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FX 38-153 AIRFOIL (fx38153-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: FX 38-153 AIRFOIL (fx38153-il)
Reynolds number: 200,000
Max Cl/Cd: 46.61 at α=6.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx38153-il-200000.txt
Download as CSV file: xf-fx38153-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 38-153 AIRFOIL                               
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.6069   0.09130   0.08805  -0.0463   1.0001   0.0464
  -9.500  -0.6326   0.08753   0.08425  -0.0450   1.0001   0.0463
  -9.250  -0.6595   0.08441   0.08109  -0.0426   1.0001   0.0462
  -9.000  -0.6873   0.08193   0.07857  -0.0388   1.0001   0.0460
  -8.750  -0.7161   0.07987   0.07647  -0.0342   1.0001   0.0458
  -8.500  -0.7453   0.07704   0.07346  -0.0303   1.0001   0.0463
  -8.250  -0.7847   0.07536   0.07126  -0.0247   1.0001   0.0473
  -6.000  -0.6496   0.03747   0.03045  -0.0226   0.9785   0.0307
  -5.750  -0.6147   0.03483   0.02744  -0.0240   0.9732   0.0297
  -5.500  -0.5698   0.03287   0.02509  -0.0270   0.9696   0.0291
  -5.250  -0.5427   0.03090   0.02267  -0.0259   0.9626   0.0271
  -5.000  -0.5093   0.02996   0.02157  -0.0267   0.9588   0.0267
  -4.750  -0.4733   0.02895   0.02052  -0.0282   0.9562   0.0267
  -4.500  -0.4465   0.02797   0.01957  -0.0281   0.9516   0.0269
  -4.250  -0.4227   0.02702   0.01866  -0.0279   0.9468   0.0276
  -4.000  -0.3888   0.02636   0.01804  -0.0297   0.9433   0.0289
  -3.750  -0.3475   0.02592   0.01755  -0.0329   0.9407   0.0315
  -3.500  -0.3231   0.02521   0.01682  -0.0329   0.9336   0.0356
  -3.250  -0.2846   0.02403   0.01591  -0.0360   0.9298   0.0847
  -3.000  -0.2437   0.02156   0.01645  -0.0408   0.9288   0.6751
  -2.750  -0.2087   0.02259   0.01743  -0.0413   0.9255   0.7392
  -2.500  -0.2017   0.02341   0.01825  -0.0360   0.9171   0.7594
  -2.250  -0.1826   0.02463   0.01943  -0.0323   0.9119   0.7780
  -2.000  -0.1660   0.02532   0.02006  -0.0289   0.9046   0.7898
  -1.750  -0.1431   0.02591   0.02057  -0.0269   0.8983   0.8023
  -1.500  -0.1176   0.02684   0.02145  -0.0243   0.8950   0.8170
  -1.250  -0.1176   0.02719   0.02181  -0.0174   0.8850   0.8247
  -1.000  -0.0867   0.02745   0.02198  -0.0172   0.8814   0.8349
  -0.750  -0.0708   0.02767   0.02217  -0.0142   0.8735   0.8456
  -0.500  -0.0515   0.02782   0.02228  -0.0107   0.8682   0.8561
  -0.250  -0.0213   0.02791   0.02231  -0.0098   0.8656   0.8678
   0.000  -0.0065   0.02789   0.02226  -0.0080   0.8562   0.8775
   0.250   0.0248   0.02754   0.02187  -0.0078   0.8527   0.8818
   0.500   0.0665   0.02719   0.02146  -0.0103   0.8506   0.8849
   0.750   0.0817   0.02695   0.02119  -0.0086   0.8401   0.8902
   1.000   0.1196   0.02655   0.02075  -0.0108   0.8373   0.8933
   1.250   0.1590   0.02609   0.02026  -0.0128   0.8356   0.8953
   1.500   0.1730   0.02580   0.01997  -0.0106   0.8245   0.8984
   1.750   0.2152   0.02520   0.01935  -0.0133   0.8221   0.9001
   2.000   0.2363   0.02487   0.01903  -0.0124   0.8123   0.9033
   2.250   0.2765   0.02426   0.01842  -0.0149   0.8088   0.9053
   2.500   0.3208   0.02355   0.01771  -0.0180   0.8066   0.9068
   2.750   0.3376   0.02304   0.01722  -0.0157   0.7960   0.9095
   3.000   0.3780   0.02210   0.01631  -0.0176   0.7930   0.9115
   3.250   0.4174   0.02112   0.01535  -0.0192   0.7892   0.9131
   3.500   0.4426   0.02049   0.01475  -0.0186   0.7792   0.9155
   3.750   0.4859   0.01950   0.01379  -0.0211   0.7762   0.9169
   4.000   0.5089   0.01911   0.01345  -0.0205   0.7640   0.9186
   4.250   0.5407   0.01857   0.01295  -0.0213   0.7535   0.9199
   4.500   0.5821   0.01779   0.01220  -0.0237   0.7432   0.9210
   4.750   0.6109   0.01718   0.01161  -0.0236   0.7254   0.9226
   5.000   0.6442   0.01662   0.01104  -0.0244   0.7038   0.9240
   5.250   0.6810   0.01617   0.01051  -0.0259   0.6768   0.9249
   5.500   0.7141   0.01594   0.01013  -0.0268   0.6391   0.9259
   5.750   0.7374   0.01600   0.00998  -0.0262   0.5964   0.9274
   6.000   0.7539   0.01624   0.01002  -0.0244   0.5553   0.9295
   6.250   0.7701   0.01654   0.01018  -0.0228   0.5205   0.9315
   6.500   0.7877   0.01690   0.01043  -0.0215   0.4894   0.9330
   6.750   0.8051   0.01733   0.01075  -0.0204   0.4589   0.9344
   7.000   0.8191   0.01771   0.01103  -0.0186   0.4275   0.9363
   7.250   0.8313   0.01814   0.01134  -0.0164   0.3970   0.9381
   7.500   0.8456   0.01862   0.01173  -0.0148   0.3642   0.9395
   7.750   0.8595   0.01920   0.01218  -0.0132   0.3341   0.9410
   8.000   0.8748   0.01979   0.01268  -0.0120   0.3028   0.9426
   8.250   0.8902   0.02042   0.01322  -0.0108   0.2761   0.9445
   8.500   0.9075   0.02106   0.01379  -0.0100   0.2500   0.9461
   8.750   0.9244   0.02181   0.01444  -0.0093   0.2283   0.9473
   9.000   0.9434   0.02250   0.01512  -0.0090   0.2092   0.9484
   9.250   0.9605   0.02308   0.01570  -0.0081   0.1927   0.9496
   9.500   0.9758   0.02373   0.01633  -0.0070   0.1793   0.9510
   9.750   0.9915   0.02443   0.01703  -0.0061   0.1668   0.9525
  10.000   1.0095   0.02503   0.01771  -0.0054   0.1539   0.9540
  10.250   1.0253   0.02575   0.01845  -0.0046   0.1409   0.9560
  10.500   1.0408   0.02657   0.01929  -0.0038   0.1284   0.9579
  10.750   1.0571   0.02743   0.02019  -0.0032   0.1144   0.9594
  11.000   1.0720   0.02844   0.02121  -0.0025   0.0994   0.9607
  11.250   1.0825   0.02967   0.02239  -0.0013   0.0850   0.9621
  11.500   1.0917   0.03092   0.02365   0.0002   0.0692   0.9637
  11.750   1.0961   0.03259   0.02523   0.0020   0.0593   0.9654
  12.000   1.1028   0.03418   0.02693   0.0034   0.0531   0.9671
  12.250   1.1028   0.03636   0.02912   0.0053   0.0492   0.9688
  12.500   1.1126   0.03784   0.03075   0.0063   0.0466   0.9709
  12.750   1.1215   0.03944   0.03248   0.0072   0.0444   0.9730
  13.000   1.1284   0.04103   0.03415   0.0083   0.0426   0.9754
  13.250   1.1336   0.04288   0.03606   0.0092   0.0411   0.9777
  13.500   1.1390   0.04487   0.03811   0.0101   0.0397   0.9799
  13.750   1.1483   0.04657   0.03997   0.0105   0.0385   0.9823
  14.000   1.1565   0.04840   0.04195   0.0108   0.0371   0.9849
  14.250   1.1637   0.05034   0.04399   0.0109   0.0358   0.9881
  14.500   1.1694   0.05243   0.04616   0.0110   0.0347   0.9924
  14.750   1.1738   0.05457   0.04837   0.0112   0.0337   0.9999
  15.000   1.1820   0.05688   0.05074   0.0115   0.0327   0.9999
  15.250   1.1900   0.05929   0.05331   0.0112   0.0323   0.9999
  15.500   1.1966   0.06189   0.05611   0.0108   0.0319   0.9999
  15.750   1.2015   0.06474   0.05917   0.0103   0.0313   0.9999
  16.000   1.2043   0.06784   0.06247   0.0096   0.0307   0.9999
  16.250   1.2053   0.07122   0.06604   0.0086   0.0300   0.9999
  16.500   1.2047   0.07485   0.06984   0.0072   0.0291   0.9999
  16.750   1.2045   0.07849   0.07360   0.0056   0.0281   0.9999
  17.000   1.2052   0.08201   0.07717   0.0041   0.0271   0.9999
  17.500   1.1932   0.09122   0.08673   0.0006   0.0257   0.9999
  17.750   1.1834   0.09686   0.09262  -0.0026   0.0253   0.9999
  18.000   1.1726   0.10289   0.09890  -0.0062   0.0248   0.9999
  18.250   1.1613   0.10918   0.10542  -0.0101   0.0243   0.9999
  18.500   1.1489   0.11583   0.11228  -0.0144   0.0238   0.9999
  18.750   1.1352   0.12296   0.11963  -0.0190   0.0236   0.9999
  19.000   1.1201   0.13069   0.12756  -0.0243   0.0233   0.9999
  19.250   1.0999   0.13984   0.13694  -0.0306   0.0233   0.9999
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