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NACA 63A210 (naca63a210-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: NACA 63A210 (naca63a210-il)
Reynolds number: 500,000
Max Cl/Cd: 58.29 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca63a210-il-500000-n5.txt
Download as CSV file: xf-naca63a210-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 63A210                                     
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.6337   0.10321   0.09934  -0.0054   0.4645   0.0077
 -10.750  -0.8334   0.04821   0.04408  -0.0427   0.4658   0.0069
 -10.500  -0.8484   0.04417   0.03978  -0.0420   0.4661   0.0070
 -10.250  -0.8449   0.04150   0.03690  -0.0417   0.4661   0.0071
 -10.000  -0.8384   0.03883   0.03398  -0.0412   0.4661   0.0073
  -9.750  -0.8292   0.03618   0.03105  -0.0406   0.4660   0.0075
  -9.500  -0.8174   0.03364   0.02821  -0.0400   0.4659   0.0078
  -9.250  -0.8034   0.03122   0.02544  -0.0393   0.4658   0.0081
  -9.000  -0.7871   0.02902   0.02291  -0.0386   0.4657   0.0084
  -8.750  -0.7685   0.02713   0.02072  -0.0379   0.4656   0.0088
  -8.500  -0.7482   0.02553   0.01885  -0.0373   0.4655   0.0092
  -8.250  -0.7263   0.02426   0.01734  -0.0368   0.4655   0.0096
  -8.000  -0.7026   0.02351   0.01641  -0.0365   0.4654   0.0099
  -7.750  -0.6818   0.02187   0.01457  -0.0359   0.4654   0.0106
  -7.500  -0.6578   0.02120   0.01382  -0.0356   0.4654   0.0112
  -7.250  -0.6334   0.02052   0.01302  -0.0353   0.4653   0.0116
  -7.000  -0.6090   0.01982   0.01222  -0.0350   0.4653   0.0121
  -6.750  -0.5844   0.01913   0.01142  -0.0346   0.4654   0.0126
  -6.500  -0.5597   0.01848   0.01066  -0.0343   0.4654   0.0132
  -6.250  -0.5347   0.01788   0.00996  -0.0339   0.4654   0.0138
  -6.000  -0.5092   0.01741   0.00938  -0.0337   0.4655   0.0143
  -5.750  -0.4843   0.01681   0.00870  -0.0333   0.4655   0.0151
  -5.500  -0.4595   0.01617   0.00800  -0.0330   0.4656   0.0162
  -5.250  -0.4337   0.01576   0.00753  -0.0328   0.4656   0.0171
  -5.000  -0.4075   0.01540   0.00712  -0.0326   0.4657   0.0180
  -4.750  -0.3812   0.01507   0.00672  -0.0324   0.4658   0.0190
  -4.500  -0.3547   0.01477   0.00636  -0.0323   0.4658   0.0203
  -4.250  -0.3279   0.01449   0.00602  -0.0322   0.4654   0.0218
  -4.000  -0.3013   0.01409   0.00559  -0.0320   0.4646   0.0261
  -3.750  -0.2741   0.01381   0.00525  -0.0319   0.4637   0.0306
  -3.500  -0.2472   0.01352   0.00497  -0.0319   0.4631   0.0403
  -3.250  -0.2201   0.01328   0.00475  -0.0318   0.4629   0.0541
  -3.000  -0.1933   0.01298   0.00453  -0.0318   0.4625   0.0786
  -2.750  -0.1669   0.01257   0.00429  -0.0317   0.4620   0.1320
  -2.500  -0.1421   0.01184   0.00400  -0.0316   0.4615   0.2564
  -2.250  -0.1180   0.01107   0.00379  -0.0314   0.4612   0.4122
  -2.000  -0.0916   0.01077   0.00370  -0.0313   0.4612   0.4798
  -1.500  -0.0384   0.01034   0.00358  -0.0309   0.4609   0.5869
  -1.250  -0.0116   0.01017   0.00353  -0.0307   0.4605   0.6303
  -1.000   0.0158   0.01006   0.00348  -0.0305   0.4600   0.6583
  -0.750   0.0434   0.00999   0.00344  -0.0305   0.4598   0.6778
  -0.500   0.0713   0.00993   0.00340  -0.0304   0.4596   0.6923
  -0.250   0.0992   0.00986   0.00334  -0.0304   0.4590   0.7039
   0.000   0.1273   0.00979   0.00327  -0.0305   0.4581   0.7150
   0.250   0.1554   0.00974   0.00323  -0.0305   0.4574   0.7264
   0.500   0.1832   0.00969   0.00321  -0.0305   0.4571   0.7374
   0.750   0.2112   0.00965   0.00321  -0.0305   0.4568   0.7483
   1.250   0.2671   0.00955   0.00318  -0.0305   0.4550   0.7710
   1.500   0.2950   0.00951   0.00317  -0.0306   0.4518   0.7822
   1.750   0.3228   0.00953   0.00322  -0.0306   0.4484   0.7945
   2.000   0.3501   0.00955   0.00333  -0.0305   0.4456   0.8076
   2.250   0.3771   0.00960   0.00348  -0.0303   0.4410   0.8222
   2.500   0.4036   0.00978   0.00373  -0.0301   0.4346   0.8397
   2.750   0.4296   0.00975   0.00386  -0.0296   0.4249   0.8630
   3.000   0.4559   0.00968   0.00394  -0.0291   0.4133   0.8949
   3.250   0.4871   0.00958   0.00402  -0.0296   0.3917   0.9311
   3.500   0.5222   0.00962   0.00370  -0.0312   0.3062   0.9621
   3.750   0.5549   0.01009   0.00366  -0.0328   0.1867   0.9874
   4.000   0.5846   0.01061   0.00386  -0.0338   0.1129   1.0000
   4.250   0.6082   0.01102   0.00409  -0.0332   0.0723   1.0000
   4.500   0.6326   0.01137   0.00434  -0.0327   0.0494   1.0000
   4.750   0.6574   0.01169   0.00461  -0.0323   0.0360   1.0000
   5.000   0.6824   0.01200   0.00490  -0.0319   0.0281   1.0000
   5.250   0.7074   0.01233   0.00523  -0.0315   0.0229   1.0000
   5.500   0.7321   0.01269   0.00561  -0.0310   0.0195   1.0000
   5.750   0.7571   0.01303   0.00599  -0.0306   0.0179   1.0000
   6.000   0.7817   0.01341   0.00640  -0.0301   0.0164   1.0000
   6.250   0.8059   0.01384   0.00686  -0.0296   0.0153   1.0000
   6.500   0.8290   0.01441   0.00750  -0.0288   0.0143   1.0000
   6.750   0.8509   0.01512   0.00829  -0.0279   0.0136   1.0000
   7.000   0.8739   0.01569   0.00894  -0.0272   0.0134   1.0000
   7.250   0.8967   0.01625   0.00957  -0.0265   0.0130   1.0000
   7.500   0.9194   0.01683   0.01023  -0.0258   0.0125   1.0000
   7.750   0.9412   0.01751   0.01098  -0.0250   0.0121   1.0000
   8.000   0.9626   0.01825   0.01183  -0.0241   0.0118   1.0000
   8.250   0.9835   0.01904   0.01271  -0.0232   0.0114   1.0000
   8.500   1.0041   0.01986   0.01363  -0.0222   0.0111   1.0000
   8.750   1.0248   0.02066   0.01450  -0.0214   0.0108   1.0000
   9.000   1.0457   0.02138   0.01529  -0.0206   0.0104   1.0000
   9.250   1.0658   0.02219   0.01617  -0.0197   0.0099   1.0000
   9.500   1.0814   0.02363   0.01773  -0.0183   0.0094   1.0000
   9.750   1.0966   0.02519   0.01949  -0.0168   0.0091   1.0000
  10.000   1.1147   0.02624   0.02070  -0.0157   0.0089   1.0000
  10.250   1.1313   0.02747   0.02210  -0.0144   0.0087   1.0000
  10.500   1.1461   0.02886   0.02368  -0.0130   0.0084   1.0000
  10.750   1.1589   0.03043   0.02545  -0.0114   0.0082   1.0000
  11.000   1.1694   0.03214   0.02737  -0.0097   0.0079   1.0000
  11.250   1.1773   0.03398   0.02942  -0.0078   0.0077   1.0000
  11.500   1.1811   0.03580   0.03144  -0.0054   0.0074   1.0000
  11.750   1.1830   0.03763   0.03345  -0.0031   0.0073   1.0000
  12.000   1.1842   0.03946   0.03544  -0.0012   0.0071   1.0000
  12.250   1.1841   0.04148   0.03761   0.0002   0.0069   1.0000
  12.500   1.1836   0.04370   0.03996   0.0011   0.0068   1.0000
  12.750   1.1829   0.04611   0.04252   0.0015   0.0066   1.0000
  13.000   1.1788   0.04924   0.04579   0.0010   0.0065   1.0000
  13.250   1.1733   0.05299   0.04968  -0.0004   0.0065   1.0000
  13.500   1.1627   0.05813   0.05499  -0.0032   0.0064   1.0000
  13.750   1.1481   0.06423   0.06125  -0.0068   0.0064   1.0000
  14.000   1.1267   0.07139   0.06860  -0.0108   0.0064   1.0000
  14.250   1.0914   0.08211   0.07956  -0.0172   0.0064   1.0000
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