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WORTMANN FX 74-080 (fx74080-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: WORTMANN FX 74-080 (fx74080-il)
Reynolds number: 500,000
Max Cl/Cd: 131.48 at α=3.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx74080-il-500000-n5.txt
Download as CSV file: xf-fx74080-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: WORTMANN FX 74-080                              
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.1876   0.09632   0.09335  -0.0851   0.8632   0.0076
  -9.250  -0.1766   0.09306   0.09005  -0.0878   0.8594   0.0077
  -9.000  -0.1662   0.09009   0.08708  -0.0904   0.8557   0.0078
  -8.750  -0.1560   0.08683   0.08381  -0.0933   0.8522   0.0080
  -8.500  -0.1453   0.08357   0.08053  -0.0961   0.8491   0.0080
  -7.750  -0.0569   0.05257   0.04964  -0.1021   0.8321   0.0080
  -7.500  -0.0586   0.04818   0.04528  -0.1026   0.8297   0.0065
  -7.250  -0.0568   0.04483   0.04195  -0.1041   0.8269   0.0056
  -7.000  -0.0950   0.06210   0.05905  -0.1139   0.8320   0.0063
  -6.750  -0.0842   0.05781   0.05476  -0.1186   0.8290   0.0055
  -6.500  -0.0709   0.05347   0.05037  -0.1231   0.8261   0.0046
  -6.250  -0.0557   0.04889   0.04571  -0.1272   0.8234   0.0045
  -6.000  -0.0384   0.04467   0.04138  -0.1305   0.8213   0.0045
  -5.750  -0.0205   0.04009   0.03665  -0.1330   0.8188   0.0043
  -5.500  -0.0018   0.03649   0.03290  -0.1343   0.8161   0.0045
  -5.250   0.0184   0.03321   0.02944  -0.1352   0.8134   0.0050
  -5.000   0.0399   0.02987   0.02589  -0.1355   0.8109   0.0057
  -4.250   0.1108   0.02228   0.01752  -0.1348   0.8043   0.0079
  -4.000   0.1330   0.01925   0.01413  -0.1341   0.8020   0.0076
  -3.750   0.1566   0.01686   0.01137  -0.1335   0.7999   0.0073
  -3.500   0.1814   0.01478   0.00893  -0.1328   0.7979   0.0071
  -3.250   0.2069   0.01314   0.00698  -0.1323   0.7961   0.0071
  -3.000   0.2328   0.01186   0.00545  -0.1318   0.7945   0.0071
  -2.750   0.2581   0.01092   0.00435  -0.1313   0.7927   0.0073
  -2.500   0.2830   0.01024   0.00358  -0.1307   0.7905   0.0080
  -2.250   0.3077   0.00956   0.00279  -0.1302   0.7884   0.0100
  -2.000   0.3340   0.00936   0.00254  -0.1300   0.7862   0.0152
  -1.750   0.3602   0.00908   0.00216  -0.1298   0.7842   0.0162
  -1.500   0.3869   0.00885   0.00187  -0.1296   0.7823   0.0251
  -1.250   0.4138   0.00870   0.00175  -0.1296   0.7806   0.0501
  -1.000   0.4384   0.00836   0.00170  -0.1293   0.7782   0.1443
  -0.750   0.4592   0.00753   0.00172  -0.1285   0.7755   0.4474
  -0.500   0.4734   0.00670   0.00185  -0.1258   0.7728   0.7716
  -0.250   0.4960   0.00662   0.00189  -0.1245   0.7705   0.8528
   0.000   0.5181   0.00652   0.00190  -0.1230   0.7684   0.9086
   0.250   0.5477   0.00644   0.00187  -0.1232   0.7663   0.9501
   0.500   0.5893   0.00642   0.00185  -0.1265   0.7640   0.9727
   0.750   0.6252   0.00643   0.00185  -0.1286   0.7614   0.9826
   1.000   0.6602   0.00644   0.00186  -0.1305   0.7587   0.9925
   1.250   0.6881   0.00649   0.00190  -0.1308   0.7561   1.0000
   1.500   0.7140   0.00654   0.00194  -0.1306   0.7535   1.0000
   1.750   0.7388   0.00658   0.00202  -0.1301   0.7497   1.0000
   2.000   0.7644   0.00662   0.00209  -0.1299   0.7461   1.0000
   2.250   0.7906   0.00667   0.00220  -0.1297   0.7429   1.0000
   2.500   0.8166   0.00672   0.00230  -0.1295   0.7393   1.0000
   2.750   0.8406   0.00670   0.00230  -0.1287   0.7290   1.0000
   3.000   0.8618   0.00665   0.00224  -0.1272   0.7046   1.0000
   3.250   0.8822   0.00671   0.00222  -0.1256   0.6703   1.0000
   3.500   0.8967   0.00708   0.00231  -0.1227   0.6119   1.0000
   3.750   0.8945   0.00827   0.00278  -0.1167   0.4689   1.0000
   4.000   0.8755   0.01072   0.00391  -0.1082   0.2077   1.0000
   4.250   0.8712   0.01257   0.00486  -0.1026   0.0225   1.0000
   4.500   0.8905   0.01301   0.00531  -0.1011   0.0131   1.0000
   4.750   0.9097   0.01344   0.00584  -0.0997   0.0066   1.0000
   5.000   0.9271   0.01397   0.00643  -0.0978   0.0051   1.0000
   5.250   0.9364   0.01492   0.00752  -0.0942   0.0038   1.0000
   5.500   0.9490   0.01569   0.00838  -0.0915   0.0037   1.0000
   5.750   0.9598   0.01663   0.00943  -0.0885   0.0035   1.0000
   6.000   0.9702   0.01771   0.01061  -0.0855   0.0034   1.0000
   6.250   0.9820   0.01895   0.01194  -0.0827   0.0034   1.0000
   6.500   0.9980   0.02044   0.01354  -0.0808   0.0033   1.0000
   6.750   1.0232   0.02222   0.01544  -0.0803   0.0034   1.0000
   7.000   1.0628   0.02480   0.01822  -0.0825   0.0034   1.0000
   7.250   1.0976   0.02778   0.02146  -0.0837   0.0035   1.0000
   7.500   1.1241   0.03138   0.02547  -0.0833   0.0036   1.0000
   7.750   1.1412   0.03535   0.02980  -0.0815   0.0038   1.0000
   8.750   1.1746   0.04698   0.04253  -0.0699   0.0037   1.0000
   9.000   1.1737   0.05031   0.04612  -0.0660   0.0037   1.0000
   9.250   1.1944   0.05162   0.04759  -0.0644   0.0029   1.0000
   9.500   1.1883   0.05472   0.05091  -0.0601   0.0030   1.0000
   9.750   1.1789   0.05781   0.05421  -0.0554   0.0029   1.0000
  10.000   1.1686   0.06079   0.05737  -0.0512   0.0028   1.0000
  10.250   1.1553   0.06391   0.06067  -0.0473   0.0027   1.0000
  10.500   1.1392   0.06734   0.06426  -0.0439   0.0027   1.0000
  10.750   1.1219   0.07103   0.06812  -0.0412   0.0026   1.0000
  11.000   1.1032   0.07481   0.07204  -0.0394   0.0028   1.0000
  11.250   1.0855   0.07915   0.07653  -0.0381   0.0026   1.0000
  11.500   1.0644   0.08388   0.08139  -0.0378   0.0027   1.0000
  11.750   1.0450   0.08913   0.08677  -0.0384   0.0027   1.0000
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