  -0.0422   0.5115   0.6432
   4.500   0.6940   0.01076   0.00478  -0.0424   0.5074   0.6481
   4.750   0.7225   0.01089   0.00488  -0.0426   0.5024   0.6529
   5.000   0.7503   0.01091   0.00499  -0.0426   0.4967   0.6578
   5.250   0.7784   0.01095   0.00505  -0.0428   0.4908   0.6626
   5.500   0.8062   0.01103   0.00514  -0.0429   0.4859   0.6673
   5.750   0.8338   0.01112   0.00530  -0.0430   0.4810   0.6722
   6.000   0.8613   0.01118   0.00543  -0.0430   0.4754   0.6776
   6.250   0.8888   0.01128   0.00553  -0.0431   0.4696   0.6829
   6.500   0.9154   0.01138   0.00567  -0.0430   0.4636   0.6880
   6.750   0.9419   0.01143   0.00583  -0.0429   0.4568   0.6931
   7.000   0.9677   0.01158   0.00594  -0.0426   0.4492   0.6986
   7.250   0.9935   0.01167   0.00610  -0.0424   0.4399   0.7039
   7.500   1.0168   0.01181   0.00625  -0.0418   0.4291   0.7094
   7.750   1.0409   0.01194   0.00644  -0.0413   0.4179   0.7152
   8.000   1.0645   0.01214   0.00665  -0.0408   0.4078   0.7210
   8.250   1.0858   0.01237   0.00688  -0.0399   0.3961   0.7264
   8.500   1.1069   0.01258   0.00715  -0.0390   0.3826   0.7322
   8.750   1.1255   0.01290   0.00746  -0.0377   0.3671   0.7387
   9.000   1.1403   0.01329   0.00782  -0.0359   0.3495   0.7448
   9.250   1.1467   0.01374   0.00825  -0.0326   0.3314   0.7510
   9.500   1.1490   0.01442   0.00887  -0.0289   0.3130   0.7580
   9.750   1.1503   0.01528   0.00968  -0.0255   0.2947   0.7652
  10.000   1.1513   0.01625   0.01063  -0.0224   0.2760   0.7726
  10.250   1.1521   0.01741   0.01172  -0.0196   0.2568   0.7807
  10.500   1.1518   0.01867   0.01296  -0.0169   0.2382   0.7884
  10.750   1.1512   0.02010   0.01434  -0.0144   0.2203   0.7970
  11.000   1.1501   0.02163   0.01584  -0.0121   0.2035   0.8056
  11.250   1.1488   0.02326   0.01745  -0.0100   0.1879   0.8154
  11.500   1.1480   0.02494   0.01912  -0.0081   0.1741   0.8252
  11.750   1.1477   0.02666   0.02084  -0.0064   0.1623   0.8365
  12.250   1.1481   0.03010   0.02434  -0.0032   0.1411   0.8628
  12.500   1.1483   0.03182   0.02612  -0.0017   0.1316   0.8814
  12.750   1.1460   0.03367   0.02805   0.0000   0.1215   0.9148
  13.000   1.1551   0.03589   0.03030  -0.0013   0.1100   1.0000
  13.250   1.1568   0.03819   0.03255  -0.0010   0.1007   1.0000
  13.500   1.1597   0.04043   0.03475  -0.0008   0.0918   1.0000
  13.750   1.1626   0.04270   0.03700  -0.0006   0.0843   1.0000
  14.000   1.1639   0.04518   0.03945  -0.0005   0.0776   1.0000
  14.250   1.1646   0.04776   0.04201  -0.0005   0.0720   1.0000
  14.500   1.1691   0.05005   0.04431  -0.0006   0.0675   1.0000
  14.750   1.1686   0.05287   0.04712  -0.0007   0.0637   1.0000
  15.000   1.1746   0.05509   0.04937  -0.0009   0.0605   1.0000
  15.250   1.1756   0.05789   0.05217  -0.0012   0.0578   1.0000
  15.500   1.1792   0.06043   0.05475  -0.0015   0.0553   1.0000
  15.750   1.1835   0.06297   0.05733  -0.0020   0.0532   1.0000
  16.000   1.1851   0.06583   0.06019  -0.0025   0.0514   1.0000
  16.250   1.1862   0.06883   0.06323  -0.0031   0.0499   1.0000
  16.500   1.1920   0.07131   0.06577  -0.0037   0.0486   1.0000
  16.750   1.1957   0.07408   0.06859  -0.0044   0.0473   1.0000
  17.000   1.1985   0.07698   0.07152  -0.0051   0.0461   1.0000
  17.250   1.1978   0.08038   0.07493  -0.0061   0.0449   1.0000
  17.500   1.2018   0.08322   0.07784  -0.0069   0.0440   1.0000
  17.750   1.2065   0.08601   0.08069  -0.0078   0.0429   1.0000
  18.000   1.2104   0.08893   0.08367  -0.0088   0.0419   1.0000
  18.250   1.2135   0.09199   0.08677  -0.0099   0.0409   1.0000
  18.500   1.2140   0.09543   0.09023  -0.0112   0.0400   1.0000
<< Back to NACA 63(4)-221 (naca634221-il)

Polar data table (+)

Polar graphs


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