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FX 84-W-097 (fx84w097-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: FX 84-W-097 (fx84w097-il)
Reynolds number: 50,000
Max Cl/Cd: 36.82 at α=7.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx84w097-il-50000-n5.txt
Download as CSV file: xf-fx84w097-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 84-W-097                                     
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.3428   0.10662   0.10011  -0.0236   1.0000   0.0724
  -9.750  -0.3386   0.10250   0.09602  -0.0245   1.0000   0.0696
  -9.500  -0.4360   0.10508   0.09818  -0.0243   1.0000   0.0610
  -9.250  -0.4267   0.10127   0.09438  -0.0244   1.0000   0.0592
  -9.000  -0.4233   0.09738   0.09054  -0.0261   1.0000   0.0582
  -8.750  -0.4221   0.09338   0.08662  -0.0284   1.0000   0.0579
  -8.500  -0.4217   0.08939   0.08271  -0.0307   1.0000   0.0576
  -8.250  -0.4232   0.08531   0.07872  -0.0333   1.0000   0.0576
  -8.000  -0.4265   0.08119   0.07469  -0.0362   1.0000   0.0573
  -7.750  -0.4286   0.07678   0.07035  -0.0395   1.0000   0.0568
  -7.500  -0.4304   0.07225   0.06586  -0.0425   1.0000   0.0564
  -7.250  -0.4326   0.06786   0.06147  -0.0447   1.0000   0.0559
  -7.000  -0.4360   0.06375   0.05732  -0.0457   1.0000   0.0554
  -6.750  -0.4411   0.06004   0.05354  -0.0455   1.0000   0.0549
  -6.500  -0.4465   0.05662   0.05000  -0.0444   1.0000   0.0544
  -6.250  -0.4503   0.05328   0.04646  -0.0431   1.0000   0.0542
  -6.000  -0.4507   0.05000   0.04293  -0.0417   1.0000   0.0541
  -5.750  -0.4474   0.04681   0.03944  -0.0405   1.0000   0.0544
  -5.500  -0.4193   0.04248   0.03454  -0.0437   0.9907   0.0561
  -5.250  -0.3875   0.03848   0.02972  -0.0467   0.9818   0.0600
  -5.000  -0.3552   0.03502   0.02553  -0.0489   0.9733   0.0624
  -4.750  -0.3229   0.03265   0.02288  -0.0507   0.9653   0.0652
  -4.500  -0.2869   0.03077   0.02057  -0.0529   0.9581   0.0721
  -4.250  -0.2539   0.02891   0.01835  -0.0541   0.9500   0.0777
  -4.000  -0.2159   0.02742   0.01655  -0.0561   0.9437   0.0859
  -3.750  -0.1835   0.02627   0.01529  -0.0572   0.9353   0.0968
  -3.500  -0.1453   0.02511   0.01398  -0.0590   0.9293   0.1105
  -3.250  -0.1139   0.02426   0.01298  -0.0597   0.9205   0.1299
  -3.000  -0.0780   0.02336   0.01210  -0.0614   0.9138   0.1609
  -2.750  -0.0504   0.02255   0.01147  -0.0617   0.9043   0.2044
  -2.500  -0.0226   0.02155   0.01095  -0.0622   0.8959   0.2927
  -2.250  -0.0017   0.02015   0.01074  -0.0609   0.8877   0.5191
  -2.000   0.0340   0.01948   0.01096  -0.0591   0.8821   0.8616
  -1.750   0.1357   0.01911   0.01006  -0.0722   0.8823   1.0000
  -1.500   0.1616   0.01920   0.00987  -0.0722   0.8722   1.0000
  -1.250   0.1827   0.01937   0.00980  -0.0713   0.8608   1.0000
  -1.000   0.2049   0.01956   0.00976  -0.0706   0.8503   1.0000
  -0.750   0.2308   0.01969   0.00966  -0.0703   0.8417   1.0000
  -0.500   0.2511   0.01993   0.00973  -0.0691   0.8308   1.0000
  -0.250   0.2724   0.02017   0.00981  -0.0681   0.8207   1.0000
   0.000   0.2987   0.02032   0.00980  -0.0677   0.8128   1.0000
   0.250   0.3194   0.02061   0.00997  -0.0667   0.8021   1.0000
   0.500   0.3420   0.02088   0.01013  -0.0658   0.7925   1.0000
   0.750   0.3682   0.02104   0.01019  -0.0653   0.7846   1.0000
   1.000   0.3892   0.02138   0.01046  -0.0643   0.7740   1.0000
   1.250   0.4131   0.02164   0.01065  -0.0636   0.7651   1.0000
   1.500   0.4380   0.02187   0.01082  -0.0630   0.7566   1.0000
   1.750   0.4600   0.02223   0.01115  -0.0621   0.7464   1.0000
   2.000   0.4860   0.02243   0.01133  -0.0615   0.7386   1.0000
   2.250   0.5088   0.02277   0.01167  -0.0608   0.7287   1.0000
   2.500   0.5317   0.02313   0.01204  -0.0600   0.7191   1.0000
   2.750   0.5589   0.02328   0.01222  -0.0595   0.7117   1.0000
   3.000   0.5803   0.02373   0.01272  -0.0586   0.7008   1.0000
   3.250   0.6040   0.02408   0.01311  -0.0579   0.6912   1.0000
   3.500   0.6307   0.02424   0.01331  -0.0573   0.6831   1.0000
   3.750   0.6525   0.02469   0.01388  -0.0565   0.6719   1.0000
   4.000   0.6760   0.02505   0.01433  -0.0557   0.6617   1.0000
   4.250   0.7038   0.02513   0.01448  -0.0550   0.6535   1.0000
   4.500   0.7255   0.02560   0.01507  -0.0542   0.6417   1.0000
   4.750   0.7481   0.02600   0.01565  -0.0533   0.6304   1.0000
   5.000   0.7725   0.02628   0.01606  -0.0525   0.6195   1.0000
   5.250   0.7997   0.02631   0.01622  -0.0516   0.6093   1.0000
   5.500   0.8232   0.02657   0.01665  -0.0506   0.5965   1.0000
   5.750   0.8462   0.02686   0.01715  -0.0495   0.5831   1.0000
   6.000   0.8696   0.02708   0.01757  -0.0484   0.5692   1.0000
   6.250   0.8936   0.02721   0.01789  -0.0472   0.5545   1.0000
   6.500   0.9188   0.02708   0.01794  -0.0458   0.5378   1.0000
   6.750   0.9383   0.02704   0.01808  -0.0438   0.5129   1.0000
   7.000   0.9588   0.02654   0.01768  -0.0413   0.4803   1.0000
   7.250   0.9736   0.02654   0.01773  -0.0386   0.4396   1.0000
   7.500   0.9872   0.02681   0.01797  -0.0360   0.3927   1.0000
   7.750   0.9970   0.02749   0.01849  -0.0334   0.3333   1.0000
   8.000   1.0009   0.02881   0.01941  -0.0305   0.2600   1.0000
   8.250   0.9977   0.03095   0.02100  -0.0275   0.1912   1.0000
   8.500   0.9925   0.03334   0.02303  -0.0248   0.1474   1.0000
   8.750   0.9888   0.03582   0.02524  -0.0225   0.1207   1.0000
   9.000   0.9879   0.03827   0.02755  -0.0207   0.1042   1.0000
   9.250   0.9897   0.04064   0.02987  -0.0192   0.0918   1.0000
   9.500   0.9936   0.04293   0.03217  -0.0178   0.0817   1.0000
   9.750   0.9991   0.04520   0.03438  -0.0165   0.0750   1.0000
  10.000   1.0104   0.04712   0.03649  -0.0152   0.0678   1.0000
  10.250   1.0222   0.04915   0.03850  -0.0140   0.0620   1.0000
  10.500   1.0450   0.05083   0.04048  -0.0126   0.0568   1.0000
  10.750   1.0653   0.05280   0.04251  -0.0116   0.0526   1.0000
  11.000   1.0830   0.05526   0.04528  -0.0106   0.0488   1.0000
  11.250   1.0963   0.05804   0.04840  -0.0097   0.0462   1.0000
  11.500   1.1067   0.06118   0.05184  -0.0090   0.0446   1.0000
  11.750   1.1114   0.06451   0.05544  -0.0084   0.0434   1.0000
  12.000   1.1123   0.06797   0.05911  -0.0080   0.0423   1.0000
  12.250   1.1116   0.07166   0.06297  -0.0078   0.0413   1.0000
  12.500   1.1059   0.07595   0.06741  -0.0081   0.0405   1.0000
  12.750   1.0906   0.08075   0.07253  -0.0091   0.0402   1.0000
  13.000   1.0745   0.08602   0.07808  -0.0107   0.0401   1.0000
  13.250   1.0565   0.09188   0.08418  -0.0131   0.0400   1.0000
  13.500   1.0379   0.09830   0.09081  -0.0162   0.0401   1.0000
  13.750   1.0190   0.10529   0.09798  -0.0200   0.0402   1.0000
  14.000   1.0004   0.11280   0.10563  -0.0244   0.0404   1.0000
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