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FX 83-W-160 (fx83w160-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: FX 83-W-160 (fx83w160-il)
Reynolds number: 100,000
Max Cl/Cd: 45.31 at α=8.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx83w160-il-100000.txt
Download as CSV file: xf-fx83w160-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 83-W-160                                     
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.5458   0.10496   0.10013  -0.0466   1.0000   0.1089
 -10.250  -0.5505   0.10181   0.09701  -0.0452   1.0000   0.1078
 -10.000  -0.8620   0.06469   0.05914  -0.0596   1.0000   0.0854
  -9.750  -0.8784   0.06042   0.05456  -0.0585   1.0000   0.0853
  -9.500  -0.8799   0.05696   0.05097  -0.0574   1.0000   0.0862
  -9.250  -0.8616   0.05682   0.05106  -0.0558   1.0000   0.0887
  -9.000  -0.8620   0.05383   0.04784  -0.0550   1.0000   0.0901
  -8.750  -0.8604   0.05051   0.04416  -0.0545   1.0000   0.0919
  -8.500  -0.8551   0.04708   0.04026  -0.0542   1.0000   0.0938
  -8.250  -0.8409   0.04381   0.03635  -0.0549   0.9989   0.0959
  -8.000  -0.8109   0.04164   0.03404  -0.0575   0.9948   0.0998
  -7.750  -0.7840   0.04050   0.03278  -0.0587   0.9910   0.1045
  -7.500  -0.7559   0.03881   0.03046  -0.0604   0.9874   0.1094
  -7.250  -0.7270   0.03747   0.02924  -0.0619   0.9827   0.1148
  -7.000  -0.6974   0.03652   0.02800  -0.0633   0.9784   0.1215
  -6.750  -0.6675   0.03544   0.02690  -0.0647   0.9744   0.1284
  -6.500  -0.6444   0.03474   0.02600  -0.0648   0.9711   0.1360
  -6.250  -0.6157   0.03391   0.02520  -0.0658   0.9673   0.1443
  -6.000  -0.5844   0.03334   0.02441  -0.0672   0.9628   0.1550
  -5.750  -0.5622   0.03269   0.02388  -0.0670   0.9590   0.1648
  -5.500  -0.5356   0.03210   0.02329  -0.0675   0.9558   0.1762
  -5.250  -0.5004   0.03183   0.02303  -0.0695   0.9522   0.1915
  -5.000  -0.4806   0.03130   0.02249  -0.0687   0.9475   0.2052
  -4.750  -0.4561   0.03090   0.02218  -0.0689   0.9437   0.2228
  -4.500  -0.4290   0.03062   0.02207  -0.0695   0.9408   0.2441
  -4.250  -0.3947   0.03055   0.02219  -0.0714   0.9379   0.2769
  -4.000  -0.3792   0.03015   0.02199  -0.0700   0.9342   0.3092
  -3.750  -0.3581   0.02987   0.02205  -0.0695   0.9302   0.3572
  -3.500  -0.3312   0.03010   0.02264  -0.0696   0.9262   0.4182
  -3.250  -0.2983   0.03105   0.02373  -0.0704   0.9229   0.4710
  -3.000  -0.2844   0.03158   0.02425  -0.0682   0.9195   0.5007
  -2.750  -0.2682   0.03222   0.02491  -0.0662   0.9158   0.5238
  -2.500  -0.2435   0.03298   0.02563  -0.0656   0.9113   0.5475
  -2.250  -0.2088   0.03398   0.02656  -0.0667   0.9074   0.5713
  -2.000  -0.1965   0.03438   0.02700  -0.0641   0.9019   0.5861
  -1.750  -0.1779   0.03489   0.02752  -0.0625   0.8973   0.6009
  -1.500  -0.1480   0.03556   0.02817  -0.0627   0.8927   0.6174
  -1.250  -0.1237   0.03613   0.02872  -0.0622   0.8874   0.6323
  -1.000  -0.1107   0.03648   0.02903  -0.0603   0.8836   0.6460
  -0.750  -0.0885   0.03696   0.02948  -0.0596   0.8789   0.6607
  -0.500  -0.0531   0.03764   0.03018  -0.0604   0.8743   0.6758
  -0.250  -0.0443   0.03792   0.03048  -0.0576   0.8686   0.6874
   0.000  -0.0272   0.03831   0.03085  -0.0563   0.8637   0.7013
   0.250   0.0066   0.03882   0.03133  -0.0574   0.8585   0.7165
   0.500   0.0215   0.03910   0.03164  -0.0553   0.8513   0.7271
   0.750   0.0439   0.03938   0.03191  -0.0549   0.8448   0.7381
   1.000   0.0890   0.03988   0.03236  -0.0578   0.8397   0.7503
   1.250   0.0914   0.04004   0.03255  -0.0544   0.8311   0.7580
   1.500   0.1226   0.04045   0.03292  -0.0555   0.8257   0.7693
   1.750   0.1500   0.04082   0.03332  -0.0556   0.8194   0.7783
   2.000   0.1672   0.04113   0.03361  -0.0548   0.8110   0.7877
   2.250   0.2093   0.04135   0.03386  -0.0569   0.8058   0.7971
   2.500   0.2179   0.04168   0.03419  -0.0548   0.7950   0.8062
   2.750   0.2576   0.04181   0.03435  -0.0564   0.7894   0.8167
   3.000   0.2686   0.04225   0.03483  -0.0547   0.7794   0.8267
   3.250   0.3060   0.04241   0.03500  -0.0563   0.7732   0.8387
   3.500   0.3227   0.04283   0.03548  -0.0552   0.7637   0.8493
   3.750   0.3598   0.04284   0.03553  -0.0567   0.7565   0.8615
   4.000   0.3813   0.04311   0.03586  -0.0562   0.7458   0.8749
   4.250   0.4219   0.04288   0.03571  -0.0579   0.7391   0.8919
   4.500   0.4450   0.04318   0.03614  -0.0580   0.7281   0.9137
   4.750   0.5071   0.04265   0.03577  -0.0636   0.7216   0.9613
   5.000   0.5341   0.04287   0.03600  -0.0646   0.7088   1.0000
   5.250   0.5978   0.04169   0.03483  -0.0692   0.7035   1.0000
   5.500   0.6264   0.04168   0.03484  -0.0699   0.6899   1.0000
   5.750   0.6937   0.03974   0.03294  -0.0742   0.6860   1.0000
   6.000   0.7176   0.03975   0.03295  -0.0739   0.6722   1.0000
   6.250   0.7834   0.03732   0.03059  -0.0774   0.6692   1.0000
   6.500   0.8054   0.03717   0.03047  -0.0764   0.6552   1.0000
   6.750   0.8670   0.03447   0.02787  -0.0789   0.6526   1.0000
   7.000   0.8906   0.03394   0.02739  -0.0776   0.6390   1.0000
   7.250   0.9578   0.03045   0.02401  -0.0803   0.6358   1.0000
   7.500   0.9877   0.02924   0.02287  -0.0792   0.6209   1.0000
   7.750   1.0239   0.02767   0.02137  -0.0787   0.6048   1.0000
   8.000   1.0663   0.02583   0.01957  -0.0790   0.5841   1.0000
   8.250   1.0834   0.02548   0.01921  -0.0764   0.5528   1.0000
   8.500   1.1055   0.02500   0.01859  -0.0744   0.5086   1.0000
   8.750   1.1268   0.02487   0.01801  -0.0723   0.4456   1.0000
   9.000   1.1316   0.02595   0.01859  -0.0688   0.3874   1.0000
   9.250   1.1350   0.02737   0.01953  -0.0655   0.3426   1.0000
   9.500   1.1403   0.02881   0.02064  -0.0627   0.3082   1.0000
   9.750   1.1485   0.03019   0.02181  -0.0604   0.2809   1.0000
  10.000   1.1614   0.03149   0.02283  -0.0588   0.2589   1.0000
  10.250   1.1749   0.03275   0.02394  -0.0573   0.2399   1.0000
  10.500   1.1918   0.03396   0.02500  -0.0562   0.2237   1.0000
  10.750   1.2091   0.03517   0.02610  -0.0552   0.2091   1.0000
  11.000   1.2237   0.03642   0.02738  -0.0539   0.1964   1.0000
  11.250   1.2417   0.03770   0.02864  -0.0530   0.1846   1.0000
  11.500   1.2636   0.03896   0.02977  -0.0526   0.1736   1.0000
  11.750   1.2775   0.04025   0.03112  -0.0513   0.1641   1.0000
  12.000   1.2953   0.04170   0.03260  -0.0505   0.1549   1.0000
  12.250   1.3189   0.04297   0.03371  -0.0503   0.1460   1.0000
  12.500   1.3276   0.04461   0.03557  -0.0486   0.1392   1.0000
  12.750   1.3503   0.04592   0.03676  -0.0484   0.1317   1.0000
  13.000   1.3602   0.04776   0.03882  -0.0468   0.1259   1.0000
  13.250   1.3717   0.04933   0.04047  -0.0455   0.1204   1.0000
  13.500   1.3947   0.05115   0.04226  -0.0455   0.1146   1.0000
  13.750   1.3959   0.05320   0.04460  -0.0433   0.1106   1.0000
  14.000   1.4068   0.05496   0.04643  -0.0421   0.1064   1.0000
  14.250   1.4269   0.05716   0.04864  -0.0419   0.1019   1.0000
  14.500   1.4192   0.05978   0.05160  -0.0393   0.0994   1.0000
  14.750   1.4182   0.06224   0.05428  -0.0375   0.0964   1.0000
  15.000   1.4257   0.06430   0.05640  -0.0365   0.0934   1.0000
  15.250   1.4401   0.06707   0.05920  -0.0361   0.0904   1.0000
  15.500   1.4194   0.07072   0.06323  -0.0336   0.0892   1.0000
  15.750   1.3993   0.07476   0.06763  -0.0318   0.0881   1.0000
  16.000   1.3782   0.07916   0.07234  -0.0304   0.0870   1.0000
  16.250   1.3559   0.08393   0.07740  -0.0296   0.0860   1.0000
  16.500   1.3300   0.08942   0.08319  -0.0295   0.0853   1.0000
  16.750   1.2961   0.09623   0.09030  -0.0304   0.0852   1.0000
  17.000   1.2468   0.10575   0.10017  -0.0332   0.0860   1.0000
  17.250   1.1803   0.11952   0.11428  -0.0396   0.0880   1.0000
  17.500   1.1112   0.13690   0.13185  -0.0495   0.0901   1.0000
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