Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

WORTMANN FX 80-080 (fx80080-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: WORTMANN FX 80-080 (fx80080-il)
Reynolds number: 500,000
Max Cl/Cd: 113.19 at α=3.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx80080-il-500000.txt
Download as CSV file: xf-fx80080-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: WORTMANN FX 80-080                              
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.4616   0.07694   0.07486  -0.0388   1.0000   0.0135
  -7.750  -0.4777   0.07221   0.07020  -0.0413   1.0000   0.0137
  -7.500  -0.4827   0.06797   0.06595  -0.0434   0.9989   0.0137
  -7.250  -0.4646   0.06133   0.05922  -0.0516   0.9937   0.0143
  -7.000  -0.4419   0.05667   0.05446  -0.0575   0.9894   0.0149
  -6.750  -0.4185   0.05135   0.04900  -0.0632   0.9833   0.0153
  -6.500  -0.3917   0.04659   0.04405  -0.0682   0.9790   0.0169
  -6.250  -0.3541   0.04314   0.04028  -0.0712   0.9742   0.0208
  -6.000  -0.3269   0.03871   0.03552  -0.0741   0.9690   0.0209
  -5.000  -0.2113   0.01683   0.01167  -0.0831   0.9532   0.0166
  -4.750  -0.1753   0.01430   0.00875  -0.0848   0.9510   0.0167
  -4.500  -0.1455   0.01306   0.00734  -0.0852   0.9449   0.0178
  -4.250  -0.1112   0.01229   0.00643  -0.0867   0.9407   0.0197
  -4.000  -0.0755   0.01152   0.00554  -0.0885   0.9374   0.0207
  -3.750  -0.0501   0.01012   0.00400  -0.0881   0.9304   0.0230
  -3.500  -0.0186   0.00956   0.00339  -0.0891   0.9256   0.0274
  -3.250   0.0106   0.00918   0.00294  -0.0894   0.9201   0.0334
  -3.000   0.0380   0.00871   0.00247  -0.0894   0.9142   0.0532
  -2.750   0.0681   0.00831   0.00220  -0.0902   0.9098   0.0992
  -2.500   0.0910   0.00765   0.00204  -0.0897   0.9035   0.2411
  -2.250   0.1115   0.00644   0.00190  -0.0891   0.8981   0.5600
  -2.000   0.1343   0.00614   0.00201  -0.0879   0.8931   0.7145
  -1.750   0.1596   0.00615   0.00207  -0.0871   0.8880   0.7565
  -1.500   0.1871   0.00618   0.00208  -0.0869   0.8839   0.7785
  -1.250   0.2136   0.00625   0.00213  -0.0865   0.8796   0.7992
  -1.000   0.2389   0.00629   0.00217  -0.0858   0.8748   0.8156
  -0.750   0.2656   0.00633   0.00220  -0.0854   0.8705   0.8303
  -0.500   0.2908   0.00639   0.00227  -0.0846   0.8662   0.8469
  -0.250   0.3143   0.00643   0.00234  -0.0833   0.8610   0.8635
   0.000   0.3397   0.00645   0.00236  -0.0826   0.8561   0.8764
   0.250   0.3643   0.00645   0.00237  -0.0817   0.8501   0.8862
   0.500   0.3902   0.00645   0.00236  -0.0812   0.8438   0.8938
   0.750   0.4163   0.00644   0.00234  -0.0807   0.8374   0.8996
   1.000   0.4419   0.00641   0.00232  -0.0801   0.8298   0.9060
   1.250   0.4673   0.00638   0.00231  -0.0795   0.8216   0.9125
   1.500   0.4934   0.00635   0.00225  -0.0789   0.8126   0.9189
   1.750   0.5175   0.00629   0.00221  -0.0779   0.8014   0.9261
   2.000   0.5421   0.00623   0.00218  -0.0771   0.7900   0.9342
   2.250   0.5676   0.00618   0.00217  -0.0764   0.7780   0.9431
   2.500   0.5950   0.00614   0.00216  -0.0762   0.7656   0.9535
   2.750   0.6260   0.00612   0.00215  -0.0768   0.7487   0.9646
   3.000   0.6607   0.00614   0.00216  -0.0783   0.7271   0.9756
   3.500   0.7199   0.00636   0.00228  -0.0793   0.6585   1.0000
   3.750   0.7326   0.00693   0.00239  -0.0762   0.5512   1.0000
   4.000   0.7413   0.00805   0.00280  -0.0727   0.4025   1.0000
   4.250   0.7543   0.00915   0.00326  -0.0702   0.2699   1.0000
   4.500   0.7710   0.01008   0.00371  -0.0685   0.1708   1.0000
   4.750   0.7908   0.01078   0.00414  -0.0673   0.1114   1.0000
   5.000   0.8122   0.01136   0.00456  -0.0663   0.0781   1.0000
   5.250   0.8339   0.01193   0.00501  -0.0653   0.0559   1.0000
   5.500   0.8555   0.01252   0.00557  -0.0642   0.0406   1.0000
   5.750   0.8754   0.01331   0.00635  -0.0628   0.0305   1.0000
   6.000   0.8992   0.01367   0.00677  -0.0621   0.0263   1.0000
   6.250   0.9184   0.01453   0.00769  -0.0606   0.0217   1.0000
   6.500   0.9390   0.01527   0.00851  -0.0594   0.0193   1.0000
   6.750   0.9625   0.01562   0.00888  -0.0588   0.0159   1.0000
   7.000   0.9742   0.01773   0.01113  -0.0559   0.0131   1.0000
   7.250   0.9969   0.01831   0.01181  -0.0550   0.0122   1.0000
   7.500   1.0177   0.01930   0.01290  -0.0538   0.0108   1.0000
   7.750   1.0380   0.02048   0.01420  -0.0526   0.0099   1.0000
   8.000   1.0578   0.02191   0.01580  -0.0513   0.0093   1.0000
   8.250   1.0768   0.02383   0.01791  -0.0500   0.0089   1.0000
   8.500   1.0945   0.02624   0.02058  -0.0485   0.0087   1.0000
   8.750   1.1047   0.03026   0.02500  -0.0462   0.0082   1.0000
   9.000   1.1125   0.03322   0.02839  -0.0434   0.0077   1.0000
   9.250   1.1203   0.03582   0.03132  -0.0407   0.0076   1.0000
   9.500   1.1192   0.03947   0.03535  -0.0372   0.0076   1.0000
   9.750   1.1137   0.04308   0.03930  -0.0333   0.0076   1.0000
  10.000   1.1059   0.04603   0.04253  -0.0291   0.0073   1.0000
  10.250   1.0738   0.05085   0.04761  -0.0233   0.0078   1.0000
  10.500   1.0437   0.05901   0.05628  -0.0185   0.0095   1.0000
  10.750   1.0383   0.05783   0.05500  -0.0177   0.0077   1.0000
  11.000   0.9382   0.05301   0.05044  -0.0138   0.0081   1.0000
  11.250   0.9188   0.05836   0.05593  -0.0144   0.0081   1.0000
  11.500   0.9027   0.06367   0.06138  -0.0159   0.0082   1.0000
  11.750   0.8803   0.07069   0.06853  -0.0189   0.0082   1.0000
  12.000   0.8583   0.07854   0.07653  -0.0233   0.0083   1.0000
  12.250   0.8388   0.08716   0.08528  -0.0290   0.0084   1.0000
<< Back to WORTMANN FX 80-080 (fx80080-il)

Polar data table (+)

Polar graphs


<< Back to WORTMANN FX 80-080 (fx80080-il)