Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

NACA 65(4)-421 (naca654421-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: NACA 65(4)-421 (naca654421-il)
Reynolds number: 1,000,000
Max Cl/Cd: 121.96 at α=6.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-naca654421-il-1000000.txt
Download as CSV file: xf-naca654421-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 65(4)-421                                  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -19.750  -0.9796   0.07928   0.07559  -0.0811   1.0000   0.0216
 -19.500  -0.9829   0.07578   0.07199  -0.0824   1.0000   0.0217
 -19.250  -0.9830   0.07262   0.06877  -0.0838   1.0000   0.0219
 -19.000  -0.9835   0.06958   0.06563  -0.0848   1.0000   0.0220
 -18.750  -0.9829   0.06665   0.06262  -0.0859   1.0000   0.0223
 -18.500  -0.9818   0.06391   0.05979  -0.0867   1.0000   0.0224
 -18.250  -0.9798   0.06131   0.05710  -0.0874   1.0000   0.0226
 -18.000  -0.9770   0.05884   0.05455  -0.0881   1.0000   0.0227
 -17.750  -0.9736   0.05650   0.05213  -0.0886   1.0000   0.0228
 -17.500  -0.9687   0.05439   0.04994  -0.0890   1.0000   0.0229
 -17.250  -0.9646   0.05220   0.04768  -0.0895   1.0000   0.0230
 -17.000  -0.9578   0.05050   0.04590  -0.0889   1.0000   0.0233
 -16.750  -0.9487   0.04905   0.04445  -0.0885   1.0000   0.0237
 -16.500  -0.9410   0.04743   0.04282  -0.0879   0.9802   0.0239
 -16.250  -0.9113   0.04538   0.04072  -0.0926   0.9669   0.0242
 -16.000  -0.8780   0.04336   0.03865  -0.0979   0.9596   0.0246
 -15.750  -0.8420   0.04148   0.03669  -0.1034   0.9514   0.0248
 -15.500  -0.8049   0.03966   0.03477  -0.1091   0.9405   0.0251
 -15.250  -0.7742   0.03811   0.03309  -0.1133   0.9217   0.0255
 -15.000  -0.7570   0.03698   0.03183  -0.1141   0.9007   0.0257
 -14.750  -0.7443   0.03597   0.03070  -0.1136   0.8839   0.0259
 -14.500  -0.7323   0.03500   0.02962  -0.1131   0.8701   0.0261
 -14.250  -0.7205   0.03401   0.02854  -0.1125   0.8584   0.0263
 -14.000  -0.7079   0.03309   0.02754  -0.1119   0.8484   0.0265
 -13.750  -0.6950   0.03220   0.02656  -0.1114   0.8386   0.0267
 -13.500  -0.6819   0.03131   0.02561  -0.1107   0.8302   0.0268
 -13.250  -0.6688   0.03043   0.02466  -0.1101   0.8216   0.0269
 -13.000  -0.6569   0.02954   0.02370  -0.1092   0.8135   0.0271
 -12.750  -0.6483   0.02844   0.02256  -0.1080   0.8059   0.0274
 -12.500  -0.6387   0.02745   0.02149  -0.1070   0.7980   0.0275
 -12.250  -0.6295   0.02639   0.02040  -0.1059   0.7913   0.0278
 -12.000  -0.6182   0.02550   0.01946  -0.1050   0.7844   0.0281
 -11.750  -0.6067   0.02469   0.01859  -0.1040   0.7774   0.0283
 -11.500  -0.5945   0.02384   0.01772  -0.1031   0.7719   0.0286
 -11.250  -0.5831   0.02300   0.01683  -0.1020   0.7657   0.0289
 -11.000  -0.5702   0.02230   0.01607  -0.1010   0.7592   0.0292
 -10.750  -0.5569   0.02155   0.01529  -0.1000   0.7539   0.0296
 -10.500  -0.5447   0.02079   0.01448  -0.0989   0.7482   0.0298
 -10.250  -0.5313   0.02014   0.01377  -0.0978   0.7423   0.0301
 -10.000  -0.5180   0.01945   0.01305  -0.0967   0.7374   0.0305
  -9.750  -0.5031   0.01885   0.01241  -0.0957   0.7325   0.0309
  -9.500  -0.4895   0.01822   0.01173  -0.0946   0.7274   0.0311
  -9.250  -0.4762   0.01762   0.01106  -0.0933   0.7222   0.0313
  -9.000  -0.4668   0.01679   0.01021  -0.0916   0.7183   0.0321
  -8.750  -0.4545   0.01613   0.00953  -0.0901   0.7138   0.0326
  -8.500  -0.4407   0.01557   0.00894  -0.0888   0.7092   0.0334
  -8.250  -0.4266   0.01509   0.00840  -0.0874   0.7043   0.0342
  -8.000  -0.4113   0.01460   0.00790  -0.0861   0.7006   0.0350
  -7.750  -0.3954   0.01416   0.00744  -0.0849   0.6969   0.0358
  -7.500  -0.3825   0.01364   0.00689  -0.0832   0.6930   0.0370
  -7.250  -0.3706   0.01315   0.00638  -0.0812   0.6891   0.0387
  -7.000  -0.3585   0.01278   0.00596  -0.0791   0.6848   0.0408
  -6.750  -0.3513   0.01241   0.00561  -0.0761   0.6821   0.0440
  -6.500  -0.3378   0.01201   0.00525  -0.0742   0.6790   0.0526
  -6.250  -0.3269   0.01141   0.00481  -0.0720   0.6757   0.0835
  -6.000  -0.3162   0.01069   0.00433  -0.0699   0.6723   0.1370
  -5.750  -0.3016   0.01004   0.00390  -0.0683   0.6685   0.1948
  -5.500  -0.2860   0.00926   0.00345  -0.0671   0.6656   0.2702
  -5.250  -0.2699   0.00827   0.00291  -0.0660   0.6632   0.3726
  -5.000  -0.2487   0.00755   0.00257  -0.0656   0.6606   0.4675
  -4.750  -0.2211   0.00739   0.00248  -0.0659   0.6579   0.5003
  -4.500  -0.1924   0.00733   0.00243  -0.0663   0.6552   0.5183
  -4.250  -0.1637   0.00730   0.00241  -0.0667   0.6525   0.5323
  -4.000  -0.1345   0.00733   0.00239  -0.0672   0.6492   0.5418
  -3.750  -0.1050   0.00733   0.00239  -0.0677   0.6474   0.5518
  -3.500  -0.0754   0.00732   0.00238  -0.0682   0.6452   0.5598
  -3.250  -0.0458   0.00734   0.00241  -0.0687   0.6428   0.5683
  -3.000  -0.0162   0.00738   0.00243  -0.0692   0.6404   0.5763
  -2.750   0.0132   0.00745   0.00251  -0.0696   0.6381   0.5853
  -2.500   0.0429   0.00756   0.00256  -0.0702   0.6357   0.5907
  -2.250   0.0722   0.00756   0.00253  -0.0707   0.6331   0.5939
  -2.000   0.1017   0.00757   0.00253  -0.0712   0.6307   0.5965
  -1.750   0.1313   0.00755   0.00252  -0.0718   0.6291   0.5985
  -1.500   0.1610   0.00754   0.00251  -0.0723   0.6272   0.6005
  -1.250   0.1906   0.00754   0.00250  -0.0729   0.6251   0.6024
  -1.000   0.2203   0.00755   0.00250  -0.0734   0.6229   0.6045
  -0.750   0.2498   0.00757   0.00249  -0.0740   0.6208   0.6065
  -0.500   0.2794   0.00760   0.00250  -0.0745   0.6187   0.6082
  -0.250   0.3089   0.00766   0.00251  -0.0751   0.6165   0.6096
   0.000   0.3385   0.00770   0.00253  -0.0757   0.6138   0.6118
   0.250   0.3678   0.00768   0.00254  -0.0762   0.6124   0.6143
   0.500   0.3972   0.00767   0.00257  -0.0767   0.6107   0.6166
   0.750   0.4265   0.00768   0.00259  -0.0772   0.6088   0.6187
   1.000   0.4559   0.00770   0.00262  -0.0777   0.6068   0.6207
   1.250   0.4853   0.00773   0.00265  -0.0783   0.6049   0.6227
   1.500   0.5147   0.00776   0.00269  -0.0788   0.6031   0.6247
   1.750   0.5440   0.00781   0.00273  -0.0793   0.6011   0.6265
   2.000   0.5734   0.00788   0.00278  -0.0798   0.5989   0.6281
   2.250   0.6029   0.00797   0.00286  -0.0804   0.5961   0.6307
   2.500   0.6318   0.00796   0.00291  -0.0809   0.5947   0.6335
   2.750   0.6607   0.00798   0.00297  -0.0813   0.5932   0.6359
   3.000   0.6896   0.00800   0.00304  -0.0818   0.5913   0.6382
   3.250   0.7184   0.00803   0.00309  -0.0822   0.5891   0.6405
   3.500   0.7470   0.00806   0.00314  -0.0826   0.5864   0.6428
   3.750   0.7755   0.00811   0.00319  -0.0829   0.5835   0.6449
   4.000   0.8041   0.00821   0.00327  -0.0834   0.5797   0.6468
   4.250   0.8318   0.00822   0.00332  -0.0836   0.5765   0.6494
   4.500   0.8585   0.00817   0.00334  -0.0836   0.5712   0.6525
   4.750   0.8845   0.00819   0.00335  -0.0834   0.5644   0.6554
   5.000   0.9114   0.00825   0.00344  -0.0835   0.5595   0.6583
   5.250   0.9383   0.00826   0.00351  -0.0835   0.5543   0.6610
   5.500   0.9628   0.00834   0.00356  -0.0831   0.5461   0.6636
   5.750   0.9887   0.00839   0.00364  -0.0829   0.5377   0.6658
   6.000   1.0117   0.00849   0.00373  -0.0823   0.5286   0.6692
   6.250   1.0369   0.00854   0.00384  -0.0820   0.5199   0.6725
   6.500   1.0586   0.00868   0.00398  -0.0811   0.5091   0.6758
   6.750   1.0781   0.00887   0.00414  -0.0798   0.4944   0.6790
   7.000   1.0927   0.00911   0.00433  -0.0776   0.4740   0.6823
   7.250   1.0963   0.00954   0.00465  -0.0733   0.4460   0.6852
   7.500   1.0937   0.01024   0.00521  -0.0681   0.4093   0.6898
   7.750   1.0849   0.01125   0.00604  -0.0623   0.3685   0.6940
   8.000   1.0764   0.01241   0.00704  -0.0569   0.3315   0.6983
   8.250   1.0682   0.01372   0.00817  -0.0520   0.2950   0.7022
   8.500   1.0600   0.01517   0.00945  -0.0474   0.2591   0.7059
   8.750   1.0527   0.01670   0.01085  -0.0433   0.2261   0.7110
   9.000   1.0505   0.01813   0.01218  -0.0401   0.2001   0.7157
   9.250   1.0456   0.01980   0.01372  -0.0367   0.1706   0.7204
   9.500   1.0434   0.02144   0.01523  -0.0339   0.1455   0.7244
   9.750   1.0401   0.02317   0.01687  -0.0311   0.1202   0.7301
  10.000   1.0379   0.02495   0.01854  -0.0287   0.0969   0.7356
  10.250   1.0346   0.02690   0.02037  -0.0263   0.0726   0.7408
  10.500   1.0331   0.02881   0.02217  -0.0242   0.0519   0.7459
  10.750   1.0358   0.03050   0.02381  -0.0225   0.0387   0.7517
  11.000   1.0431   0.03195   0.02527  -0.0213   0.0334   0.7575
  11.250   1.0516   0.03336   0.02667  -0.0203   0.0302   0.7628
  11.500   1.0626   0.03458   0.02795  -0.0195   0.0284   0.7693
  11.750   1.0713   0.03601   0.02941  -0.0186   0.0266   0.7759
  12.000   1.0825   0.03730   0.03074  -0.0180   0.0255   0.7821
  12.250   1.0936   0.03859   0.03210  -0.0173   0.0247   0.7895
  12.500   1.1042   0.03995   0.03351  -0.0167   0.0237   0.7971
  12.750   1.1122   0.04155   0.03515  -0.0159   0.0227   0.8046
  13.000   1.1206   0.04313   0.03681  -0.0153   0.0221   0.8128
  13.250   1.1325   0.04446   0.03819  -0.0149   0.0216   0.8208
  13.500   1.1424   0.04594   0.03975  -0.0143   0.0210   0.8298
  13.750   1.1526   0.04746   0.04133  -0.0139   0.0206   0.8388
  14.000   1.1619   0.04900   0.04295  -0.0134   0.0201   0.8490
  14.250   1.1692   0.05078   0.04479  -0.0129   0.0196   0.8600
  14.500   1.1709   0.05309   0.04719  -0.0122   0.0189   0.8728
  14.750   1.1777   0.05486   0.04906  -0.0116   0.0188   0.8894
  15.000   1.1846   0.05646   0.05080  -0.0108   0.0186   0.9149
  15.250   1.1994   0.05821   0.05271  -0.0118   0.0183   0.9631
  15.500   1.2073   0.06016   0.05471  -0.0119   0.0181   1.0000
  15.750   1.2156   0.06217   0.05676  -0.0120   0.0178   1.0000
  16.000   1.2236   0.06423   0.05886  -0.0121   0.0175   1.0000
  16.250   1.2298   0.06653   0.06121  -0.0123   0.0173   1.0000
  16.500   1.2377   0.06867   0.06339  -0.0125   0.0170   1.0000
  16.750   1.2440   0.07101   0.06577  -0.0128   0.0168   1.0000
  17.000   1.2490   0.07353   0.06834  -0.0132   0.0167   1.0000
  17.250   1.2532   0.07616   0.07101  -0.0135   0.0164   1.0000
  17.500   1.2547   0.07918   0.07408  -0.0140   0.0162   1.0000
  17.750   1.2512   0.08281   0.07777  -0.0145   0.0158   1.0000
  18.000   1.2552   0.08563   0.08065  -0.0151   0.0158   1.0000
<< Back to NACA 65(4)-421 (naca654421-il)

Polar data table (+)

Polar graphs


<< Back to NACA 65(4)-421 (naca654421-il)