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 082-512 AIRFOIL (fx082512-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: WORTMANN FX 082-512 AIRFOIL (fx082512-il)
Reynolds number: 1,000,000
Max Cl/Cd: 82.08 at α=5.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx082512-il-1000000-n5.txt
Download as CSV file: xf-fx082512-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: WORTMANN FX 082-512 AIRFOIL                     
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -17.250  -0.8140   0.12409   0.12169  -0.0382   1.0000   0.0051
 -17.000  -0.8462   0.11362   0.11108  -0.0431   1.0000   0.0051
 -16.750  -0.8708   0.10524   0.10258  -0.0471   1.0000   0.0051
 -16.500  -0.8912   0.09807   0.09530  -0.0506   1.0000   0.0050
 -16.250  -0.9048   0.09240   0.08954  -0.0532   1.0000   0.0050
 -16.000  -0.9124   0.08794   0.08501  -0.0551   1.0000   0.0051
 -15.750  -0.9216   0.08337   0.08036  -0.0570   1.0000   0.0051
 -15.500  -0.9273   0.07882   0.07572  -0.0596   0.9998   0.0052
 -15.250  -0.9259   0.07475   0.07157  -0.0628   0.9993   0.0052
 -15.000  -0.9247   0.07065   0.06739  -0.0661   0.9986   0.0053
 -14.750  -0.9217   0.06689   0.06355  -0.0693   0.9978   0.0053
 -14.500  -0.9224   0.06264   0.05922  -0.0729   0.9969   0.0055
 -14.250  -0.9203   0.05880   0.05530  -0.0764   0.9959   0.0056
 -14.000  -0.9151   0.05539   0.05182  -0.0798   0.9951   0.0056
 -13.750  -0.9098   0.05207   0.04842  -0.0832   0.9942   0.0057
 -13.500  -0.9055   0.04920   0.04551  -0.0853   0.9922   0.0060
 -13.250  -0.8994   0.04630   0.04255  -0.0882   0.9900   0.0061
 -13.000  -0.8902   0.04376   0.03996  -0.0911   0.9881   0.0063
 -12.750  -0.8804   0.04099   0.03713  -0.0948   0.9864   0.0065
 -12.500  -0.8795   0.03846   0.03454  -0.0963   0.9822   0.0066
 -12.250  -0.8709   0.03565   0.03168  -0.0995   0.9775   0.0067
 -12.000  -0.8504   0.03258   0.02853  -0.1053   0.9753   0.0069
 -11.750  -0.8383   0.02987   0.02575  -0.1087   0.9700   0.0071
 -11.500  -0.8156   0.02703   0.02281  -0.1143   0.9665   0.0074
 -11.250  -0.7855   0.02412   0.01980  -0.1211   0.9646   0.0076
 -11.000  -0.7500   0.02074   0.01632  -0.1296   0.9635   0.0083
 -10.750  -0.7139   0.01839   0.01387  -0.1360   0.9627   0.0089
 -10.500  -0.6800   0.01714   0.01254  -0.1397   0.9621   0.0096
 -10.250  -0.6464   0.01619   0.01151  -0.1427   0.9616   0.0101
 -10.000  -0.6225   0.01535   0.01061  -0.1434   0.9576   0.0109
  -9.750  -0.5913   0.01447   0.00968  -0.1457   0.9559   0.0121
  -9.500  -0.5596   0.01375   0.00892  -0.1477   0.9545   0.0134
  -9.250  -0.5277   0.01318   0.00827  -0.1494   0.9533   0.0146
  -9.000  -0.4949   0.01250   0.00756  -0.1515   0.9522   0.0184
  -8.750  -0.4622   0.01191   0.00694  -0.1533   0.9513   0.0227
  -8.500  -0.4289   0.01125   0.00634  -0.1554   0.9505   0.0355
  -8.250  -0.3967   0.01089   0.00599  -0.1568   0.9496   0.0431
  -8.000  -0.3641   0.01061   0.00572  -0.1582   0.9488   0.0475
  -7.750  -0.3313   0.01037   0.00545  -0.1595   0.9481   0.0500
  -7.500  -0.2980   0.01009   0.00517  -0.1610   0.9475   0.0527
  -7.250  -0.2678   0.00990   0.00497  -0.1617   0.9456   0.0549
  -7.000  -0.2391   0.00973   0.00478  -0.1621   0.9430   0.0565
  -6.750  -0.2088   0.00961   0.00463  -0.1627   0.9410   0.0579
  -6.500  -0.1760   0.00932   0.00430  -0.1641   0.9395   0.0605
  -6.250  -0.1421   0.00903   0.00399  -0.1656   0.9382   0.0625
  -6.000  -0.1078   0.00878   0.00370  -0.1672   0.9369   0.0637
  -5.750  -0.0729   0.00854   0.00344  -0.1689   0.9356   0.0650
  -5.500  -0.0374   0.00832   0.00318  -0.1708   0.9344   0.0662
  -5.250  -0.0011   0.00812   0.00295  -0.1727   0.9331   0.0674
  -5.000   0.0358   0.00793   0.00274  -0.1748   0.9319   0.0686
  -4.750   0.0669   0.00780   0.00259  -0.1756   0.9292   0.0696
  -4.500   0.0968   0.00769   0.00246  -0.1761   0.9258   0.0703
  -4.250   0.1323   0.00752   0.00226  -0.1779   0.9223   0.0719
  -4.000   0.1746   0.00733   0.00205  -0.1812   0.9177   0.0746
  -3.500   0.2423   0.00710   0.00181  -0.1839   0.9100   0.0800
  -3.250   0.2766   0.00697   0.00169  -0.1854   0.9040   0.0866
  -3.000   0.3235   0.00596   0.00118  -0.1907   0.8995   0.2581
  -2.750   0.3533   0.00591   0.00116  -0.1911   0.8923   0.2730
  -2.500   0.3871   0.00591   0.00114  -0.1924   0.8829   0.2805
  -2.250   0.4159   0.00591   0.00114  -0.1925   0.8733   0.2872
  -2.000   0.4463   0.00594   0.00112  -0.1930   0.8617   0.2908
  -1.750   0.4744   0.00599   0.00111  -0.1929   0.8397   0.2942
  -1.500   0.4999   0.00612   0.00112  -0.1922   0.8092   0.2981
  -1.250   0.5209   0.00636   0.00116  -0.1905   0.7663   0.3011
  -1.000   0.5375   0.00676   0.00126  -0.1878   0.7031   0.3034
  -0.750   0.5518   0.00737   0.00144  -0.1848   0.6086   0.3046
  -0.500   0.5677   0.00818   0.00170  -0.1824   0.4855   0.3063
  -0.250   0.5840   0.00919   0.00206  -0.1802   0.3316   0.3082
   0.000   0.6057   0.00977   0.00230  -0.1790   0.2463   0.3102
   0.250   0.6238   0.01073   0.00270  -0.1772   0.0892   0.3120
   0.500   0.6503   0.01088   0.00282  -0.1769   0.0821   0.3143
   0.750   0.6768   0.01101   0.00294  -0.1765   0.0785   0.3168
   1.000   0.7030   0.01117   0.00307  -0.1761   0.0751   0.3190
   1.250   0.7298   0.01128   0.00320  -0.1758   0.0738   0.3216
   1.500   0.7565   0.01139   0.00333  -0.1755   0.0726   0.3230
   1.750   0.7830   0.01152   0.00347  -0.1751   0.0713   0.3244
   2.000   0.8093   0.01166   0.00363  -0.1747   0.0700   0.3258
   2.250   0.8355   0.01181   0.00378  -0.1743   0.0687   0.3272
   2.500   0.8615   0.01197   0.00395  -0.1739   0.0672   0.3286
   2.750   0.8872   0.01215   0.00414  -0.1734   0.0653   0.3299
   3.000   0.9127   0.01236   0.00437  -0.1728   0.0635   0.3312
   3.250   0.9383   0.01253   0.00456  -0.1722   0.0621   0.3325
   3.500   0.9645   0.01264   0.00469  -0.1718   0.0606   0.3340
   3.750   0.9905   0.01277   0.00484  -0.1714   0.0584   0.3360
   4.000   1.0160   0.01293   0.00502  -0.1709   0.0562   0.3377
   4.250   1.0412   0.01313   0.00522  -0.1703   0.0537   0.3394
   4.500   1.0666   0.01329   0.00540  -0.1697   0.0517   0.3411
   4.750   1.0918   0.01346   0.00558  -0.1691   0.0482   0.3429
   5.000   1.1166   0.01366   0.00578  -0.1684   0.0444   0.3446
   5.250   1.1409   0.01390   0.00598  -0.1677   0.0367   0.3461
   5.500   1.1636   0.01428   0.00629  -0.1667   0.0254   0.3475
   5.750   1.1862   0.01464   0.00664  -0.1656   0.0192   0.3489
   6.000   1.2090   0.01494   0.00699  -0.1645   0.0170   0.3511
   6.250   1.2310   0.01529   0.00737  -0.1633   0.0151   0.3532
   6.500   1.2522   0.01569   0.00779  -0.1619   0.0132   0.3553
   6.750   1.2739   0.01604   0.00818  -0.1607   0.0122   0.3576
   7.000   1.2954   0.01640   0.00857  -0.1594   0.0114   0.3600
   7.250   1.3163   0.01681   0.00901  -0.1580   0.0106   0.3621
   7.500   1.3365   0.01727   0.00948  -0.1565   0.0098   0.3639
   7.750   1.3563   0.01777   0.01003  -0.1549   0.0091   0.3665
   8.000   1.3768   0.01818   0.01052  -0.1535   0.0088   0.3692
   8.250   1.3968   0.01863   0.01103  -0.1520   0.0084   0.3719
   8.500   1.4165   0.01911   0.01156  -0.1505   0.0080   0.3747
   8.750   1.4359   0.01962   0.01212  -0.1489   0.0077   0.3774
   9.000   1.4547   0.02017   0.01270  -0.1473   0.0073   0.3798
   9.250   1.4727   0.02079   0.01337  -0.1455   0.0069   0.3830
   9.500   1.4899   0.02148   0.01413  -0.1437   0.0065   0.3867
   9.750   1.5081   0.02204   0.01476  -0.1420   0.0064   0.3908
  10.000   1.5258   0.02266   0.01545  -0.1403   0.0062   0.3951
  10.250   1.5431   0.02332   0.01621  -0.1385   0.0060   0.4002
  10.500   1.5597   0.02402   0.01698  -0.1367   0.0058   0.4066
  10.750   1.5758   0.02475   0.01779  -0.1348   0.0056   0.4128
  11.000   1.5919   0.02551   0.01864  -0.1330   0.0054   0.4209
  11.500   1.6219   0.02720   0.02051  -0.1291   0.0051   0.4438
  11.750   1.6361   0.02815   0.02157  -0.1272   0.0050   0.4629
  12.000   1.6490   0.02925   0.02281  -0.1252   0.0048   0.4927
  12.250   1.6605   0.03055   0.02431  -0.1231   0.0046   0.5452
  12.500   1.6753   0.03167   0.02569  -0.1217   0.0046   0.6482
  13.000   1.6945   0.03368   0.02839  -0.1170   0.0045   1.0000
  13.250   1.7040   0.03504   0.02985  -0.1149   0.0044   1.0000
  13.500   1.7124   0.03649   0.03140  -0.1128   0.0043   1.0000
  13.750   1.7193   0.03812   0.03313  -0.1106   0.0043   1.0000
  14.000   1.7263   0.03976   0.03488  -0.1085   0.0042   1.0000
  14.250   1.7321   0.04155   0.03677  -0.1065   0.0041   1.0000
  14.500   1.7363   0.04353   0.03885  -0.1045   0.0040   1.0000
  14.750   1.7394   0.04567   0.04112  -0.1026   0.0040   1.0000
  15.000   1.7431   0.04780   0.04335  -0.1009   0.0039   1.0000
  15.250   1.7439   0.05032   0.04599  -0.0993   0.0038   1.0000
  15.500   1.7444   0.05295   0.04873  -0.0979   0.0038   1.0000
  15.750   1.7431   0.05589   0.05180  -0.0966   0.0037   1.0000
  16.000   1.7430   0.05880   0.05481  -0.0957   0.0036   1.0000
  16.250   1.7404   0.06215   0.05828  -0.0950   0.0036   1.0000
  16.500   1.7348   0.06604   0.06230  -0.0946   0.0036   1.0000
  16.750   1.7288   0.07018   0.06657  -0.0946   0.0035   1.0000
  17.000   1.7195   0.07502   0.07156  -0.0951   0.0035   1.0000
  17.250   1.7084   0.08042   0.07711  -0.0962   0.0035   1.0000
  17.500   1.6972   0.08610   0.08294  -0.0978   0.0034   1.0000
  17.750   1.6804   0.09310   0.09011  -0.1005   0.0034   1.0000
  18.000   1.6607   0.10112   0.09831  -0.1042   0.0034   1.0000
  18.250   1.6391   0.11006   0.10743  -0.1089   0.0034   1.0000
  18.500   1.6114   0.12092   0.11850  -0.1155   0.0034   1.0000
  18.750   1.5729   0.13516   0.13299  -0.1250   0.0034   1.0000
<< Back to WORTMANN FX 082-512 AIRFOIL (fx082512-il)

Polar data table (+)

Polar graphs


<< Back to WORTMANN FX 082-512 AIRFOIL (fx082512-il)