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NACA 6-H-20 AIRFOIL (n6h20-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: NACA 6-H-20 AIRFOIL (n6h20-il)
Reynolds number: 500,000
Max Cl/Cd: 67.58 at α=8.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-n6h20-il-500000.txt
Download as CSV file: xf-n6h20-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 6-H-20 AIRFOIL                             
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.000  -0.1387   0.10904   0.10521  -0.0570   0.6267   0.0324
 -11.750  -0.1357   0.10590   0.10207  -0.0584   0.6260   0.0333
 -11.500  -0.1815   0.09531   0.09155  -0.0670   0.6258   0.0354
 -11.250  -0.1753   0.09260   0.08884  -0.0671   0.6250   0.0356
 -11.000  -0.1686   0.09039   0.08664  -0.0673   0.6240   0.0358
 -10.750  -0.1648   0.08767   0.08394  -0.0682   0.6235   0.0360
 -10.500  -0.1601   0.08526   0.08156  -0.0689   0.6229   0.0364
 -10.250  -0.1658   0.08155   0.07788  -0.0710   0.6223   0.0366
 -10.000  -0.1738   0.07798   0.07433  -0.0725   0.6216   0.0369
  -9.750  -0.1850   0.07446   0.07082  -0.0732   0.6207   0.0372
  -9.500  -0.1994   0.07102   0.06737  -0.0729   0.6199   0.0376
  -9.250  -0.2160   0.06771   0.06404  -0.0716   0.6191   0.0379
  -9.000  -0.2330   0.06461   0.06091  -0.0691   0.6183   0.0384
  -8.750  -0.3452   0.05542   0.05110  -0.0539   0.6178   0.0410
  -8.500  -0.3291   0.05324   0.04902  -0.0537   0.6169   0.0413
  -8.250  -0.3214   0.05176   0.04753  -0.0518   0.6160   0.0415
  -8.000  -0.3119   0.05062   0.04637  -0.0499   0.6152   0.0418
  -7.750  -0.3051   0.04915   0.04484  -0.0476   0.6143   0.0422
  -7.500  -0.2964   0.04783   0.04346  -0.0455   0.6135   0.0428
  -7.250  -0.2895   0.04611   0.04163  -0.0429   0.6128   0.0437
  -7.000  -0.3183   0.04129   0.03606  -0.0331   0.6121   0.0475
  -6.750  -0.2997   0.03958   0.03437  -0.0324   0.6114   0.0479
  -6.500  -0.2828   0.03827   0.03302  -0.0312   0.6106   0.0484
  -6.250  -0.2659   0.03712   0.03180  -0.0298   0.6098   0.0490
  -6.000  -0.2499   0.03596   0.03052  -0.0282   0.6089   0.0501
  -5.750  -0.2443   0.03716   0.03113  -0.0227   0.6078   0.0539
  -5.500  -0.2334   0.02727   0.02027  -0.0189   0.6072   0.0411
  -5.250  -0.2015   0.02580   0.01875  -0.0200   0.6064   0.0403
  -5.000  -0.1674   0.02427   0.01709  -0.0214   0.6056   0.0400
  -4.750  -0.1301   0.02308   0.01577  -0.0235   0.6047   0.0399
  -4.500  -0.0908   0.02219   0.01477  -0.0259   0.6037   0.0401
  -4.250  -0.0589   0.02184   0.01432  -0.0270   0.6027   0.0406
  -4.000   0.0128   0.02037   0.01279  -0.0360   0.6018   0.0412
  -3.750   0.0706   0.01955   0.01201  -0.0420   0.6009   0.0418
  -3.500   0.1100   0.01923   0.01171  -0.0444   0.5999   0.0425
  -3.250   0.1445   0.01901   0.01151  -0.0458   0.5989   0.0433
  -3.000   0.1775   0.01882   0.01133  -0.0470   0.5980   0.0441
  -2.750   0.2087   0.01867   0.01118  -0.0478   0.5972   0.0450
  -2.500   0.2380   0.01856   0.01108  -0.0483   0.5964   0.0462
  -2.250   0.2671   0.01842   0.01094  -0.0487   0.5957   0.0475
  -2.000   0.2952   0.01825   0.01081  -0.0490   0.5950   0.0492
  -1.750   0.3219   0.01818   0.01075  -0.0490   0.5943   0.0509
  -1.500   0.3481   0.01812   0.01070  -0.0489   0.5937   0.0529
  -1.250   0.3740   0.01806   0.01065  -0.0488   0.5930   0.0560
  -1.000   0.3991   0.01811   0.01071  -0.0485   0.5921   0.0602
  -0.750   0.4224   0.01831   0.01098  -0.0481   0.5909   0.0694
  -0.500   0.4371   0.01818   0.01140  -0.0464   0.5896   0.1983
  -0.250   0.4343   0.01806   0.01193  -0.0417   0.5878   0.3698
   0.000   0.4211   0.01799   0.01226  -0.0350   0.5855   0.4787
   0.250   0.3889   0.01769   0.01224  -0.0246   0.5833   0.5508
   0.500   0.3526   0.01770   0.01236  -0.0128   0.5814   0.5913
   0.750   0.3156   0.01763   0.01237   0.0000   0.5798   0.6322
   1.000   0.7575   0.02446   0.01957  -0.0706   0.5820   0.9214
   1.250   0.7945   0.02403   0.01910  -0.0728   0.5811   0.9226
   1.500   0.8271   0.02376   0.01880  -0.0741   0.5802   0.9238
   1.750   0.8571   0.02362   0.01864  -0.0750   0.5794   0.9249
   2.000   0.8855   0.02354   0.01853  -0.0756   0.5786   0.9260
   2.250   0.9133   0.02346   0.01843  -0.0761   0.5779   0.9274
   2.500   0.9398   0.02350   0.01845  -0.0763   0.5772   0.9294
   2.750   0.9202   0.02604   0.02097  -0.0671   0.5761   0.9355
   3.000   0.9539   0.02537   0.02033  -0.0692   0.5747   0.9361
   3.250   0.9814   0.02539   0.02045  -0.0705   0.5727   0.9366
   3.500   1.0077   0.02535   0.02045  -0.0711   0.5704   0.9369
   3.750   1.0340   0.02523   0.02035  -0.0716   0.5686   0.9372
   4.000   1.0610   0.02480   0.01991  -0.0718   0.5669   0.9374
   4.250   1.0867   0.02464   0.01975  -0.0719   0.5658   0.9376
   4.500   1.1139   0.02424   0.01934  -0.0722   0.5646   0.9378
   4.750   1.1420   0.02375   0.01883  -0.0724   0.5635   0.9380
   5.000   1.1710   0.02318   0.01821  -0.0728   0.5623   0.9382
   5.250   1.2001   0.02265   0.01762  -0.0731   0.5610   0.9383
   5.500   1.2250   0.02264   0.01765  -0.0733   0.5590   0.9387
   5.750   1.2459   0.02300   0.01813  -0.0734   0.5563   0.9393
   6.000   1.2683   0.02320   0.01841  -0.0734   0.5541   0.9399
   6.250   1.2923   0.02319   0.01844  -0.0735   0.5521   0.9405
   6.500   1.3177   0.02304   0.01831  -0.0737   0.5505   0.9411
   6.750   1.3451   0.02268   0.01796  -0.0740   0.5490   0.9417
   7.000   1.3733   0.02227   0.01753  -0.0743   0.5476   0.9422
   7.250   1.4029   0.02173   0.01696  -0.0748   0.5460   0.9427
   7.500   1.4242   0.02188   0.01718  -0.0745   0.5436   0.9439
   7.750   1.4314   0.02283   0.01827  -0.0724   0.5399   0.9475
   8.000   1.4168   0.02402   0.01953  -0.0653   0.5369   0.9525
   8.250   1.4448   0.02359   0.01913  -0.0661   0.5346   0.9529
   8.500   1.4774   0.02284   0.01837  -0.0671   0.5322   0.9531
   8.750   1.5076   0.02231   0.01783  -0.0679   0.5294   0.9535
   9.000   1.4196   0.02725   0.02304  -0.0557   0.5195   0.9627
   9.250   1.4165   0.02769   0.02346  -0.0503   0.5169   0.9679
   9.500   1.4598   0.02645   0.02221  -0.0523   0.5150   0.9678
   9.750   1.3893   0.03179   0.02769  -0.0446   0.5020   0.9720
  10.000   1.3178   0.03764   0.03360  -0.0342   0.4892   0.9812
  10.250   1.3574   0.03622   0.03218  -0.0358   0.4870   0.9814
  10.500   1.3343   0.03943   0.03545  -0.0329   0.4746   0.9827
  10.750   1.3733   0.03813   0.03414  -0.0344   0.4714   0.9831
  11.000   1.3609   0.04099   0.03705  -0.0325   0.4594   0.9846
  11.250   1.3665   0.04234   0.03841  -0.0315   0.4492   0.9859
  11.500   1.3888   0.04218   0.03821  -0.0314   0.4415   0.9868
  11.750   1.3840   0.04415   0.04019  -0.0293   0.4290   0.9881
  12.000   1.3843   0.04543   0.04143  -0.0270   0.4167   0.9886
  12.250   0.8826   0.03816   0.03347   0.0780   0.4316   0.9137
  12.500   0.9153   0.03753   0.03282   0.0769   0.4268   0.9137
  12.750   0.9157   0.03909   0.03438   0.0786   0.4160   0.9138
  13.000   0.9379   0.03915   0.03440   0.0784   0.4086   0.9138
  13.250   0.9449   0.04030   0.03553   0.0794   0.3984   0.9138
  13.500   0.9552   0.04122   0.03643   0.0801   0.3880   0.9139
  13.750   0.9694   0.04186   0.03701   0.0804   0.3783   0.9140
  14.000   0.9728   0.04335   0.03848   0.0815   0.3667   0.9141
  14.250   0.9791   0.04463   0.03973   0.0823   0.3557   0.9142
  14.500   0.9857   0.04590   0.04094   0.0831   0.3441   0.9144
  14.750   0.9909   0.04734   0.04234   0.0838   0.3326   0.9145
  15.000   0.9944   0.04897   0.04397   0.0846   0.3217   0.9146
  15.250   0.9977   0.05063   0.04558   0.0854   0.3096   0.9148
  15.500   1.0023   0.05222   0.04712   0.0859   0.2989   0.9149
  15.750   1.0021   0.05428   0.04916   0.0867   0.2853   0.9151
  16.000   1.0046   0.05616   0.05100   0.0872   0.2724   0.9152
  16.250   1.0080   0.05800   0.05280   0.0876   0.2613   0.9154
  16.500   1.0082   0.06014   0.05490   0.0881   0.2510   0.9156
  16.750   1.0138   0.06185   0.05661   0.0883   0.2418   0.9158
  17.000   1.0186   0.06365   0.05837   0.0884   0.2341   0.9160
  17.250   1.0236   0.06551   0.06025   0.0884   0.2263   0.9162
  17.500   1.0284   0.06737   0.06208   0.0885   0.2194   0.9164
  17.750   1.0360   0.06904   0.06379   0.0883   0.2118   0.9166
  18.000   1.0379   0.07124   0.06596   0.0883   0.2037   0.9168
  18.250   1.0436   0.07316   0.06793   0.0880   0.1939   0.9170
  18.500   1.0432   0.07571   0.07046   0.0880   0.1769   0.9172
  18.750   1.0188   0.08075   0.07525   0.0885   0.1363   0.9173
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