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 77-080 (fx77080-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: WORTMANN FX 77-080 (fx77080-il)
Reynolds number: 500,000
Max Cl/Cd: 58.57 at α=6.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx77080-il-500000-n5.txt
Download as CSV file: xf-fx77080-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: WORTMANN FX 77-080                              
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -15.000  -0.9062   0.11977   0.11722   0.0185   1.0000   0.0082
 -14.750  -0.9553   0.10472   0.10208   0.0106   1.0000   0.0082
 -14.500  -0.9995   0.09138   0.08863   0.0032   1.0000   0.0081
 -14.250  -1.0450   0.07803   0.07516  -0.0046   1.0000   0.0079
 -14.000  -1.0719   0.06774   0.06474  -0.0114   1.0000   0.0077
 -13.750  -1.0974   0.05687   0.05365  -0.0202   1.0000   0.0078
 -13.500  -1.1197   0.04809   0.04463  -0.0279   1.0000   0.0077
 -13.250  -1.1346   0.04255   0.03887  -0.0317   1.0000   0.0077
 -13.000  -1.1438   0.03893   0.03505  -0.0325   1.0000   0.0078
 -12.750  -1.1478   0.03639   0.03232  -0.0317   1.0000   0.0079
 -12.500  -1.1535   0.03404   0.02977  -0.0295   1.0000   0.0079
 -12.250  -1.1522   0.03233   0.02788  -0.0271   1.0000   0.0081
 -12.000  -1.1463   0.03062   0.02597  -0.0252   1.0000   0.0082
 -11.750  -1.1367   0.02914   0.02432  -0.0235   1.0000   0.0083
 -11.500  -1.1299   0.02723   0.02221  -0.0214   1.0000   0.0084
 -11.250  -1.1191   0.02569   0.02053  -0.0196   1.0000   0.0087
 -11.000  -1.1046   0.02449   0.01919  -0.0182   1.0000   0.0089
 -10.750  -1.0878   0.02352   0.01811  -0.0169   1.0000   0.0091
 -10.500  -1.0704   0.02256   0.01703  -0.0156   1.0000   0.0094
 -10.250  -1.0523   0.02166   0.01603  -0.0143   1.0000   0.0097
 -10.000  -1.0334   0.02083   0.01509  -0.0131   1.0000   0.0101
  -9.750  -1.0137   0.02008   0.01423  -0.0120   1.0000   0.0105
  -9.500  -0.9935   0.01936   0.01339  -0.0108   1.0000   0.0111
  -9.250  -0.9732   0.01864   0.01254  -0.0097   1.0000   0.0114
  -9.000  -0.9547   0.01768   0.01149  -0.0083   1.0000   0.0120
  -8.750  -0.9341   0.01699   0.01074  -0.0071   1.0000   0.0127
  -8.500  -0.9130   0.01636   0.01004  -0.0060   1.0000   0.0132
  -8.250  -0.8913   0.01581   0.00942  -0.0050   1.0000   0.0139
  -8.000  -0.8692   0.01531   0.00885  -0.0040   1.0000   0.0148
  -7.750  -0.8471   0.01482   0.00827  -0.0029   1.0000   0.0155
  -7.500  -0.8257   0.01424   0.00763  -0.0017   1.0000   0.0165
  -7.250  -0.8036   0.01377   0.00714  -0.0007   1.0000   0.0180
  -7.000  -0.7809   0.01341   0.00674   0.0003   1.0000   0.0195
  -6.750  -0.7581   0.01305   0.00633   0.0013   1.0000   0.0209
  -6.500  -0.7363   0.01258   0.00582   0.0025   1.0000   0.0229
  -6.250  -0.7140   0.01220   0.00543   0.0036   1.0000   0.0252
  -6.000  -0.6913   0.01190   0.00509   0.0047   1.0000   0.0275
  -5.750  -0.6692   0.01153   0.00471   0.0058   1.0000   0.0307
  -5.500  -0.6470   0.01120   0.00437   0.0070   1.0000   0.0344
  -5.250  -0.6246   0.01092   0.00408   0.0081   1.0000   0.0383
  -5.000  -0.6027   0.01060   0.00379   0.0093   1.0000   0.0456
  -4.750  -0.5809   0.01030   0.00353   0.0106   1.0000   0.0555
  -4.500  -0.5592   0.01001   0.00329   0.0118   1.0000   0.0689
  -4.250  -0.5321   0.00972   0.00308   0.0118   0.9990   0.0861
  -4.000  -0.4997   0.00945   0.00289   0.0107   0.9956   0.1042
  -3.750  -0.4671   0.00922   0.00272   0.0096   0.9925   0.1199
  -3.500  -0.4336   0.00903   0.00255   0.0084   0.9898   0.1324
  -3.250  -0.4014   0.00883   0.00240   0.0074   0.9857   0.1453
  -3.000  -0.3663   0.00859   0.00224   0.0058   0.9814   0.1642
  -2.750  -0.3332   0.00834   0.00208   0.0047   0.9749   0.1867
  -2.500  -0.3011   0.00807   0.00194   0.0038   0.9691   0.2179
  -2.250  -0.2681   0.00780   0.00181   0.0026   0.9630   0.2528
  -2.000  -0.2329   0.00751   0.00168   0.0010   0.9555   0.2953
  -1.750  -0.1959   0.00722   0.00157  -0.0011   0.9467   0.3417
  -1.500  -0.1604   0.00696   0.00146  -0.0027   0.9335   0.3878
  -1.250  -0.1250   0.00668   0.00136  -0.0043   0.9150   0.4435
  -1.000  -0.0917   0.00644   0.00125  -0.0053   0.8780   0.4997
  -0.750  -0.0647   0.00631   0.00116  -0.0049   0.8336   0.5522
  -0.500  -0.0420   0.00620   0.00110  -0.0035   0.7911   0.6071
  -0.250  -0.0205   0.00616   0.00107  -0.0019   0.7470   0.6528
   0.000   0.0002   0.00616   0.00105   0.0000   0.6992   0.6965
   0.250   0.0204   0.00618   0.00106   0.0019   0.6493   0.7443
   0.500   0.0415   0.00624   0.00110   0.0036   0.5993   0.7900
   0.750   0.0645   0.00633   0.00116   0.0049   0.5482   0.8320
   1.000   0.0918   0.00645   0.00125   0.0053   0.4981   0.8794
   1.250   0.1254   0.00666   0.00136   0.0043   0.4465   0.9162
   1.500   0.1605   0.00696   0.00146   0.0027   0.3895   0.9335
   1.750   0.1955   0.00722   0.00157   0.0012   0.3422   0.9465
   2.000   0.2329   0.00753   0.00169  -0.0010   0.2918   0.9556
   2.250   0.2683   0.00780   0.00181  -0.0026   0.2527   0.9631
   2.500   0.3012   0.00806   0.00194  -0.0038   0.2183   0.9692
   2.750   0.3333   0.00832   0.00208  -0.0047   0.1892   0.9749
   3.000   0.3662   0.00859   0.00224  -0.0058   0.1654   0.9813
   3.250   0.4012   0.00882   0.00240  -0.0074   0.1467   0.9856
   3.500   0.4337   0.00902   0.00255  -0.0084   0.1330   0.9899
   3.750   0.4671   0.00923   0.00272  -0.0097   0.1183   0.9925
   4.000   0.4995   0.00946   0.00289  -0.0107   0.1030   0.9956
   4.250   0.5320   0.00971   0.00308  -0.0118   0.0866   0.9989
   4.500   0.5592   0.01001   0.00329  -0.0118   0.0690   1.0000
   4.750   0.5809   0.01029   0.00353  -0.0105   0.0561   1.0000
   5.000   0.6027   0.01060   0.00379  -0.0093   0.0460   1.0000
   5.250   0.6246   0.01091   0.00407  -0.0081   0.0387   1.0000
   5.500   0.6470   0.01120   0.00437  -0.0070   0.0345   1.0000
   5.750   0.6692   0.01153   0.00471  -0.0058   0.0306   1.0000
   6.000   0.6914   0.01189   0.00508  -0.0047   0.0274   1.0000
   6.250   0.7140   0.01219   0.00542  -0.0036   0.0249   1.0000
   6.500   0.7363   0.01258   0.00581  -0.0025   0.0226   1.0000
   6.750   0.7582   0.01303   0.00631  -0.0013   0.0208   1.0000
   7.000   0.7809   0.01339   0.00673  -0.0003   0.0193   1.0000
   7.250   0.8035   0.01378   0.00716   0.0007   0.0179   1.0000
   7.500   0.8255   0.01426   0.00765   0.0018   0.0165   1.0000
   7.750   0.8470   0.01484   0.00829   0.0029   0.0155   1.0000
   8.000   0.8691   0.01533   0.00886   0.0040   0.0146   1.0000
   8.250   0.8909   0.01587   0.00949   0.0051   0.0139   1.0000
   8.500   0.9127   0.01641   0.01009   0.0061   0.0132   1.0000
   8.750   0.9341   0.01700   0.01074   0.0071   0.0126   1.0000
   9.000   0.9544   0.01773   0.01153   0.0083   0.0120   1.0000
   9.250   0.9731   0.01867   0.01257   0.0097   0.0114   1.0000
   9.500   0.9942   0.01927   0.01330   0.0107   0.0110   1.0000
   9.750   1.0142   0.02002   0.01416   0.0119   0.0105   1.0000
  10.000   1.0333   0.02085   0.01511   0.0131   0.0101   1.0000
  10.250   1.0527   0.02163   0.01599   0.0143   0.0097   1.0000
  10.500   1.0710   0.02251   0.01698   0.0155   0.0094   1.0000
  10.750   1.0884   0.02346   0.01804   0.0168   0.0091   1.0000
  11.000   1.1052   0.02443   0.01912   0.0181   0.0088   1.0000
  11.250   1.1186   0.02576   0.02059   0.0197   0.0085   1.0000
  11.500   1.1284   0.02743   0.02242   0.0215   0.0084   1.0000
  11.750   1.1393   0.02890   0.02406   0.0232   0.0082   1.0000
  12.000   1.1472   0.03057   0.02593   0.0251   0.0081   1.0000
  12.250   1.1538   0.03223   0.02777   0.0269   0.0081   1.0000
  12.500   1.1516   0.03426   0.03000   0.0296   0.0079   1.0000
  12.750   1.1513   0.03618   0.03212   0.0314   0.0077   1.0000
  13.000   1.1416   0.03926   0.03539   0.0323   0.0078   1.0000
  13.250   1.1314   0.04309   0.03942   0.0312   0.0078   1.0000
  13.500   1.1243   0.04755   0.04409   0.0281   0.0076   1.0000
  13.750   1.0987   0.05690   0.05368   0.0200   0.0078   1.0000
  14.000   1.0712   0.06815   0.06514   0.0109   0.0078   1.0000
  14.250   1.0373   0.07995   0.07710   0.0031   0.0079   1.0000
  14.500   1.0026   0.09140   0.08866  -0.0036   0.0079   1.0000
  14.750   0.9568   0.10490   0.10226  -0.0110   0.0081   1.0000
<< Back to WORTMANN FX 77-080 (fx77080-il)

Polar data table (+)

Polar graphs


<< Back to WORTMANN FX 77-080 (fx77080-il)