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FX 63-147 AIRFOIL (fx63147-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: FX 63-147 AIRFOIL (fx63147-il)
Reynolds number: 100,000
Max Cl/Cd: 47.61 at α=10°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx63147-il-100000.txt
Download as CSV file: xf-fx63147-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 63-147 AIRFOIL                               
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.3650   0.09810   0.09367  -0.0428   1.0001   0.1117
  -8.750  -0.3920   0.09454   0.09026  -0.0450   1.0001   0.1154
  -8.500  -0.4330   0.09079   0.08666  -0.0473   1.0001   0.1162
  -8.250  -0.4679   0.08877   0.08475  -0.0452   1.0001   0.1163
  -8.000  -0.4187   0.08591   0.08191  -0.0409   1.0001   0.1233
  -7.750  -0.4466   0.08342   0.07955  -0.0394   1.0001   0.1246
  -7.500  -0.4824   0.08183   0.07807  -0.0360   1.0001   0.1241
  -7.250  -0.5148   0.08012   0.07644  -0.0332   1.0001   0.1242
  -7.000  -0.5416   0.07821   0.07457  -0.0310   1.0001   0.1254
  -6.750  -0.5333   0.07234   0.06854  -0.0387   0.9901   0.1351
  -6.500  -0.5163   0.06735   0.06337  -0.0449   0.9785   0.1488
  -5.500  -0.4005   0.04192   0.03508  -0.0605   0.9400   0.0657
  -5.250  -0.3560   0.03780   0.03013  -0.0627   0.9343   0.0520
  -5.000  -0.3235   0.03471   0.02681  -0.0639   0.9253   0.0493
  -4.750  -0.2795   0.03182   0.02340  -0.0662   0.9200   0.0461
  -4.500  -0.2452   0.02993   0.02118  -0.0667   0.9105   0.0448
  -4.250  -0.2019   0.02806   0.01917  -0.0687   0.9052   0.0450
  -4.000  -0.1713   0.02674   0.01784  -0.0688   0.8952   0.0462
  -3.750  -0.1288   0.02527   0.01639  -0.0710   0.8899   0.0493
  -3.500  -0.0989   0.02418   0.01532  -0.0715   0.8794   0.0556
  -3.250  -0.0538   0.02260   0.01374  -0.0745   0.8747   0.0768
  -3.000  -0.0518   0.01969   0.01403  -0.0689   0.8644   0.6466
  -2.750  -0.0292   0.02144   0.01572  -0.0625   0.8587   0.7624
  -2.500  -0.0169   0.02283   0.01699  -0.0560   0.8469   0.7935
  -2.250   0.0233   0.02478   0.01874  -0.0513   0.8438   0.8379
  -2.000   0.1334   0.02543   0.01899  -0.0610   0.8450   0.8803
  -1.750   0.2037   0.02465   0.01793  -0.0689   0.8388   0.8913
  -1.500   0.2634   0.02388   0.01692  -0.0751   0.8306   0.9025
  -1.250   0.3039   0.02339   0.01624  -0.0778   0.8196   0.9132
  -1.000   0.3593   0.02268   0.01531  -0.0834   0.8110   0.9223
  -0.750   0.4025   0.02216   0.01464  -0.0867   0.7992   0.9318
  -0.500   0.4384   0.02181   0.01417  -0.0888   0.7874   0.9420
  -0.250   0.4728   0.02153   0.01376  -0.0906   0.7766   0.9508
   0.000   0.5177   0.02101   0.01309  -0.0944   0.7665   0.9579
   0.250   0.5466   0.02085   0.01286  -0.0953   0.7548   0.9657
   0.500   0.5829   0.02060   0.01253  -0.0977   0.7443   0.9732
   0.750   0.6262   0.02020   0.01201  -0.1013   0.7351   0.9800
   1.000   0.6588   0.02004   0.01183  -0.1030   0.7236   0.9871
   1.250   0.6944   0.01986   0.01159  -0.1054   0.7132   0.9928
   1.500   0.7348   0.01958   0.01123  -0.1084   0.7042   0.9976
   1.750   0.7590   0.01969   0.01137  -0.1086   0.6936   0.9999
   2.000   0.7795   0.01987   0.01150  -0.1077   0.6850   0.9999
   2.250   0.7987   0.02006   0.01169  -0.1067   0.6760   0.9999
   2.500   0.8163   0.02035   0.01202  -0.1054   0.6675   0.9999
   2.750   0.8377   0.02053   0.01218  -0.1046   0.6596   0.9999
   3.000   0.8526   0.02088   0.01258  -0.1028   0.6508   0.9999
   3.250   0.8760   0.02102   0.01268  -0.1023   0.6433   0.9999
   3.500   0.8880   0.02145   0.01320  -0.1000   0.6343   0.9999
   3.750   0.9132   0.02154   0.01327  -0.0998   0.6272   0.9999
   4.000   0.9222   0.02201   0.01386  -0.0969   0.6177   0.9999
   4.250   0.9497   0.02208   0.01388  -0.0970   0.6110   0.9999
   4.500   0.9546   0.02267   0.01463  -0.0934   0.6019   0.9999
   4.750   0.9824   0.02278   0.01470  -0.0936   0.5955   0.9999
   5.000   0.9843   0.02344   0.01553  -0.0894   0.5866   0.9999
   5.250   1.0115   0.02357   0.01565  -0.0895   0.5804   0.9999
   5.500   1.0108   0.02432   0.01658  -0.0850   0.5721   0.9999
   5.750   1.0371   0.02444   0.01669  -0.0848   0.5655   0.9999
   6.000   1.0356   0.02513   0.01754  -0.0801   0.5570   0.9999
   6.250   1.0648   0.02511   0.01753  -0.0803   0.5498   0.9999
   6.500   1.0584   0.02587   0.01845  -0.0747   0.5414   0.9999
   6.750   1.0903   0.02578   0.01835  -0.0753   0.5341   0.9999
   7.000   1.0788   0.02655   0.01930  -0.0689   0.5256   0.9999
   7.250   1.1056   0.02626   0.01902  -0.0684   0.5158   0.9999
   7.500   1.1155   0.02621   0.01902  -0.0651   0.5052   0.9999
   7.750   1.1150   0.02633   0.01923  -0.0601   0.4948   0.9999
   8.000   1.1327   0.02598   0.01888  -0.0580   0.4835   0.9999
   8.250   1.1562   0.02546   0.01832  -0.0568   0.4713   0.9999
   8.500   1.1520   0.02570   0.01873  -0.0514   0.4610   0.9999
   8.750   1.1642   0.02569   0.01881  -0.0489   0.4497   0.9999
   9.000   1.1840   0.02554   0.01872  -0.0476   0.4379   0.9999
   9.250   1.2061   0.02537   0.01858  -0.0466   0.4256   0.9999
   9.500   1.2175   0.02558   0.01897  -0.0444   0.4132   0.9999
   9.750   1.2294   0.02585   0.01941  -0.0423   0.4007   0.9999
  10.000   1.2436   0.02612   0.01983  -0.0406   0.3878   0.9999
  10.250   1.2572   0.02644   0.02028  -0.0390   0.3738   0.9999
  10.500   1.2690   0.02687   0.02085  -0.0372   0.3587   0.9999
  10.750   1.2776   0.02745   0.02157  -0.0352   0.3416   0.9999
  11.000   1.2835   0.02822   0.02244  -0.0332   0.3227   0.9999
  11.250   1.2871   0.02933   0.02366  -0.0312   0.3025   0.9999
  11.500   1.2863   0.03087   0.02529  -0.0293   0.2791   0.9999
  11.750   1.2812   0.03299   0.02745  -0.0277   0.2515   0.9999
  12.000   1.2714   0.03581   0.03019  -0.0263   0.2214   0.9999
  12.250   1.2570   0.03947   0.03373  -0.0255   0.1900   0.9999
  12.500   1.2398   0.04379   0.03790  -0.0252   0.1628   0.9999
  12.750   1.2221   0.04846   0.04243  -0.0253   0.1401   0.9999
  13.000   1.2057   0.05320   0.04704  -0.0256   0.1225   0.9999
  13.250   1.1928   0.05773   0.05148  -0.0259   0.1077   0.9999
  13.500   1.1844   0.06176   0.05543  -0.0262   0.0965   0.9999
  13.750   1.1822   0.06493   0.05851  -0.0259   0.0874   0.9999
  14.000   1.1856   0.06747   0.06102  -0.0254   0.0800   0.9999
  14.250   1.1949   0.06933   0.06290  -0.0246   0.0739   0.9999
  14.500   1.2021   0.07162   0.06523  -0.0245   0.0692   0.9999
  14.750   1.2155   0.07311   0.06667  -0.0236   0.0648   0.9999
  15.000   1.2231   0.07557   0.06934  -0.0235   0.0616   0.9999
  15.250   1.2330   0.07771   0.07153  -0.0234   0.0584   0.9999
  15.500   1.2484   0.07929   0.07309  -0.0223   0.0544   0.9999
  15.750   1.2435   0.08344   0.07757  -0.0237   0.0523   0.9999
  16.000   1.2389   0.08755   0.08191  -0.0252   0.0496   0.9999
  16.250   1.2405   0.09068   0.08502  -0.0263   0.0461   0.9999
  16.500   1.2376   0.09474   0.08923  -0.0273   0.0435   0.9999
  16.750   1.2273   0.09999   0.09479  -0.0297   0.0417   0.9999
  17.000   1.2197   0.10500   0.10002  -0.0320   0.0396   0.9999
  17.250   1.2223   0.10816   0.10315  -0.0331   0.0369   0.9999
  17.500   1.2141   0.11349   0.10867  -0.0349   0.0355   0.9999
  17.750   1.1978   0.12044   0.11593  -0.0388   0.0351   0.9999
  18.000   1.1805   0.12784   0.12361  -0.0433   0.0349   0.9999
  18.250   1.1621   0.13584   0.13187  -0.0485   0.0349   0.9999
  18.500   1.1433   0.14423   0.14048  -0.0541   0.0350   0.9999
  18.750   1.1239   0.15337   0.14981  -0.0606   0.0353   0.9999
  19.000   1.1044   0.16297   0.15956  -0.0673   0.0357   0.9999
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