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FX 84-W-150 (fx84w150-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: FX 84-W-150 (fx84w150-il)
Reynolds number: 100,000
Max Cl/Cd: 47.44 at α=8°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx84w150-il-100000-n5.txt
Download as CSV file: xf-fx84w150-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 84-W-150                                     
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.2346   0.09459   0.08947  -0.0841   0.9522   0.0410
 -10.750  -0.2341   0.08826   0.08313  -0.0894   0.9456   0.0413
 -10.500  -0.2386   0.08161   0.07648  -0.0945   0.9371   0.0414
 -10.250  -0.2519   0.07268   0.06755  -0.1016   0.9290   0.0413
 -10.000  -0.2977   0.05851   0.05325  -0.1139   0.9148   0.0407
  -9.750  -0.3339   0.05238   0.04688  -0.1170   0.9001   0.0403
  -9.500  -0.3622   0.04853   0.04274  -0.1157   0.8876   0.0403
  -9.250  -0.3782   0.04464   0.03845  -0.1144   0.8787   0.0407
  -9.000  -0.3866   0.04123   0.03457  -0.1126   0.8697   0.0412
  -8.750  -0.3886   0.03787   0.03059  -0.1108   0.8629   0.0423
  -8.500  -0.3766   0.03647   0.02905  -0.1096   0.8558   0.0436
  -8.250  -0.3590   0.03538   0.02782  -0.1088   0.8507   0.0452
  -8.000  -0.3445   0.03390   0.02609  -0.1077   0.8447   0.0469
  -7.750  -0.3298   0.03208   0.02387  -0.1064   0.8384   0.0487
  -7.500  -0.3108   0.03039   0.02178  -0.1055   0.8340   0.0507
  -7.250  -0.2906   0.02968   0.02105  -0.1048   0.8285   0.0529
  -7.000  -0.2703   0.02876   0.01996  -0.1040   0.8226   0.0554
  -6.750  -0.2474   0.02754   0.01842  -0.1033   0.8183   0.0582
  -6.500  -0.2245   0.02662   0.01742  -0.1028   0.8141   0.0610
  -6.250  -0.2037   0.02606   0.01681  -0.1020   0.8078   0.0642
  -6.000  -0.1794   0.02522   0.01577  -0.1014   0.8033   0.0680
  -5.750  -0.1543   0.02441   0.01489  -0.1010   0.7999   0.0719
  -5.500  -0.1333   0.02397   0.01443  -0.1002   0.7937   0.0764
  -5.250  -0.1095   0.02337   0.01369  -0.0995   0.7888   0.0814
  -5.000  -0.0846   0.02277   0.01311  -0.0992   0.7851   0.0873
  -4.750  -0.0607   0.02231   0.01253  -0.0985   0.7806   0.0941
  -4.500  -0.0395   0.02191   0.01219  -0.0977   0.7745   0.1015
  -4.250  -0.0147   0.02143   0.01168  -0.0972   0.7704   0.1112
  -4.000   0.0117   0.02096   0.01116  -0.0969   0.7673   0.1238
  -3.750   0.0322   0.02075   0.01099  -0.0960   0.7608   0.1375
  -3.500   0.0560   0.02038   0.01068  -0.0954   0.7559   0.1560
  -3.250   0.0820   0.01993   0.01029  -0.0951   0.7524   0.1817
  -3.000   0.1051   0.01961   0.01010  -0.0945   0.7476   0.2157
  -2.750   0.1265   0.01930   0.00999  -0.0937   0.7417   0.2632
  -2.500   0.1506   0.01874   0.00973  -0.0932   0.7377   0.3427
  -2.250   0.1742   0.01804   0.00953  -0.0924   0.7347   0.4706
  -2.000   0.1895   0.01793   0.00991  -0.0900   0.7278   0.5898
  -1.750   0.2113   0.01785   0.01003  -0.0882   0.7233   0.6767
  -1.500   0.2357   0.01781   0.01001  -0.0867   0.7200   0.7335
  -1.250   0.2556   0.01798   0.01020  -0.0847   0.7147   0.7731
  -1.000   0.2755   0.01815   0.01035  -0.0828   0.7092   0.8054
  -0.750   0.2997   0.01816   0.01031  -0.0814   0.7055   0.8347
  -0.500   0.3263   0.01811   0.01017  -0.0803   0.7026   0.8611
  -0.250   0.3435   0.01843   0.01050  -0.0782   0.6955   0.8849
   0.000   0.3708   0.01848   0.01049  -0.0775   0.6912   0.9125
   0.250   0.4145   0.01844   0.01035  -0.0798   0.6883   0.9379
   0.500   0.4569   0.01850   0.01033  -0.0826   0.6841   0.9547
   0.750   0.4953   0.01867   0.01044  -0.0852   0.6782   0.9656
   1.000   0.5373   0.01862   0.01031  -0.0882   0.6742   0.9740
   1.250   0.5803   0.01849   0.01007  -0.0913   0.6712   0.9815
   1.500   0.6167   0.01873   0.01031  -0.0938   0.6647   0.9911
   1.750   0.6538   0.01877   0.01030  -0.0962   0.6597   1.0000
   2.000   0.6736   0.01873   0.01018  -0.0949   0.6559   1.0000
   2.250   0.6803   0.01907   0.01053  -0.0917   0.6493   1.0000
   2.500   0.6945   0.01923   0.01066  -0.0895   0.6438   1.0000
   2.750   0.7180   0.01920   0.01056  -0.0888   0.6401   1.0000
   3.000   0.7298   0.01959   0.01095  -0.0865   0.6337   1.0000
   3.250   0.7495   0.01981   0.01115  -0.0853   0.6282   1.0000
   3.500   0.7775   0.01980   0.01110  -0.0854   0.6245   1.0000
   3.750   0.7948   0.02020   0.01151  -0.0840   0.6184   1.0000
   4.000   0.8156   0.02048   0.01181  -0.0831   0.6127   1.0000
   4.250   0.8450   0.02049   0.01178  -0.0834   0.6089   1.0000
   4.500   0.8633   0.02090   0.01223  -0.0822   0.6026   1.0000
   4.750   0.8845   0.02120   0.01255  -0.0813   0.5966   1.0000
   5.000   0.9153   0.02118   0.01252  -0.0818   0.5927   1.0000
   5.250   0.9303   0.02172   0.01312  -0.0801   0.5856   1.0000
   5.500   0.9539   0.02193   0.01337  -0.0796   0.5798   1.0000
   5.750   0.9873   0.02183   0.01327  -0.0804   0.5759   1.0000
   6.000   0.9959   0.02258   0.01412  -0.0779   0.5676   1.0000
   6.250   1.0240   0.02264   0.01421  -0.0780   0.5625   1.0000
   6.500   1.0446   0.02299   0.01463  -0.0771   0.5563   1.0000
   6.750   1.0616   0.02344   0.01515  -0.0757   0.5493   1.0000
   7.000   1.0959   0.02329   0.01502  -0.0765   0.5447   1.0000
   7.250   1.1007   0.02409   0.01594  -0.0735   0.5355   1.0000
   7.500   1.1339   0.02391   0.01579  -0.0741   0.5294   1.0000
   7.750   1.1365   0.02470   0.01669  -0.0707   0.5202   1.0000
   8.000   1.1675   0.02461   0.01664  -0.0711   0.5139   1.0000
   8.250   1.1698   0.02551   0.01765  -0.0678   0.5049   1.0000
   8.500   1.1993   0.02543   0.01762  -0.0679   0.4980   1.0000
   8.750   1.2004   0.02644   0.01875  -0.0647   0.4883   1.0000
   9.000   1.2237   0.02651   0.01887  -0.0639   0.4795   1.0000
   9.250   1.2343   0.02699   0.01941  -0.0618   0.4670   1.0000
   9.500   1.2386   0.02779   0.02025  -0.0591   0.4526   1.0000
   9.750   1.2453   0.02854   0.02102  -0.0567   0.4371   1.0000
  10.000   1.2514   0.02944   0.02195  -0.0545   0.4212   1.0000
  10.250   1.2568   0.03048   0.02302  -0.0524   0.4052   1.0000
  10.500   1.2618   0.03165   0.02422  -0.0503   0.3888   1.0000
  10.750   1.2649   0.03303   0.02562  -0.0484   0.3716   1.0000
  11.000   1.2663   0.03463   0.02724  -0.0464   0.3529   1.0000
  11.250   1.2677   0.03631   0.02891  -0.0446   0.3327   1.0000
  11.500   1.2684   0.03810   0.03063  -0.0429   0.3108   1.0000
  11.750   1.2668   0.04021   0.03270  -0.0413   0.2875   1.0000
  12.000   1.2641   0.04250   0.03490  -0.0397   0.2641   1.0000
  12.250   1.2596   0.04510   0.03742  -0.0383   0.2396   1.0000
  12.500   1.2542   0.04795   0.04017  -0.0372   0.2161   1.0000
  12.750   1.2472   0.05109   0.04320  -0.0362   0.1937   1.0000
  13.000   1.2410   0.05436   0.04639  -0.0355   0.1718   1.0000
  13.250   1.2340   0.05783   0.04979  -0.0349   0.1515   1.0000
  13.500   1.2275   0.06140   0.05328  -0.0346   0.1339   1.0000
  13.750   1.2218   0.06501   0.05684  -0.0344   0.1183   1.0000
  14.000   1.2167   0.06865   0.06045  -0.0344   0.1056   1.0000
  14.250   1.2118   0.07236   0.06412  -0.0345   0.0956   1.0000
  14.500   1.2097   0.07580   0.06760  -0.0347   0.0870   1.0000
  14.750   1.2077   0.07931   0.07114  -0.0350   0.0801   1.0000
  15.000   1.2057   0.08286   0.07472  -0.0354   0.0745   1.0000
  15.250   1.2057   0.08618   0.07809  -0.0358   0.0696   1.0000
  15.500   1.2061   0.08950   0.08147  -0.0362   0.0652   1.0000
  15.750   1.2055   0.09293   0.08489  -0.0368   0.0618   1.0000
  16.000   1.2095   0.09578   0.08787  -0.0372   0.0582   1.0000
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