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NACA 64(1)-212 (n64212-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: NACA 64(1)-212 (n64212-il)
Reynolds number: 200,000
Max Cl/Cd: 55.94 at α=4.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-n64212-il-200000-n5.txt
Download as CSV file: xf-n64212-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 64(1)-212                                  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.000  -0.6501   0.08345   0.07971  -0.0321   1.0000   0.0188
 -11.750  -0.6806   0.07231   0.06846  -0.0404   1.0000   0.0185
 -11.500  -0.7086   0.06429   0.06029  -0.0461   1.0000   0.0184
 -11.250  -0.7312   0.05848   0.05431  -0.0494   1.0000   0.0183
 -11.000  -0.7527   0.05359   0.04924  -0.0511   1.0000   0.0183
 -10.750  -0.7726   0.04951   0.04495  -0.0511   1.0000   0.0183
 -10.500  -0.7923   0.04597   0.04114  -0.0493   1.0000   0.0184
 -10.250  -0.8037   0.04250   0.03735  -0.0473   1.0000   0.0186
 -10.000  -0.8086   0.03901   0.03343  -0.0454   1.0000   0.0188
  -9.750  -0.8063   0.03609   0.03008  -0.0437   1.0000   0.0191
  -9.500  -0.7972   0.03380   0.02760  -0.0424   1.0000   0.0196
  -9.250  -0.7830   0.03252   0.02625  -0.0415   1.0000   0.0202
  -9.000  -0.7682   0.03137   0.02499  -0.0404   1.0000   0.0208
  -8.750  -0.7537   0.03000   0.02346  -0.0390   1.0000   0.0215
  -8.500  -0.7400   0.02841   0.02166  -0.0374   1.0000   0.0221
  -8.250  -0.7267   0.02692   0.01995  -0.0355   1.0000   0.0226
  -8.000  -0.6993   0.02522   0.01799  -0.0364   0.9926   0.0233
  -7.750  -0.6671   0.02369   0.01621  -0.0379   0.9851   0.0241
  -7.500  -0.6359   0.02231   0.01467  -0.0393   0.9767   0.0253
  -7.250  -0.6048   0.02118   0.01351  -0.0408   0.9682   0.0265
  -7.000  -0.5731   0.02017   0.01243  -0.0422   0.9601   0.0277
  -6.750  -0.5424   0.01920   0.01138  -0.0432   0.9508   0.0289
  -6.500  -0.5134   0.01833   0.01041  -0.0439   0.9407   0.0303
  -6.250  -0.4844   0.01758   0.00954  -0.0445   0.9310   0.0317
  -6.000  -0.4588   0.01669   0.00864  -0.0446   0.9201   0.0340
  -5.750  -0.4333   0.01613   0.00804  -0.0445   0.9091   0.0367
  -5.500  -0.4079   0.01561   0.00742  -0.0443   0.8988   0.0396
  -5.250  -0.3834   0.01504   0.00676  -0.0439   0.8887   0.0426
  -5.000  -0.3591   0.01456   0.00626  -0.0435   0.8782   0.0477
  -4.750  -0.3342   0.01413   0.00577  -0.0431   0.8687   0.0539
  -4.500  -0.3094   0.01371   0.00531  -0.0427   0.8593   0.0641
  -4.250  -0.2850   0.01318   0.00487  -0.0423   0.8498   0.0878
  -4.000  -0.2616   0.01248   0.00442  -0.0420   0.8412   0.1517
  -3.500  -0.2186   0.01053   0.00373  -0.0411   0.8232   0.4613
  -3.250  -0.1927   0.01035   0.00366  -0.0407   0.8146   0.5157
  -3.000  -0.1661   0.01027   0.00360  -0.0403   0.8066   0.5543
  -2.750  -0.1401   0.01022   0.00363  -0.0397   0.7986   0.5967
  -2.500  -0.1143   0.01026   0.00374  -0.0390   0.7906   0.6348
  -2.250  -0.0875   0.01027   0.00373  -0.0386   0.7827   0.6527
  -2.000  -0.0596   0.01025   0.00362  -0.0386   0.7748   0.6621
  -1.750  -0.0322   0.01023   0.00356  -0.0384   0.7674   0.6696
  -1.500  -0.0040   0.01021   0.00346  -0.0384   0.7601   0.6775
  -1.250   0.0237   0.01018   0.00341  -0.0383   0.7528   0.6831
  -1.000   0.0517   0.01018   0.00335  -0.0383   0.7457   0.6903
  -0.750   0.0795   0.01016   0.00330  -0.0383   0.7381   0.6963
  -0.500   0.1074   0.01016   0.00327  -0.0382   0.7313   0.7029
  -0.250   0.1355   0.01017   0.00326  -0.0383   0.7241   0.7101
   0.000   0.1631   0.01018   0.00326  -0.0382   0.7182   0.7169
   0.250   0.1913   0.01020   0.00328  -0.0383   0.7110   0.7246
   0.500   0.2188   0.01022   0.00330  -0.0381   0.7048   0.7310
   0.750   0.2470   0.01025   0.00334  -0.0382   0.6978   0.7390
   1.000   0.2744   0.01028   0.00340  -0.0380   0.6915   0.7458
   1.250   0.3024   0.01033   0.00346  -0.0381   0.6858   0.7545
   1.500   0.3297   0.01037   0.00357  -0.0379   0.6793   0.7618
   1.750   0.3577   0.01043   0.00364  -0.0379   0.6738   0.7704
   2.000   0.3848   0.01048   0.00377  -0.0377   0.6672   0.7777
   2.250   0.4124   0.01054   0.00387  -0.0377   0.6605   0.7865
   2.500   0.4392   0.01060   0.00400  -0.0374   0.6525   0.7947
   2.750   0.4663   0.01066   0.00411  -0.0371   0.6450   0.8037
   3.000   0.4930   0.01072   0.00426  -0.0368   0.6365   0.8127
   3.250   0.5188   0.01075   0.00432  -0.0362   0.6210   0.8215
   3.500   0.5438   0.01077   0.00431  -0.0354   0.5950   0.8315
   3.750   0.5673   0.01082   0.00433  -0.0343   0.5631   0.8409
   4.000   0.5910   0.01093   0.00440  -0.0334   0.5284   0.8510
   4.500   0.6360   0.01137   0.00468  -0.0311   0.4384   0.8731
   4.750   0.6510   0.01219   0.00498  -0.0290   0.3243   0.8859
   5.000   0.6640   0.01335   0.00560  -0.0270   0.2096   0.9006
   5.250   0.6793   0.01433   0.00620  -0.0253   0.1283   0.9174
   5.500   0.6980   0.01510   0.00676  -0.0241   0.0830   0.9364
   5.750   0.7228   0.01575   0.00733  -0.0240   0.0604   0.9583
   6.000   0.7523   0.01639   0.00794  -0.0250   0.0489   1.0000
   6.250   0.7747   0.01704   0.00860  -0.0246   0.0427   1.0000
   6.500   0.7971   0.01767   0.00926  -0.0242   0.0384   1.0000
   6.750   0.8173   0.01849   0.01007  -0.0234   0.0349   1.0000
   7.000   0.8389   0.01914   0.01079  -0.0228   0.0322   1.0000
   7.250   0.8595   0.01986   0.01156  -0.0221   0.0299   1.0000
   7.500   0.8781   0.02076   0.01248  -0.0212   0.0282   1.0000
   7.750   0.8950   0.02185   0.01360  -0.0200   0.0269   1.0000
   8.000   0.9140   0.02276   0.01460  -0.0190   0.0259   1.0000
   8.250   0.9328   0.02376   0.01567  -0.0180   0.0249   1.0000
   8.500   0.9515   0.02482   0.01682  -0.0171   0.0240   1.0000
   8.750   0.9705   0.02590   0.01797  -0.0162   0.0232   1.0000
   9.000   0.9891   0.02695   0.01906  -0.0153   0.0224   1.0000
   9.250   1.0068   0.02810   0.02024  -0.0145   0.0216   1.0000
   9.500   1.0251   0.02964   0.02184  -0.0137   0.0208   1.0000
   9.750   1.0434   0.03095   0.02335  -0.0128   0.0203   1.0000
  10.000   1.0611   0.03251   0.02510  -0.0119   0.0198   1.0000
  10.250   1.0771   0.03422   0.02703  -0.0108   0.0194   1.0000
  10.500   1.0906   0.03608   0.02910  -0.0095   0.0190   1.0000
  10.750   1.1010   0.03804   0.03129  -0.0080   0.0186   1.0000
  11.000   1.1086   0.04013   0.03362  -0.0064   0.0183   1.0000
  11.250   1.1130   0.04230   0.03602  -0.0047   0.0180   1.0000
  11.500   1.1151   0.04447   0.03841  -0.0031   0.0177   1.0000
  11.750   1.1150   0.04675   0.04090  -0.0016   0.0175   1.0000
  12.000   1.1148   0.04885   0.04314  -0.0005   0.0171   1.0000
  12.250   1.1118   0.05144   0.04591   0.0004   0.0169   1.0000
  12.500   1.1101   0.05383   0.04841   0.0009   0.0166   1.0000
  12.750   1.1049   0.05691   0.05163   0.0011   0.0164   1.0000
  13.000   1.0953   0.06072   0.05563   0.0009   0.0163   1.0000
  13.250   1.0819   0.06520   0.06031   0.0001   0.0162   1.0000
  13.500   1.0650   0.07036   0.06568  -0.0015   0.0161   1.0000
  13.750   1.0462   0.07619   0.07173  -0.0038   0.0161   1.0000
  14.000   1.0254   0.08281   0.07857  -0.0071   0.0161   1.0000
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