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 3 AIRFOIL (fx3-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: WORTMANN FX 3 AIRFOIL (fx3-il)
Reynolds number: 1,000,000
Max Cl/Cd: 58.15 at α=3.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx3-il-1000000-n5.txt
Download as CSV file: xf-fx3-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: WORTMANN FX 3 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
  ------ -------- --------- --------- -------- -------- --------
 -19.750  -0.8174   0.08386   0.07972  -0.1217   0.7922   0.0058
 -19.500  -0.8366   0.07733   0.07306  -0.1251   0.7922   0.0059
 -19.250  -0.8498   0.07193   0.06753  -0.1279   0.7921   0.0059
 -19.000  -0.8591   0.06731   0.06279  -0.1302   0.7921   0.0059
 -18.750  -0.8652   0.06330   0.05868  -0.1320   0.7921   0.0060
 -18.500  -0.8688   0.05976   0.05503  -0.1335   0.7920   0.0060
 -18.250  -0.8697   0.05663   0.05181  -0.1347   0.7920   0.0061
 -18.000  -0.8690   0.05381   0.04889  -0.1357   0.7920   0.0062
 -17.750  -0.8667   0.05125   0.04624  -0.1366   0.7919   0.0062
 -17.500  -0.8626   0.04895   0.04386  -0.1373   0.7919   0.0063
 -17.250  -0.8570   0.04687   0.04170  -0.1378   0.7918   0.0064
 -17.000  -0.8504   0.04495   0.03969  -0.1383   0.7918   0.0064
 -16.750  -0.8466   0.04284   0.03750  -0.1385   0.7917   0.0066
 -16.500  -0.8402   0.04104   0.03563  -0.1387   0.7917   0.0067
 -16.250  -0.8316   0.03946   0.03400  -0.1388   0.7916   0.0069
 -16.000  -0.8218   0.03804   0.03252  -0.1389   0.7916   0.0070
 -15.750  -0.8107   0.03677   0.03119  -0.1389   0.7915   0.0072
 -15.500  -0.7985   0.03559   0.02997  -0.1389   0.7915   0.0074
 -15.250  -0.7858   0.03447   0.02880  -0.1390   0.7915   0.0076
 -15.000  -0.7720   0.03346   0.02774  -0.1390   0.7915   0.0078
 -14.750  -0.7577   0.03250   0.02672  -0.1389   0.7915   0.0080
 -14.500  -0.7432   0.03157   0.02574  -0.1389   0.7914   0.0082
 -14.250  -0.7281   0.03070   0.02482  -0.1388   0.7914   0.0084
 -14.000  -0.7119   0.02991   0.02398  -0.1388   0.7914   0.0085
 -13.750  -0.6971   0.02903   0.02306  -0.1386   0.7913   0.0088
 -13.500  -0.6814   0.02822   0.02222  -0.1384   0.7913   0.0092
 -13.250  -0.6650   0.02748   0.02145  -0.1383   0.7912   0.0095
 -13.000  -0.6479   0.02680   0.02074  -0.1382   0.7912   0.0098
 -12.750  -0.6299   0.02619   0.02010  -0.1381   0.7912   0.0102
 -12.500  -0.6116   0.02561   0.01949  -0.1380   0.7911   0.0106
 -12.250  -0.5929   0.02506   0.01891  -0.1380   0.7911   0.0110
 -12.000  -0.5743   0.02451   0.01833  -0.1379   0.7911   0.0114
 -11.750  -0.5564   0.02393   0.01775  -0.1377   0.7911   0.0121
 -11.500  -0.5379   0.02340   0.01721  -0.1375   0.7910   0.0129
 -11.250  -0.5188   0.02292   0.01671  -0.1374   0.7910   0.0136
 -11.000  -0.4990   0.02249   0.01626  -0.1373   0.7910   0.0142
 -10.750  -0.4796   0.02205   0.01580  -0.1372   0.7909   0.0151
 -10.500  -0.4604   0.02159   0.01535  -0.1370   0.7909   0.0164
 -10.250  -0.4407   0.02118   0.01494  -0.1368   0.7909   0.0176
 -10.000  -0.4206   0.02080   0.01454  -0.1367   0.7908   0.0191
  -9.750  -0.4013   0.02038   0.01415  -0.1365   0.7908   0.0217
  -9.500  -0.3812   0.02001   0.01379  -0.1363   0.7908   0.0245
  -9.250  -0.3612   0.01964   0.01346  -0.1362   0.7907   0.0283
  -9.000  -0.3401   0.01933   0.01315  -0.1361   0.7907   0.0309
  -8.750  -0.3193   0.01902   0.01288  -0.1360   0.7907   0.0343
  -8.500  -0.2976   0.01876   0.01262  -0.1360   0.7906   0.0370
  -8.250  -0.2755   0.01852   0.01237  -0.1360   0.7906   0.0384
  -8.000  -0.2546   0.01823   0.01209  -0.1358   0.7905   0.0408
  -7.750  -0.2335   0.01796   0.01185  -0.1356   0.7905   0.0431
  -7.500  -0.2119   0.01773   0.01162  -0.1355   0.7905   0.0451
  -7.250  -0.1904   0.01751   0.01140  -0.1354   0.7904   0.0465
  -7.000  -0.1701   0.01732   0.01121  -0.1350   0.7904   0.0480
  -6.750  -0.1523   0.01711   0.01103  -0.1342   0.7903   0.0507
  -6.500  -0.1355   0.01696   0.01090  -0.1331   0.7902   0.0531
  -6.250  -0.1202   0.01685   0.01081  -0.1317   0.7901   0.0555
  -6.000  -0.1028   0.01675   0.01071  -0.1307   0.7900   0.0573
  -5.750  -0.0845   0.01660   0.01058  -0.1300   0.7899   0.0601
  -5.500  -0.0659   0.01644   0.01045  -0.1293   0.7897   0.0635
  -5.250  -0.0462   0.01631   0.01034  -0.1289   0.7896   0.0668
  -5.000  -0.0253   0.01619   0.01024  -0.1287   0.7893   0.0697
  -4.750  -0.0043   0.01604   0.01011  -0.1285   0.7889   0.0757
  -4.500   0.0170   0.01591   0.01002  -0.1285   0.7886   0.0830
  -4.250   0.0384   0.01573   0.00992  -0.1287   0.7883   0.0985
  -4.000   0.0615   0.01528   0.00966  -0.1299   0.7879   0.1464
  -3.750   0.0965   0.01416   0.00900  -0.1351   0.7875   0.2669
  -3.500   0.1729   0.01211   0.00832  -0.1504   0.7879   0.6137
  -3.000   0.2266   0.01291   0.00903  -0.1511   0.7872   0.6538
  -2.750   0.2465   0.01353   0.00970  -0.1498   0.7865   0.6558
  -2.500   0.2665   0.01409   0.01028  -0.1487   0.7858   0.6575
  -2.250   0.2849   0.01474   0.01095  -0.1472   0.7851   0.6600
  -2.000   0.3060   0.01526   0.01146  -0.1465   0.7844   0.6629
  -1.750   0.3343   0.01551   0.01165  -0.1473   0.7838   0.6659
  -1.500   0.3513   0.01607   0.01226  -0.1455   0.7831   0.6674
  -1.250   0.3689   0.01661   0.01285  -0.1437   0.7825   0.6687
  -1.000   0.3924   0.01690   0.01314  -0.1434   0.7821   0.6692
  -0.750   0.3391   0.02021   0.01651  -0.1308   0.7736   0.6702
  -0.500   0.3663   0.02029   0.01658  -0.1312   0.7724   0.6707
  -0.250   0.3963   0.02025   0.01654  -0.1321   0.7717   0.6712
   0.000   0.4265   0.02022   0.01650  -0.1331   0.7711   0.6715
   0.250   0.4563   0.02023   0.01650  -0.1340   0.7706   0.6720
   0.500   0.4864   0.02022   0.01649  -0.1349   0.7702   0.6726
   0.750   0.5177   0.02015   0.01642  -0.1361   0.7698   0.6731
   1.000   0.5499   0.02002   0.01629  -0.1374   0.7695   0.6733
   1.250   0.5822   0.01988   0.01615  -0.1387   0.7692   0.6736
   1.500   0.6149   0.01972   0.01599  -0.1401   0.7689   0.6740
   1.750   0.6499   0.01941   0.01568  -0.1419   0.7686   0.6741
   2.000   0.6873   0.01893   0.01522  -0.1440   0.7684   0.6743
   2.250   0.7249   0.01843   0.01473  -0.1461   0.7683   0.6744
   2.500   0.7614   0.01801   0.01431  -0.1480   0.7681   0.6746
   2.750   0.7971   0.01763   0.01395  -0.1499   0.7679   0.6747
   3.000   0.8328   0.01724   0.01358  -0.1517   0.7678   0.6748
   3.250   0.8727   0.01654   0.01291  -0.1541   0.7678   0.6749
   3.500   0.9118   0.01568   0.01207  -0.1564   0.7660   0.6751
   4.750   0.9699   0.01708   0.01264  -0.1453   0.5866   0.6760
   5.000   0.9611   0.01866   0.01402  -0.1398   0.5492   0.6761
   5.250   0.9615   0.01993   0.01513  -0.1359   0.5164   0.6762
   5.500   0.9670   0.02100   0.01603  -0.1329   0.4820   0.6763
   5.750   0.9719   0.02209   0.01690  -0.1298   0.4380   0.6764
   6.000   0.9758   0.02323   0.01775  -0.1266   0.3849   0.6766
   6.250   0.9816   0.02428   0.01849  -0.1237   0.3278   0.6768
   6.500   0.9911   0.02519   0.01914  -0.1214   0.2785   0.6769
   6.750   1.0020   0.02607   0.01978  -0.1193   0.2328   0.6769
   7.000   1.0138   0.02693   0.02042  -0.1174   0.1909   0.6770
   7.250   1.0257   0.02780   0.02108  -0.1156   0.1507   0.6770
   7.500   1.0394   0.02862   0.02172  -0.1141   0.1192   0.6771
   7.750   1.0562   0.02930   0.02230  -0.1130   0.1000   0.6771
   8.000   1.0738   0.02995   0.02288  -0.1121   0.0850   0.6771
   8.250   1.0918   0.03058   0.02345  -0.1113   0.0735   0.6772
   8.500   1.1106   0.03116   0.02400  -0.1106   0.0655   0.6772
   8.750   1.1288   0.03179   0.02459  -0.1098   0.0565   0.6772
   9.000   1.1461   0.03247   0.02521  -0.1089   0.0470   0.6773
   9.250   1.1612   0.03329   0.02594  -0.1077   0.0328   0.6773
   9.500   1.1763   0.03412   0.02671  -0.1064   0.0226   0.6773
   9.750   1.1932   0.03487   0.02745  -0.1055   0.0190   0.6774
  10.000   1.2095   0.03565   0.02824  -0.1046   0.0168   0.6774
  10.250   1.2266   0.03639   0.02900  -0.1037   0.0154   0.6774
  10.500   1.2438   0.03712   0.02977  -0.1029   0.0144   0.6775
  10.750   1.2604   0.03791   0.03056  -0.1020   0.0133   0.6775
  11.000   1.2762   0.03874   0.03141  -0.1010   0.0123   0.6775
  11.250   1.2932   0.03952   0.03222  -0.1002   0.0117   0.6776
  11.500   1.3096   0.04033   0.03306  -0.0993   0.0111   0.6776
  11.750   1.3246   0.04126   0.03401  -0.0983   0.0105   0.6776
  12.000   1.3389   0.04224   0.03501  -0.0973   0.0099   0.6777
  12.250   1.3525   0.04326   0.03608  -0.0961   0.0093   0.6777
  12.500   1.3677   0.04419   0.03705  -0.0952   0.0090   0.6777
  12.750   1.3824   0.04516   0.03806  -0.0943   0.0087   0.6778
  13.000   1.3961   0.04622   0.03916  -0.0932   0.0084   0.6778
  13.250   1.4089   0.04737   0.04035  -0.0921   0.0081   0.6778
  13.500   1.4216   0.04854   0.04155  -0.0911   0.0078   0.6779
  13.750   1.4338   0.04975   0.04281  -0.0900   0.0075   0.6779
  14.000   1.4441   0.05112   0.04423  -0.0887   0.0071   0.6779
  14.250   1.4555   0.05243   0.04558  -0.0876   0.0069   0.6780
  14.500   1.4669   0.05374   0.04695  -0.0866   0.0067   0.6780
  14.750   1.4778   0.05511   0.04838  -0.0855   0.0066   0.6781
  15.000   1.4875   0.05661   0.04994  -0.0844   0.0064   0.6781
  15.250   1.4974   0.05813   0.05151  -0.0834   0.0062   0.6781
  15.500   1.5064   0.05973   0.05317  -0.0823   0.0060   0.6782
  15.750   1.5146   0.06144   0.05495  -0.0813   0.0059   0.6782
  16.000   1.5227   0.06317   0.05673  -0.0803   0.0057   0.6783
  16.250   1.5290   0.06510   0.05872  -0.0792   0.0056   0.6783
  16.500   1.5348   0.06708   0.06077  -0.0782   0.0054   0.6783
  16.750   1.5382   0.06937   0.06314  -0.0771   0.0053   0.6784
  17.000   1.5427   0.07158   0.06542  -0.0762   0.0052   0.6784
  17.250   1.5470   0.07386   0.06779  -0.0753   0.0051   0.6784
  17.500   1.5513   0.07616   0.07017  -0.0746   0.0051   0.6785
  17.750   1.5550   0.07857   0.07267  -0.0740   0.0050   0.6785
  18.000   1.5573   0.08117   0.07535  -0.0734   0.0049   0.6785
  18.250   1.5592   0.08383   0.07810  -0.0728   0.0048   0.6786
  18.500   1.5604   0.08661   0.08097  -0.0724   0.0047   0.6786
  18.750   1.5606   0.08957   0.08402  -0.0721   0.0047   0.6787
  19.000   1.5603   0.09261   0.08715  -0.0719   0.0046   0.6787
  19.250   1.5601   0.09569   0.09032  -0.0719   0.0045   0.6787
<< Back to WORTMANN FX 3 AIRFOIL (fx3-il)

Polar data table (+)

Polar graphs


<< Back to WORTMANN FX 3 AIRFOIL (fx3-il)