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BELL/WORTMANN FX 69-H-083 AIRFOIL (fx69h083-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: BELL/WORTMANN FX 69-H-083 AIRFOIL (fx69h083-il)
Reynolds number: 500,000
Max Cl/Cd: 90.08 at α=4.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx69h083-il-500000.txt
Download as CSV file: xf-fx69h083-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: BELL/WORTMANN FX 69-H-083 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
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.5167   0.10589   0.10382   0.0026   1.0000   0.0107
  -9.000  -0.5249   0.09924   0.09723   0.0005   1.0000   0.0112
  -8.750  -0.5216   0.09563   0.09363  -0.0008   1.0000   0.0114
  -8.500  -0.5171   0.09222   0.09024  -0.0022   1.0000   0.0117
  -8.250  -0.5132   0.08857   0.08659  -0.0045   1.0000   0.0120
  -8.000  -0.5102   0.08454   0.08258  -0.0078   1.0000   0.0123
  -7.750  -0.5073   0.08012   0.07818  -0.0126   1.0000   0.0126
  -7.500  -0.4992   0.07529   0.07334  -0.0180   1.0000   0.0130
  -7.250  -0.4886   0.07032   0.06834  -0.0231   1.0000   0.0135
  -7.000  -0.4757   0.06531   0.06327  -0.0278   1.0000   0.0141
  -6.750  -0.3827   0.04642   0.04435  -0.0398   0.9709   0.0170
  -6.500  -0.3738   0.04153   0.03931  -0.0410   0.9578   0.0170
  -6.250  -0.3660   0.03708   0.03469  -0.0410   0.9460   0.0170
  -6.000  -0.3569   0.03278   0.03020  -0.0405   0.9357   0.0171
  -5.750  -0.3466   0.02868   0.02587  -0.0396   0.9269   0.0171
  -5.500  -0.3487   0.02003   0.01686  -0.0390   0.9180   0.0182
  -5.250  -0.3335   0.01735   0.01401  -0.0382   0.9102   0.0188
  -5.000  -0.3166   0.01512   0.01159  -0.0373   0.9027   0.0197
  -4.750  -0.2974   0.01296   0.00920  -0.0364   0.8951   0.0208
  -4.500  -0.2775   0.01090   0.00684  -0.0351   0.8884   0.0226
  -4.250  -0.2485   0.01127   0.00690  -0.0339   0.8800   0.0266
  -4.000  -0.2411   0.01753   0.01196  -0.0316   0.8901   0.0178
  -3.750  -0.2171   0.01576   0.01000  -0.0310   0.8828   0.0199
  -3.500  -0.1915   0.01433   0.00835  -0.0302   0.8759   0.0205
  -3.250  -0.1652   0.01303   0.00687  -0.0294   0.8686   0.0213
  -3.000  -0.1396   0.01213   0.00584  -0.0287   0.8613   0.0225
  -2.750  -0.1132   0.01150   0.00514  -0.0282   0.8527   0.0244
  -2.500  -0.0874   0.01096   0.00448  -0.0276   0.8447   0.0259
  -2.250  -0.0613   0.01040   0.00383  -0.0270   0.8351   0.0268
  -2.000  -0.0360   0.00961   0.00293  -0.0264   0.8256   0.0296
  -1.750  -0.0095   0.00929   0.00254  -0.0260   0.8171   0.0338
  -1.500   0.0178   0.00898   0.00216  -0.0257   0.8082   0.0424
  -1.250   0.0417   0.00794   0.00188  -0.0254   0.7998   0.2604
  -1.000   0.0588   0.00633   0.00170  -0.0238   0.7916   0.6840
  -0.750   0.0798   0.00574   0.00187  -0.0212   0.7826   0.9376
  -0.500   0.1526   0.00602   0.00202  -0.0303   0.7754   0.9932
  -0.250   0.1986   0.00605   0.00194  -0.0344   0.7654   1.0000
   0.000   0.2256   0.00604   0.00184  -0.0343   0.7539   1.0000
   0.250   0.2526   0.00604   0.00176  -0.0342   0.7416   1.0000
   0.500   0.2795   0.00605   0.00168  -0.0341   0.7289   1.0000
   0.750   0.3063   0.00607   0.00162  -0.0339   0.7159   1.0000
   1.000   0.3329   0.00609   0.00157  -0.0338   0.7020   1.0000
   1.250   0.3595   0.00613   0.00153  -0.0336   0.6859   1.0000
   1.500   0.3859   0.00619   0.00151  -0.0333   0.6689   1.0000
   1.750   0.4124   0.00626   0.00150  -0.0332   0.6535   1.0000
   2.000   0.4390   0.00633   0.00152  -0.0330   0.6393   1.0000
   2.250   0.4654   0.00641   0.00155  -0.0328   0.6248   1.0000
   2.500   0.4918   0.00649   0.00161  -0.0326   0.6100   1.0000
   2.750   0.5180   0.00659   0.00166  -0.0324   0.5949   1.0000
   3.000   0.5442   0.00670   0.00174  -0.0321   0.5791   1.0000
   3.250   0.5702   0.00683   0.00182  -0.0319   0.5620   1.0000
   3.500   0.5961   0.00697   0.00194  -0.0316   0.5439   1.0000
   3.750   0.6219   0.00712   0.00205  -0.0313   0.5218   1.0000
   4.000   0.6475   0.00730   0.00218  -0.0310   0.4975   1.0000
   4.250   0.6729   0.00751   0.00233  -0.0307   0.4744   1.0000
   4.500   0.6981   0.00775   0.00250  -0.0304   0.4473   1.0000
   4.750   0.7222   0.00815   0.00274  -0.0299   0.3963   1.0000
   5.000   0.7455   0.00866   0.00301  -0.0294   0.3396   1.0000
   5.250   0.7674   0.00940   0.00338  -0.0288   0.2580   1.0000
   5.500   0.7865   0.01059   0.00399  -0.0280   0.1476   1.0000
   5.750   0.8071   0.01154   0.00462  -0.0273   0.0771   1.0000
   6.000   0.8263   0.01279   0.00558  -0.0261   0.0200   1.0000
   6.250   0.8483   0.01359   0.00648  -0.0252   0.0153   1.0000
   6.500   0.8708   0.01426   0.00725  -0.0244   0.0139   1.0000
   6.750   0.8924   0.01506   0.00815  -0.0235   0.0127   1.0000
   7.000   0.9126   0.01601   0.00919  -0.0224   0.0117   1.0000
   7.250   0.9312   0.01720   0.01047  -0.0211   0.0111   1.0000
   7.500   0.9487   0.01859   0.01197  -0.0196   0.0107   1.0000
   7.750   0.9665   0.02010   0.01361  -0.0182   0.0106   1.0000
   8.000   0.9828   0.02243   0.01607  -0.0166   0.0101   1.0000
   8.250   1.0008   0.02490   0.01875  -0.0153   0.0095   1.0000
   8.500   1.0204   0.02672   0.02078  -0.0142   0.0094   1.0000
   8.750   1.0382   0.02897   0.02327  -0.0129   0.0093   1.0000
   9.000   1.0519   0.03225   0.02687  -0.0112   0.0093   1.0000
  13.250   0.6980   0.12360   0.12155  -0.0146   0.0183   1.0000
  13.500   0.6843   0.12901   0.12696  -0.0167   0.0182   1.0000
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