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NACA 63-209 (naca63209-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: NACA 63-209 (naca63209-il)
Reynolds number: 50,000
Max Cl/Cd: 32.06 at α=5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-naca63209-il-50000.txt
Download as CSV file: xf-naca63209-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 63-209                                     
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.5079   0.10329   0.09637   0.0064   1.0000   0.3271
  -8.500  -0.5089   0.10069   0.09383   0.0065   1.0000   0.3446
  -8.250  -0.5107   0.09802   0.09124   0.0068   1.0000   0.3611
  -7.750  -0.4950   0.09171   0.08499   0.0087   1.0000   0.4026
  -7.500  -0.4697   0.08702   0.08026   0.0096   1.0000   0.4230
  -7.250  -0.4628   0.08385   0.07710   0.0102   1.0000   0.4404
  -7.000  -0.4594   0.08058   0.07388   0.0102   1.0000   0.4501
  -6.750  -0.5599   0.06465   0.05826  -0.0248   1.0000   0.2287
  -6.500  -0.5620   0.05330   0.04609  -0.0361   1.0000   0.1565
  -6.250  -0.5495   0.04736   0.03921  -0.0383   1.0000   0.1332
  -6.000  -0.5316   0.04293   0.03444  -0.0381   1.0000   0.1252
  -5.750  -0.5118   0.03960   0.03020  -0.0377   1.0000   0.1199
  -5.500  -0.4911   0.03672   0.02680  -0.0370   1.0000   0.1206
  -5.250  -0.4690   0.03372   0.02346  -0.0362   1.0000   0.1211
  -5.000  -0.4454   0.03109   0.02047  -0.0351   1.0000   0.1214
  -4.750  -0.4218   0.02869   0.01793  -0.0340   1.0000   0.1238
  -4.500  -0.3986   0.02693   0.01594  -0.0328   1.0000   0.1324
  -4.250  -0.3757   0.02513   0.01417  -0.0313   1.0000   0.1423
  -4.000  -0.3530   0.02354   0.01257  -0.0294   1.0000   0.1531
  -3.750  -0.3325   0.02212   0.01122  -0.0277   1.0000   0.1775
  -3.500  -0.3138   0.02025   0.00978  -0.0261   1.0000   0.2229
  -3.250  -0.3203   0.01758   0.01002  -0.0174   1.0000   0.6681
  -3.000  -0.1722   0.02101   0.01240  -0.0165   1.0000   0.9602
  -2.750  -0.0732   0.01959   0.01025  -0.0315   1.0000   0.9939
  -2.500  -0.0471   0.01891   0.00939  -0.0336   1.0000   1.0000
  -2.250  -0.0415   0.01853   0.00897  -0.0318   1.0000   1.0000
  -2.000  -0.0404   0.01824   0.00867  -0.0292   1.0000   1.0000
  -1.750  -0.0449   0.01802   0.00845  -0.0258   1.0000   1.0000
  -1.500  -0.0557   0.01785   0.00828  -0.0214   1.0000   1.0000
  -1.250  -0.0703   0.01766   0.00810  -0.0165   1.0000   1.0000
  -1.000  -0.0844   0.01745   0.00786  -0.0116   1.0000   1.0000
  -0.750  -0.0891   0.01730   0.00760  -0.0082   1.0000   1.0000
  -0.500  -0.0796   0.01731   0.00747  -0.0070   1.0000   1.0000
  -0.250  -0.0634   0.01745   0.00746  -0.0067   1.0000   1.0000
   0.000  -0.0446   0.01766   0.00753  -0.0068   1.0000   1.0000
   0.250  -0.0249   0.01794   0.00769  -0.0069   1.0000   1.0000
   0.500  -0.0047   0.01828   0.00791  -0.0072   1.0000   1.0000
   0.750   0.0156   0.01867   0.00822  -0.0074   1.0000   1.0000
   1.000   0.0358   0.01911   0.00858  -0.0077   1.0000   1.0000
   1.250   0.0558   0.01960   0.00902  -0.0079   1.0000   1.0000
   1.500   0.0757   0.02013   0.00952  -0.0082   1.0000   1.0000
   1.750   0.0953   0.02071   0.01008  -0.0085   1.0000   1.0000
   2.000   0.1148   0.02134   0.01070  -0.0088   1.0000   1.0000
   2.250   0.1420   0.02218   0.01157  -0.0107   0.9960   1.0000
   2.500   0.1905   0.02348   0.01296  -0.0164   0.9826   1.0000
   2.750   0.2353   0.02464   0.01426  -0.0213   0.9680   1.0000
   3.000   0.2782   0.02575   0.01551  -0.0257   0.9525   1.0000
   3.250   0.3194   0.02682   0.01676  -0.0297   0.9361   1.0000
   3.500   0.3617   0.02787   0.01806  -0.0335   0.9184   1.0000
   3.750   0.4110   0.02891   0.01939  -0.0382   0.8993   1.0000
   4.000   0.4486   0.02975   0.02051  -0.0406   0.8771   1.0000
   4.250   0.4991   0.03036   0.02158  -0.0442   0.8513   1.0000
   4.500   0.6241   0.02524   0.01753  -0.0465   0.7653   1.0000
   4.750   0.6596   0.02132   0.01392  -0.0369   0.6814   1.0000
   5.000   0.6544   0.02041   0.01132  -0.0232   0.3299   1.0000
   5.250   0.6582   0.02424   0.01342  -0.0201   0.1914   1.0000
   5.500   0.6819   0.02647   0.01542  -0.0187   0.1570   1.0000
   5.750   0.7108   0.02870   0.01738  -0.0182   0.1349   1.0000
   6.000   0.7436   0.03102   0.01982  -0.0178   0.1241   1.0000
   6.250   0.7739   0.03366   0.02275  -0.0173   0.1177   1.0000
   6.500   0.8006   0.03637   0.02553  -0.0169   0.1098   1.0000
   6.750   0.8263   0.03980   0.02930  -0.0163   0.1081   1.0000
   7.000   0.8497   0.04341   0.03335  -0.0154   0.1083   1.0000
   7.250   0.8675   0.04667   0.03749  -0.0138   0.1112   1.0000
   7.500   0.8800   0.05109   0.04272  -0.0126   0.1157   1.0000
   7.750   0.8909   0.05565   0.04774  -0.0117   0.1185   1.0000
   8.000   0.9018   0.06043   0.05281  -0.0112   0.1207   1.0000
   8.250   0.8937   0.06601   0.05913  -0.0109   0.1307   1.0000
   8.500   0.8813   0.07236   0.06591  -0.0119   0.1426   1.0000
   8.750   0.7885   0.07070   0.06480  -0.0084   0.1520   1.0000
   9.000   0.7327   0.07835   0.07247  -0.0124   0.1570   1.0000
   9.250   0.6935   0.08862   0.08269  -0.0199   0.1694   1.0000
   9.500   0.7208   0.11609   0.10951  -0.0542   0.3473   1.0000
   9.750   0.7150   0.11968   0.11304  -0.0552   0.3368   1.0000
  10.000   0.7410   0.12587   0.11935  -0.0551   0.3315   1.0000
  10.250   0.7344   0.12875   0.12217  -0.0560   0.3187   1.0000
  10.500   0.5987   0.12717   0.12101  -0.0455   0.3067   1.0000
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