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NACA 66 (p51hroot-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: NACA 66 (p51hroot-il)
Reynolds number: 500,000
Max Cl/Cd: 67.21 at α=4°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-p51hroot-il-500000.txt
Download as CSV file: xf-p51hroot-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 66                                         
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -12.500  -0.4197   0.08175   0.07913  -0.0679   0.8541   0.0332
 -12.250  -0.4669   0.06836   0.06563  -0.0762   0.8537   0.0321
 -12.000  -0.5097   0.05937   0.05648  -0.0802   0.8522   0.0317
 -11.750  -0.7328   0.04661   0.04245  -0.0787   0.8581   0.0227
 -11.500  -0.7508   0.04360   0.03918  -0.0749   0.8535   0.0226
 -11.250  -0.7604   0.04083   0.03622  -0.0716   0.8493   0.0223
 -11.000  -0.7705   0.03828   0.03342  -0.0675   0.8448   0.0222
 -10.750  -0.7785   0.03575   0.03059  -0.0631   0.8409   0.0223
 -10.500  -0.7758   0.03364   0.02819  -0.0602   0.8379   0.0223
 -10.250  -0.7721   0.03212   0.02632  -0.0570   0.8349   0.0229
 -10.000  -0.7622   0.03083   0.02479  -0.0548   0.8323   0.0231
  -9.750  -0.7485   0.02835   0.02200  -0.0533   0.8298   0.0234
  -9.500  -0.7229   0.02567   0.01917  -0.0540   0.8279   0.0239
  -9.250  -0.7004   0.02454   0.01797  -0.0538   0.8257   0.0245
  -9.000  -0.6784   0.02380   0.01719  -0.0534   0.8237   0.0252
  -8.750  -0.6538   0.02275   0.01603  -0.0533   0.8219   0.0258
  -8.500  -0.6289   0.02183   0.01499  -0.0532   0.8202   0.0265
  -8.250  -0.6044   0.02111   0.01414  -0.0530   0.8184   0.0274
  -8.000  -0.5819   0.02065   0.01359  -0.0524   0.8168   0.0281
  -7.750  -0.5449   0.01900   0.01191  -0.0548   0.8156   0.0295
  -7.500  -0.5192   0.01830   0.01123  -0.0549   0.8140   0.0305
  -7.250  -0.4950   0.01770   0.01060  -0.0547   0.8122   0.0313
  -7.000  -0.4723   0.01718   0.01007  -0.0542   0.8103   0.0323
  -6.750  -0.4506   0.01676   0.00961  -0.0535   0.8085   0.0335
  -6.500  -0.4293   0.01640   0.00919  -0.0526   0.8069   0.0343
  -6.250  -0.4098   0.01583   0.00857  -0.0514   0.8055   0.0350
  -6.000  -0.3956   0.01511   0.00783  -0.0494   0.8040   0.0364
  -5.750  -0.3769   0.01474   0.00744  -0.0481   0.8026   0.0376
  -5.500  -0.3567   0.01443   0.00713  -0.0470   0.8012   0.0393
  -5.250  -0.3359   0.01412   0.00680  -0.0461   0.7999   0.0407
  -5.000  -0.3142   0.01385   0.00651  -0.0453   0.7986   0.0421
  -4.750  -0.2950   0.01345   0.00610  -0.0440   0.7971   0.0445
  -4.500  -0.2735   0.01317   0.00583  -0.0432   0.7957   0.0477
  -4.250  -0.2507   0.01295   0.00560  -0.0426   0.7944   0.0519
  -4.000  -0.2302   0.01259   0.00533  -0.0415   0.7929   0.0672
  -3.750  -0.2245   0.01142   0.00488  -0.0382   0.7911   0.2263
  -3.500  -0.2238   0.01006   0.00442  -0.0340   0.7896   0.4376
  -3.250  -0.2204   0.00902   0.00428  -0.0297   0.7882   0.6450
  -3.000  -0.1955   0.00910   0.00442  -0.0291   0.7873   0.6946
  -2.750  -0.1690   0.00923   0.00453  -0.0288   0.7864   0.7168
  -2.500  -0.1423   0.00944   0.00474  -0.0286   0.7854   0.7338
  -2.250  -0.1157   0.00966   0.00498  -0.0284   0.7844   0.7489
  -2.000  -0.0890   0.00997   0.00533  -0.0280   0.7832   0.7637
  -1.750  -0.0613   0.01027   0.00569  -0.0278   0.7819   0.7741
  -1.500  -0.0345   0.01049   0.00591  -0.0276   0.7807   0.7830
  -1.250  -0.0066   0.01080   0.00626  -0.0275   0.7796   0.7903
  -1.000   0.0206   0.01094   0.00638  -0.0275   0.7781   0.7960
  -0.750   0.0490   0.01081   0.00622  -0.0277   0.7750   0.7992
  -0.500   0.0798   0.01044   0.00574  -0.0277   0.7686   0.8014
  -0.250   0.1072   0.01033   0.00565  -0.0277   0.7636   0.8036
   0.000   0.1355   0.01021   0.00551  -0.0279   0.7598   0.8056
   0.250   0.1642   0.01017   0.00545  -0.0283   0.7578   0.8076
   0.500   0.1934   0.01008   0.00533  -0.0287   0.7556   0.8096
   0.750   0.2228   0.01003   0.00522  -0.0292   0.7534   0.8113
   1.000   0.2503   0.00999   0.00521  -0.0295   0.7507   0.8130
   1.250   0.2779   0.00988   0.00510  -0.0297   0.7462   0.8145
   1.500   0.3070   0.00965   0.00485  -0.0301   0.7413   0.8158
   1.750   0.3370   0.00950   0.00466  -0.0305   0.7373   0.8171
   2.000   0.3637   0.00941   0.00464  -0.0305   0.7321   0.8186
   2.250   0.3921   0.00927   0.00450  -0.0306   0.7261   0.8202
   2.500   0.4217   0.00914   0.00434  -0.0310   0.7209   0.8218
   2.750   0.4480   0.00906   0.00433  -0.0309   0.7145   0.8236
   3.000   0.4761   0.00894   0.00422  -0.0311   0.7081   0.8254
   3.250   0.5031   0.00885   0.00415  -0.0311   0.6995   0.8274
   3.500   0.5299   0.00872   0.00402  -0.0310   0.6872   0.8296
   3.750   0.5551   0.00863   0.00395  -0.0306   0.6682   0.8317
   4.000   0.5753   0.00856   0.00375  -0.0291   0.6095   0.8337
   4.250   0.5688   0.00950   0.00407  -0.0227   0.4856   0.8368
   4.500   0.5613   0.01045   0.00459  -0.0165   0.3927   0.8405
   4.750   0.5520   0.01119   0.00503  -0.0100   0.3222   0.8450
   5.000   0.5451   0.01222   0.00567  -0.0044   0.2420   0.8492
   5.250   0.5387   0.01339   0.00644   0.0007   0.1485   0.8535
   5.500   0.5352   0.01465   0.00726   0.0053   0.0556   0.8583
   5.750   0.5489   0.01524   0.00775   0.0071   0.0393   0.8625
   6.000   0.5655   0.01571   0.00822   0.0085   0.0354   0.8661
   6.250   0.5830   0.01609   0.00866   0.0098   0.0339   0.8697
   6.500   0.6001   0.01653   0.00914   0.0112   0.0327   0.8738
   6.750   0.6173   0.01699   0.00963   0.0124   0.0319   0.8784
   7.000   0.6323   0.01757   0.01024   0.0139   0.0308   0.8831
   7.250   0.6452   0.01821   0.01094   0.0158   0.0302   0.8880
   7.500   0.6602   0.01879   0.01156   0.0173   0.0298   0.8937
   7.750   0.6757   0.01935   0.01217   0.0187   0.0295   0.8994
   8.000   0.6907   0.01987   0.01276   0.0203   0.0289   0.9054
   8.250   0.7055   0.02047   0.01341   0.0218   0.0284   0.9126
   8.500   0.7189   0.02108   0.01409   0.0235   0.0279   0.9201
   8.750   0.7338   0.02164   0.01469   0.0250   0.0271   0.9294
   9.000   0.7473   0.02226   0.01537   0.0266   0.0264   0.9400
   9.250   0.7629   0.02302   0.01617   0.0277   0.0259   0.9526
   9.500   0.7846   0.02404   0.01722   0.0274   0.0255   0.9647
   9.750   0.8133   0.02494   0.01819   0.0258   0.0249   0.9753
  10.000   0.8437   0.02575   0.01907   0.0240   0.0244   0.9902
  10.250   0.8659   0.02654   0.01990   0.0240   0.0238   1.0000
  10.500   0.8872   0.02732   0.02071   0.0243   0.0235   1.0000
  10.750   0.9085   0.02812   0.02154   0.0245   0.0229   1.0000
  11.000   0.9297   0.02892   0.02237   0.0248   0.0225   1.0000
  11.250   0.9519   0.02981   0.02327   0.0250   0.0221   1.0000
  11.500   0.9780   0.03082   0.02429   0.0248   0.0218   1.0000
  11.750   1.0176   0.03245   0.02596   0.0231   0.0213   1.0000
  12.000   1.0307   0.03365   0.02733   0.0243   0.0211   1.0000
  12.250   1.0480   0.03516   0.02902   0.0250   0.0209   1.0000
  12.500   1.0691   0.03725   0.03130   0.0252   0.0209   1.0000
  12.750   1.0815   0.03927   0.03351   0.0263   0.0209   1.0000
  13.000   1.0930   0.04171   0.03615   0.0273   0.0210   1.0000
  13.250   1.1013   0.04459   0.03924   0.0285   0.0211   1.0000
  13.500   1.1248   0.04808   0.04283   0.0280   0.0214   1.0000
  13.750   0.9586   0.06675   0.06337   0.0418   0.0323   1.0000
  14.000   0.9424   0.07034   0.06709   0.0426   0.0320   1.0000
  14.250   0.9233   0.07450   0.07138   0.0429   0.0318   1.0000
  14.500   0.8988   0.07950   0.07652   0.0425   0.0317   1.0000
  14.750   0.8723   0.08530   0.08248   0.0410   0.0317   1.0000
  15.000   0.8262   0.09485   0.09224   0.0368   0.0319   1.0000
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