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FX 74-130 WP1 (fx74130wp1-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: FX 74-130 WP1 (fx74130wp1-il)
Reynolds number: 100,000
Max Cl/Cd: 39.76 at α=8.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx74130wp1-il-100000-n5.txt
Download as CSV file: xf-fx74130wp1-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 74-130 WP1                                   
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.1819   0.11202   0.10669  -0.1020   0.9352   0.0469
 -11.000  -0.1786   0.10863   0.10330  -0.1071   0.9321   0.0479
 -10.750  -0.1743   0.10506   0.09972  -0.1113   0.9293   0.0482
 -10.250  -0.0722   0.08656   0.08142  -0.1113   0.9096   0.0580
  -9.750  -0.1423   0.09029   0.08494  -0.1165   0.9181   0.0516
  -9.500  -0.1328   0.08741   0.08204  -0.1180   0.9158   0.0561
  -9.250  -0.1338   0.08430   0.07897  -0.1196   0.9117   0.0575
  -9.000  -0.1367   0.08071   0.07541  -0.1231   0.9073   0.0595
  -8.750  -0.1333   0.07694   0.07164  -0.1255   0.9041   0.0586
  -8.250  -0.1624   0.06632   0.06092  -0.1310   0.8930   0.0349
  -8.000  -0.1665   0.06342   0.05798  -0.1308   0.8896   0.0338
  -7.750  -0.1735   0.06075   0.05524  -0.1298   0.8857   0.0326
  -7.500  -0.1842   0.05823   0.05264  -0.1275   0.8804   0.0313
  -7.000  -0.1915   0.05059   0.04418  -0.1241   0.8728   0.0262
  -6.750  -0.1973   0.04891   0.04241  -0.1203   0.8676   0.0259
  -6.500  -0.1928   0.04638   0.03966  -0.1184   0.8639   0.0256
  -6.250  -0.1820   0.04362   0.03661  -0.1173   0.8613   0.0252
  -6.000  -0.1668   0.04091   0.03353  -0.1166   0.8595   0.0249
  -5.750  -0.1731   0.04004   0.03249  -0.1114   0.8534   0.0248
  -5.500  -0.1597   0.03786   0.02994  -0.1097   0.8501   0.0246
  -5.250  -0.1390   0.03565   0.02731  -0.1090   0.8480   0.0246
  -5.000  -0.1148   0.03359   0.02483  -0.1087   0.8464   0.0247
  -4.750  -0.1001   0.03234   0.02323  -0.1065   0.8433   0.0250
  -4.500  -0.0931   0.03166   0.02232  -0.1031   0.8385   0.0255
  -4.250  -0.0709   0.03044   0.02084  -0.1022   0.8359   0.0271
  -4.000  -0.0457   0.02937   0.01970  -0.1022   0.8340   0.0297
  -3.750  -0.0180   0.02833   0.01852  -0.1022   0.8326   0.0313
  -3.500   0.0098   0.02737   0.01744  -0.1021   0.8315   0.0331
  -3.250   0.0075   0.02752   0.01754  -0.0972   0.8252   0.0341
  -3.000   0.0266   0.02705   0.01698  -0.0958   0.8221   0.0370
  -2.750   0.0511   0.02645   0.01638  -0.0956   0.8201   0.0437
  -2.500   0.0782   0.02589   0.01571  -0.0956   0.8186   0.0507
  -2.250   0.1060   0.02536   0.01521  -0.0958   0.8174   0.0749
  -2.000   0.1013   0.02556   0.01567  -0.0907   0.8104   0.1161
  -1.750   0.1029   0.02367   0.01616  -0.0862   0.8073   0.6273
  -1.500   0.1082   0.02444   0.01712  -0.0797   0.8047   0.8102
  -1.250   0.1100   0.02489   0.01756  -0.0720   0.8028   0.8679
  -1.000   0.0879   0.02558   0.01831  -0.0623   0.7943   0.8966
  -0.750   0.1340   0.02600   0.01856  -0.0631   0.7940   0.9589
  -0.500   0.1727   0.02616   0.01849  -0.0658   0.7924   0.9631
  -0.250   0.2073   0.02626   0.01840  -0.0677   0.7908   0.9661
   0.000   0.2412   0.02633   0.01831  -0.0693   0.7894   0.9687
   0.500   0.2774   0.02717   0.01899  -0.0682   0.7797   0.9774
   0.750   0.3083   0.02732   0.01904  -0.0694   0.7775   0.9797
   1.000   0.3406   0.02741   0.01904  -0.0708   0.7757   0.9819
   1.250   0.3717   0.02752   0.01908  -0.0719   0.7739   0.9842
   1.500   0.3805   0.02826   0.01982  -0.0703   0.7658   0.9902
   1.750   0.4105   0.02840   0.01991  -0.0713   0.7633   0.9931
   2.000   0.4422   0.02847   0.01995  -0.0724   0.7614   0.9956
   2.500   0.4542   0.02915   0.02062  -0.0663   0.7494   1.0000
   2.750   0.4811   0.02915   0.02061  -0.0664   0.7473   1.0000
   3.000   0.4786   0.02978   0.02124  -0.0624   0.7384   1.0000
   3.250   0.5060   0.02986   0.02134  -0.0627   0.7354   1.0000
   3.500   0.5378   0.02987   0.02136  -0.0636   0.7334   1.0000
   3.750   0.5439   0.03057   0.02209  -0.0612   0.7242   1.0000
   4.000   0.5746   0.03061   0.02217  -0.0620   0.7213   1.0000
   4.250   0.6053   0.03063   0.02227  -0.0629   0.7184   1.0000
   4.500   0.6176   0.03125   0.02294  -0.0614   0.7094   1.0000
   4.750   0.6514   0.03112   0.02288  -0.0625   0.7068   1.0000
   5.000   0.6649   0.03173   0.02355  -0.0613   0.6975   1.0000
   5.250   0.6981   0.03154   0.02349  -0.0622   0.6940   1.0000
   5.750   0.7482   0.03171   0.02388  -0.0621   0.6808   1.0000
   6.250   0.8016   0.03152   0.02398  -0.0622   0.6667   1.0000
   6.500   0.8215   0.03168   0.02426  -0.0614   0.6562   1.0000
   6.750   0.8601   0.03061   0.02337  -0.0622   0.6514   1.0000
   7.000   0.8802   0.03052   0.02343  -0.0611   0.6388   1.0000
   7.250   0.9029   0.03013   0.02322  -0.0601   0.6251   1.0000
   7.500   0.9275   0.02955   0.02280  -0.0592   0.6092   1.0000
   7.750   0.9412   0.02978   0.02316  -0.0574   0.5837   1.0000
   8.000   0.9662   0.02904   0.02250  -0.0562   0.5492   1.0000
   8.250   1.0222   0.02571   0.01865  -0.0564   0.4444   1.0000
   8.500   1.0290   0.02674   0.01899  -0.0534   0.3442   1.0000
   8.750   1.0288   0.02853   0.02029  -0.0505   0.2674   1.0000
   9.000   1.0299   0.03043   0.02174  -0.0481   0.1974   1.0000
   9.250   1.0337   0.03229   0.02320  -0.0461   0.1376   1.0000
   9.500   1.0402   0.03404   0.02468  -0.0445   0.0984   1.0000
   9.750   1.0480   0.03573   0.02626  -0.0430   0.0753   1.0000
  10.000   1.0563   0.03741   0.02789  -0.0415   0.0624   1.0000
  10.250   1.0659   0.03902   0.02959  -0.0402   0.0550   1.0000
  10.500   1.0721   0.04092   0.03148  -0.0387   0.0498   1.0000
  10.750   1.0830   0.04247   0.03321  -0.0376   0.0451   1.0000
  11.000   1.0924   0.04418   0.03500  -0.0365   0.0411   1.0000
  11.250   1.0995   0.04624   0.03706  -0.0352   0.0386   1.0000
  11.500   1.1134   0.04780   0.03884  -0.0342   0.0359   1.0000
  11.750   1.1264   0.04946   0.04066  -0.0334   0.0328   1.0000
  12.000   1.1383   0.05126   0.04252  -0.0326   0.0305   1.0000
  12.250   1.1569   0.05325   0.04457  -0.0319   0.0286   1.0000
  12.500   1.1738   0.05512   0.04674  -0.0313   0.0266   1.0000
  12.750   1.1856   0.05720   0.04905  -0.0306   0.0244   1.0000
  13.000   1.1959   0.05945   0.05148  -0.0299   0.0230   1.0000
  13.250   1.2067   0.06201   0.05419  -0.0293   0.0220   1.0000
  13.500   1.2177   0.06541   0.05773  -0.0288   0.0209   1.0000
  13.750   1.2164   0.06870   0.06148  -0.0277   0.0202   1.0000
  14.000   1.2122   0.07236   0.06552  -0.0268   0.0194   1.0000
  14.250   1.2053   0.07636   0.06987  -0.0262   0.0187   1.0000
  14.500   1.1962   0.08063   0.07445  -0.0259   0.0181   1.0000
  14.750   1.1849   0.08531   0.07942  -0.0261   0.0177   1.0000
  15.000   1.1712   0.09051   0.08491  -0.0267   0.0175   1.0000
  15.250   1.1554   0.09625   0.09093  -0.0279   0.0174   1.0000
  15.500   1.1373   0.10262   0.09758  -0.0299   0.0173   1.0000
  15.750   1.1175   0.10976   0.10497  -0.0329   0.0174   1.0000
  16.000   1.0959   0.11781   0.11326  -0.0370   0.0175   1.0000
  16.250   1.0725   0.12708   0.12275  -0.0425   0.0177   1.0000
  16.500   1.0470   0.13803   0.13385  -0.0495   0.0181   1.0000
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