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NACA 65-209 (naca65209-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: NACA 65-209 (naca65209-il)
Reynolds number: 200,000
Max Cl/Cd: 50.43 at α=3°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca65209-il-200000-n5.txt
Download as CSV file: xf-naca65209-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 65-209                                     
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.5416   0.08764   0.08409  -0.0255   1.0000   0.0154
  -9.250  -0.5448   0.08257   0.07906  -0.0287   1.0000   0.0151
  -9.000  -0.5505   0.07682   0.07336  -0.0331   1.0000   0.0148
  -8.750  -0.5614   0.07088   0.06742  -0.0383   1.0000   0.0147
  -8.500  -0.5751   0.06643   0.06294  -0.0403   1.0000   0.0144
  -8.250  -0.5833   0.06181   0.05823  -0.0415   1.0000   0.0142
  -8.000  -0.5886   0.05715   0.05343  -0.0420   1.0000   0.0139
  -7.750  -0.5910   0.05257   0.04867  -0.0416   1.0000   0.0138
  -7.500  -0.5908   0.04819   0.04406  -0.0406   1.0000   0.0136
  -7.250  -0.5889   0.04404   0.03966  -0.0389   1.0000   0.0135
  -7.000  -0.5853   0.04020   0.03553  -0.0368   1.0000   0.0136
  -6.750  -0.5804   0.03670   0.03172  -0.0343   1.0000   0.0138
  -6.500  -0.5599   0.03236   0.02688  -0.0346   0.9955   0.0143
  -6.250  -0.5311   0.02880   0.02275  -0.0357   0.9896   0.0157
  -6.000  -0.4986   0.02686   0.02030  -0.0369   0.9848   0.0171
  -5.750  -0.4712   0.02289   0.01582  -0.0379   0.9793   0.0179
  -5.500  -0.4391   0.02099   0.01369  -0.0394   0.9755   0.0191
  -5.250  -0.4087   0.01988   0.01241  -0.0404   0.9694   0.0208
  -5.000  -0.3756   0.01879   0.01115  -0.0417   0.9651   0.0232
  -4.750  -0.3457   0.01750   0.00965  -0.0421   0.9587   0.0243
  -4.500  -0.3140   0.01643   0.00845  -0.0430   0.9535   0.0256
  -4.250  -0.2839   0.01567   0.00759  -0.0436   0.9470   0.0266
  -4.000  -0.2558   0.01446   0.00639  -0.0442   0.9404   0.0302
  -3.750  -0.2272   0.01378   0.00565  -0.0446   0.9333   0.0323
  -3.500  -0.1984   0.01320   0.00497  -0.0450   0.9263   0.0349
  -3.250  -0.1705   0.01277   0.00442  -0.0452   0.9187   0.0381
  -3.000  -0.1423   0.01229   0.00390  -0.0454   0.9116   0.0457
  -2.750  -0.1155   0.01188   0.00351  -0.0454   0.9036   0.0628
  -2.500  -0.0917   0.01062   0.00302  -0.0455   0.8965   0.2620
  -2.250  -0.0750   0.00917   0.00302  -0.0439   0.8875   0.6241
  -2.000  -0.0519   0.00906   0.00318  -0.0423   0.8807   0.7156
  -1.750  -0.0275   0.00907   0.00323  -0.0412   0.8727   0.7526
  -1.500  -0.0026   0.00910   0.00325  -0.0401   0.8662   0.7802
  -1.250   0.0231   0.00911   0.00323  -0.0394   0.8584   0.7962
  -1.000   0.0501   0.00909   0.00316  -0.0391   0.8519   0.8035
  -0.750   0.0773   0.00908   0.00309  -0.0390   0.8444   0.8120
  -0.500   0.1041   0.00907   0.00304  -0.0387   0.8382   0.8188
  -0.250   0.1311   0.00907   0.00302  -0.0385   0.8306   0.8271
   0.000   0.1578   0.00907   0.00300  -0.0381   0.8245   0.8343
   0.250   0.1845   0.00908   0.00301  -0.0379   0.8170   0.8424
   0.500   0.2112   0.00909   0.00302  -0.0375   0.8110   0.8502
   0.750   0.2375   0.00910   0.00306  -0.0372   0.8034   0.8581
   1.000   0.2643   0.00912   0.00308  -0.0369   0.7975   0.8666
   1.250   0.2902   0.00915   0.00318  -0.0364   0.7897   0.8747
   1.500   0.3168   0.00918   0.00322  -0.0361   0.7836   0.8836
   1.750   0.3426   0.00921   0.00333  -0.0356   0.7756   0.8924
   2.000   0.3690   0.00923   0.00340  -0.0351   0.7689   0.9015
   2.250   0.3950   0.00925   0.00352  -0.0347   0.7587   0.9117
   2.500   0.4199   0.00921   0.00347  -0.0336   0.7357   0.9218
   2.750   0.4438   0.00916   0.00332  -0.0323   0.6931   0.9323
   3.000   0.4670   0.00926   0.00317  -0.0308   0.6190   0.9439
   3.250   0.4892   0.00980   0.00317  -0.0296   0.4785   0.9568
   3.500   0.5042   0.01199   0.00384  -0.0288   0.1584   0.9747
   3.750   0.5323   0.01314   0.00447  -0.0299   0.0536   0.9982
   4.000   0.5557   0.01368   0.00498  -0.0294   0.0411   1.0000
   4.250   0.5787   0.01428   0.00559  -0.0289   0.0340   1.0000
   4.500   0.6021   0.01489   0.00631  -0.0283   0.0313   1.0000
   4.750   0.6253   0.01554   0.00705  -0.0277   0.0293   1.0000
   5.000   0.6479   0.01631   0.00788  -0.0270   0.0275   1.0000
   5.250   0.6703   0.01718   0.00880  -0.0263   0.0262   1.0000
   5.500   0.6931   0.01806   0.00971  -0.0257   0.0245   1.0000
   5.750   0.7146   0.01943   0.01113  -0.0250   0.0224   1.0000
   6.000   0.7382   0.02085   0.01264  -0.0244   0.0215   1.0000
   6.250   0.7631   0.02205   0.01399  -0.0240   0.0208   1.0000
   6.500   0.7880   0.02353   0.01565  -0.0235   0.0201   1.0000
   6.750   0.8126   0.02524   0.01760  -0.0230   0.0193   1.0000
   7.000   0.8361   0.02665   0.01924  -0.0224   0.0177   1.0000
   7.250   0.8584   0.02815   0.02099  -0.0218   0.0165   1.0000
   7.500   0.8792   0.03014   0.02327  -0.0210   0.0157   1.0000
   7.750   0.8980   0.03228   0.02568  -0.0201   0.0151   1.0000
   8.000   0.9141   0.03482   0.02852  -0.0190   0.0146   1.0000
   8.500   0.9322   0.04197   0.03656  -0.0153   0.0131   1.0000
   8.750   0.9374   0.04603   0.04109  -0.0131   0.0123   1.0000
   9.000   0.9359   0.05075   0.04622  -0.0108   0.0119   1.0000
   9.250   0.9301   0.05530   0.05109  -0.0086   0.0118   1.0000
   9.500   0.9193   0.05971   0.05577  -0.0065   0.0118   1.0000
   9.750   0.9025   0.06363   0.05987  -0.0042   0.0118   1.0000
  10.000   0.8839   0.06783   0.06424  -0.0034   0.0118   1.0000
  10.250   0.8644   0.07270   0.06924  -0.0043   0.0119   1.0000
  10.500   0.8440   0.07869   0.07534  -0.0071   0.0120   1.0000
  10.750   0.8251   0.08598   0.08272  -0.0120   0.0122   1.0000
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