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NACA 65(1)-212 (naca651212-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: NACA 65(1)-212 (naca651212-il)
Reynolds number: 50,000
Max Cl/Cd: 26.21 at α=6°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-naca651212-il-50000.txt
Download as CSV file: xf-naca651212-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 65(1)-212                                  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.4521   0.11019   0.10301  -0.0106   1.0000   0.3653
  -9.500  -0.4512   0.10748   0.10035  -0.0102   1.0000   0.3809
  -9.250  -0.4499   0.10473   0.09766  -0.0097   1.0000   0.3962
  -9.000  -0.4219   0.09947   0.09234  -0.0100   1.0000   0.4051
  -8.750  -0.4179   0.09624   0.08916  -0.0099   1.0000   0.4160
  -8.500  -0.4280   0.07328   0.06699  -0.0340   1.0000   0.2369
  -8.250  -0.4872   0.06396   0.05787  -0.0404   1.0000   0.2073
  -8.000  -0.5279   0.05897   0.05298  -0.0399   1.0000   0.1946
  -7.750  -0.6286   0.06463   0.05804  -0.0380   1.0000   0.1836
  -7.500  -0.6480   0.06004   0.05317  -0.0364   1.0000   0.1651
  -7.250  -0.6578   0.05630   0.04908  -0.0339   1.0000   0.1535
  -7.000  -0.6662   0.05296   0.04515  -0.0310   1.0000   0.1430
  -6.750  -0.6609   0.04968   0.04168  -0.0288   1.0000   0.1396
  -6.500  -0.6575   0.04643   0.03790  -0.0264   1.0000   0.1336
  -6.250  -0.6480   0.04388   0.03474  -0.0240   1.0000   0.1286
  -6.000  -0.6345   0.04107   0.03165  -0.0223   1.0000   0.1261
  -5.750  -0.6190   0.03855   0.02876  -0.0206   1.0000   0.1241
  -5.500  -0.6015   0.03631   0.02615  -0.0189   1.0000   0.1238
  -5.250  -0.5832   0.03451   0.02396  -0.0174   1.0000   0.1263
  -5.000  -0.5633   0.03292   0.02196  -0.0159   1.0000   0.1294
  -4.750  -0.5411   0.03116   0.02003  -0.0147   1.0000   0.1317
  -4.500  -0.5179   0.02966   0.01856  -0.0134   1.0000   0.1362
  -4.250  -0.4959   0.02869   0.01741  -0.0118   1.0000   0.1446
  -4.000  -0.4758   0.02756   0.01640  -0.0101   1.0000   0.1565
  -3.750  -0.4581   0.02648   0.01541  -0.0081   1.0000   0.1697
  -3.500  -0.1554   0.03011   0.02107  -0.0228   1.0000   0.9709
  -3.250  -0.0937   0.02879   0.01937  -0.0314   1.0000   0.9895
  -3.000  -0.0577   0.02805   0.01840  -0.0356   1.0000   1.0000
  -2.750  -0.0614   0.02806   0.01837  -0.0324   1.0000   1.0000
  -2.500  -0.0647   0.02807   0.01830  -0.0293   1.0000   1.0000
  -2.250  -0.0676   0.02805   0.01823  -0.0263   1.0000   1.0000
  -2.000  -0.0700   0.02801   0.01814  -0.0233   1.0000   1.0000
  -1.750  -0.0721   0.02796   0.01803  -0.0204   1.0000   1.0000
  -1.500  -0.0740   0.02788   0.01790  -0.0175   1.0000   1.0000
  -1.250  -0.0758   0.02779   0.01775  -0.0146   1.0000   1.0000
  -1.000  -0.0776   0.02767   0.01758  -0.0117   1.0000   1.0000
  -0.750  -0.0795   0.02752   0.01740  -0.0088   1.0000   1.0000
  -0.500  -0.0816   0.02735   0.01716  -0.0058   1.0000   1.0000
  -0.250  -0.0840   0.02714   0.01691  -0.0028   1.0000   1.0000
   0.000  -0.0868   0.02689   0.01662   0.0003   1.0000   1.0000
   0.250  -0.0899   0.02661   0.01629   0.0035   1.0000   1.0000
   0.500  -0.0929   0.02629   0.01593   0.0067   1.0000   1.0000
   0.750  -0.0945   0.02599   0.01558   0.0097   1.0000   1.0000
   1.000  -0.0923   0.02579   0.01532   0.0122   1.0000   1.0000
   1.250  -0.0832   0.02580   0.01525   0.0135   1.0000   1.0000
   1.500  -0.0693   0.02600   0.01537   0.0139   1.0000   1.0000
   1.750  -0.0525   0.02634   0.01564   0.0140   1.0000   1.0000
   2.000  -0.0344   0.02677   0.01602   0.0138   1.0000   1.0000
   2.250  -0.0155   0.02728   0.01648   0.0135   1.0000   1.0000
   2.500   0.0037   0.02787   0.01703   0.0131   1.0000   1.0000
   2.750   0.0230   0.02850   0.01765   0.0128   1.0000   1.0000
   3.000   0.0422   0.02920   0.01833   0.0124   1.0000   1.0000
   3.250   0.0835   0.03076   0.01996   0.0077   0.9888   1.0000
   3.500   0.1224   0.03228   0.02153   0.0035   0.9772   1.0000
   3.750   0.1599   0.03376   0.02310  -0.0003   0.9646   1.0000
   4.000   0.1965   0.03523   0.02469  -0.0038   0.9511   1.0000
   4.250   0.2321   0.03666   0.02624  -0.0070   0.9364   1.0000
   4.500   0.2676   0.03807   0.02781  -0.0101   0.9197   1.0000
   4.750   0.3061   0.03954   0.02949  -0.0135   0.9014   1.0000
   5.000   0.3460   0.04098   0.03114  -0.0167   0.8804   1.0000
   5.250   0.3801   0.04215   0.03255  -0.0188   0.8581   1.0000
   5.500   0.4208   0.04331   0.03402  -0.0214   0.8328   1.0000
   5.750   0.4663   0.04410   0.03517  -0.0239   0.8028   1.0000
   6.000   0.6637   0.02532   0.01521  -0.0089   0.2374   1.0000
   6.250   0.6642   0.02773   0.01694  -0.0053   0.1880   1.0000
   6.500   0.6826   0.02961   0.01850  -0.0036   0.1592   1.0000
   6.750   0.7306   0.03159   0.02040  -0.0051   0.1389   1.0000
   7.000   0.7797   0.03393   0.02270  -0.0072   0.1250   1.0000
   7.250   0.8258   0.03716   0.02589  -0.0093   0.1194   1.0000
   7.500   0.8528   0.03959   0.02881  -0.0086   0.1168   1.0000
   7.750   0.8755   0.04220   0.03184  -0.0077   0.1135   1.0000
   8.000   0.8959   0.04519   0.03524  -0.0066   0.1121   1.0000
   8.250   0.9127   0.04864   0.03916  -0.0052   0.1135   1.0000
   8.500   0.9258   0.05236   0.04331  -0.0037   0.1157   1.0000
   8.750   0.9388   0.05656   0.04785  -0.0025   0.1182   1.0000
   9.000   0.9392   0.06011   0.05201  -0.0001   0.1225   1.0000
   9.250   0.9269   0.06456   0.05702   0.0025   0.1279   1.0000
   9.500   0.9282   0.06933   0.06199   0.0036   0.1317   1.0000
   9.750   0.8982   0.07363   0.06674   0.0058   0.1386   1.0000
  10.000   0.8737   0.07855   0.07183   0.0070   0.1442   1.0000
  10.250   0.8401   0.08397   0.07735   0.0065   0.1513   1.0000
  10.500   0.7895   0.09194   0.08534   0.0019   0.1569   1.0000
  10.750   0.7639   0.10516   0.09856  -0.0069   0.1904   1.0000
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