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NACA 64(1)-212 MOD A (n64212ma-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: NACA 64(1)-212 MOD A (n64212ma-il)
Reynolds number: 200,000
Max Cl/Cd: 48.4 at α=7.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-n64212ma-il-200000-n5.txt
Download as CSV file: xf-n64212ma-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 64(1)-212 MOD A                            
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.3926   0.10319   0.09934  -0.0290   1.0000   0.0357
 -10.000  -0.3972   0.09820   0.09439  -0.0326   1.0000   0.0358
  -9.750  -0.4025   0.09299   0.08921  -0.0363   1.0000   0.0359
  -9.500  -0.4012   0.08900   0.08527  -0.0380   1.0000   0.0360
  -9.250  -0.3890   0.08743   0.08374  -0.0363   1.0000   0.0365
  -9.000  -0.3876   0.08393   0.08028  -0.0378   1.0000   0.0367
  -8.750  -0.3845   0.08107   0.07746  -0.0387   1.0000   0.0377
  -8.500  -0.3911   0.07652   0.07297  -0.0420   1.0000   0.0381
  -8.250  -0.4076   0.07200   0.06850  -0.0453   1.0000   0.0386
  -8.000  -0.4264   0.06478   0.06101  -0.0540   0.9718   0.0403
  -7.500  -0.4076   0.05169   0.04738  -0.0614   0.9385   0.0314
  -7.250  -0.3914   0.04848   0.04399  -0.0626   0.9225   0.0311
  -7.000  -0.3780   0.04505   0.04030  -0.0629   0.9069   0.0309
  -6.750  -0.3642   0.04191   0.03690  -0.0626   0.8924   0.0308
  -6.500  -0.3546   0.03690   0.03121  -0.0612   0.8793   0.0317
  -5.750  -0.2995   0.03012   0.02364  -0.0584   0.8420   0.0319
  -5.250  -0.2554   0.02694   0.02005  -0.0570   0.8213   0.0323
  -5.000  -0.2322   0.02546   0.01834  -0.0562   0.8112   0.0326
  -4.750  -0.2081   0.02419   0.01688  -0.0556   0.8003   0.0331
  -4.500  -0.1835   0.02308   0.01556  -0.0549   0.7894   0.0341
  -4.250  -0.1582   0.02176   0.01398  -0.0543   0.7792   0.0349
  -4.000  -0.1324   0.02052   0.01249  -0.0536   0.7691   0.0352
  -3.750  -0.1062   0.01944   0.01119  -0.0529   0.7593   0.0356
  -3.500  -0.0799   0.01851   0.01008  -0.0523   0.7487   0.0360
  -3.250  -0.0539   0.01779   0.00931  -0.0518   0.7377   0.0364
  -3.000  -0.0279   0.01718   0.00865  -0.0513   0.7242   0.0370
  -2.750  -0.0019   0.01666   0.00807  -0.0507   0.7106   0.0379
  -2.500   0.0241   0.01618   0.00749  -0.0501   0.6973   0.0392
  -2.250   0.0504   0.01567   0.00689  -0.0495   0.6839   0.0403
  -2.000   0.0761   0.01517   0.00637  -0.0490   0.6717   0.0409
  -1.750   0.1019   0.01475   0.00595  -0.0484   0.6576   0.0418
  -1.500   0.1278   0.01439   0.00556  -0.0479   0.6416   0.0427
  -1.250   0.1534   0.01408   0.00517  -0.0473   0.6216   0.0439
  -1.000   0.1793   0.01381   0.00482  -0.0468   0.6023   0.0454
  -0.750   0.2051   0.01358   0.00456  -0.0464   0.5811   0.0474
  -0.500   0.2310   0.01344   0.00431  -0.0459   0.5529   0.0500
  -0.250   0.2564   0.01333   0.00406  -0.0454   0.5165   0.0523
   0.000   0.2768   0.01376   0.00390  -0.0441   0.3890   0.0550
   0.250   0.2959   0.01455   0.00405  -0.0430   0.2554   0.0585
   0.500   0.3211   0.01469   0.00404  -0.0426   0.2223   0.0657
   0.750   0.3464   0.01479   0.00403  -0.0423   0.1936   0.0813
   1.000   0.3671   0.01326   0.00409  -0.0421   0.1760   0.6097
   1.250   0.3900   0.01328   0.00434  -0.0408   0.1604   0.6975
   1.500   0.4132   0.01343   0.00455  -0.0395   0.1447   0.7440
   1.750   0.4362   0.01363   0.00475  -0.0383   0.1339   0.7805
   2.000   0.4581   0.01380   0.00495  -0.0367   0.1285   0.8099
   2.250   0.4811   0.01398   0.00512  -0.0354   0.1256   0.8303
   2.500   0.5054   0.01415   0.00526  -0.0346   0.1237   0.8419
   2.750   0.5303   0.01432   0.00540  -0.0339   0.1222   0.8511
   3.000   0.5542   0.01449   0.00556  -0.0330   0.1211   0.8614
   3.250   0.5780   0.01468   0.00573  -0.0322   0.1201   0.8721
   3.500   0.6014   0.01487   0.00591  -0.0312   0.1194   0.8839
   3.750   0.6245   0.01506   0.00610  -0.0302   0.1188   0.8958
   4.000   0.6478   0.01526   0.00630  -0.0293   0.1181   0.9092
   4.250   0.6710   0.01546   0.00650  -0.0284   0.1170   0.9248
   4.500   0.6960   0.01569   0.00673  -0.0278   0.1155   0.9424
   4.750   0.7252   0.01600   0.00702  -0.0284   0.1136   0.9626
   5.000   0.7566   0.01638   0.00734  -0.0295   0.1118   1.0000
   5.250   0.7819   0.01672   0.00766  -0.0294   0.1102   1.0000
   5.500   0.8067   0.01709   0.00800  -0.0292   0.1089   1.0000
   5.750   0.8311   0.01748   0.00837  -0.0289   0.1078   1.0000
   6.000   0.8549   0.01789   0.00875  -0.0285   0.1069   1.0000
   6.250   0.8782   0.01835   0.00917  -0.0280   0.1060   1.0000
   6.500   0.9013   0.01881   0.00961  -0.0275   0.1054   1.0000
   6.750   0.9251   0.01919   0.01002  -0.0271   0.1045   1.0000
   7.000   0.9483   0.01960   0.01045  -0.0266   0.1033   1.0000
   7.250   0.9709   0.02006   0.01090  -0.0260   0.1021   1.0000
   7.500   0.9927   0.02056   0.01141  -0.0254   0.1008   1.0000
   7.750   1.0137   0.02114   0.01195  -0.0247   0.0997   1.0000
   8.000   1.0358   0.02158   0.01244  -0.0240   0.0985   1.0000
   8.250   1.0575   0.02202   0.01294  -0.0233   0.0972   1.0000
   8.500   1.0779   0.02254   0.01349  -0.0225   0.0953   1.0000
   8.750   1.0966   0.02314   0.01406  -0.0215   0.0938   1.0000
   9.000   1.1164   0.02351   0.01457  -0.0205   0.0921   1.0000
   9.250   1.1347   0.02398   0.01513  -0.0194   0.0899   1.0000
   9.500   1.1524   0.02450   0.01569  -0.0182   0.0880   1.0000
   9.750   1.1717   0.02488   0.01623  -0.0172   0.0853   1.0000
  10.000   1.1908   0.02529   0.01677  -0.0163   0.0822   1.0000
  10.250   1.2120   0.02565   0.01733  -0.0155   0.0768   1.0000
  10.500   1.2322   0.02584   0.01744  -0.0149   0.0574   1.0000
  10.750   1.2455   0.02674   0.01821  -0.0137   0.0541   1.0000
  11.000   1.2560   0.02793   0.01941  -0.0122   0.0519   1.0000
  11.250   1.2648   0.02925   0.02079  -0.0108   0.0502   1.0000
  11.500   1.2747   0.03050   0.02213  -0.0095   0.0487   1.0000
  11.750   1.2837   0.03184   0.02356  -0.0083   0.0474   1.0000
  12.000   1.2911   0.03332   0.02512  -0.0071   0.0465   1.0000
  12.250   1.3009   0.03465   0.02658  -0.0062   0.0453   1.0000
  12.500   1.3084   0.03620   0.02823  -0.0053   0.0445   1.0000
  12.750   1.3142   0.03794   0.03006  -0.0045   0.0438   1.0000
  13.000   1.3200   0.03973   0.03195  -0.0038   0.0432   1.0000
  13.250   1.3261   0.04155   0.03389  -0.0032   0.0425   1.0000
  13.500   1.3306   0.04357   0.03603  -0.0028   0.0419   1.0000
  13.750   1.3339   0.04579   0.03837  -0.0026   0.0414   1.0000
  14.000   1.3358   0.04822   0.04091  -0.0025   0.0410   1.0000
  14.250   1.3362   0.05090   0.04369  -0.0026   0.0406   1.0000
  14.500   1.3356   0.05379   0.04669  -0.0029   0.0403   1.0000
  14.750   1.3354   0.05674   0.04977  -0.0034   0.0400   1.0000
  15.000   1.3341   0.05996   0.05312  -0.0041   0.0395   1.0000
  15.250   1.3316   0.06348   0.05678  -0.0051   0.0390   1.0000
  15.500   1.3277   0.06734   0.06077  -0.0064   0.0386   1.0000
  15.750   1.3226   0.07155   0.06511  -0.0081   0.0382   1.0000
  16.000   1.3161   0.07616   0.06985  -0.0101   0.0379   1.0000
  16.250   1.3084   0.08116   0.07497  -0.0124   0.0376   1.0000
  16.500   1.2998   0.08651   0.08044  -0.0151   0.0374   1.0000
  16.750   1.2904   0.09227   0.08635  -0.0182   0.0370   1.0000
  17.000   1.2807   0.09827   0.09250  -0.0215   0.0368   1.0000
  17.250   1.2703   0.10451   0.09888  -0.0250   0.0365   1.0000
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