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FX 63-147 AIRFOIL (fx63147-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: FX 63-147 AIRFOIL (fx63147-il)
Reynolds number: 200,000
Max Cl/Cd: 68.55 at α=8.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx63147-il-200000.txt
Download as CSV file: xf-fx63147-il-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.3122   0.08927   0.08648  -0.0395   1.0001   0.0499
  -9.000  -0.4035   0.08515   0.08209  -0.0502   1.0001   0.0449
  -8.750  -0.4315   0.07986   0.07684  -0.0525   1.0001   0.0447
  -8.000  -0.4809   0.07043   0.06738  -0.0540   0.9922   0.0455
  -7.750  -0.4638   0.06570   0.06254  -0.0600   0.9848   0.0474
  -7.500  -0.4542   0.06030   0.05667  -0.0664   0.9721   0.0518
  -7.250  -0.4454   0.05442   0.05052  -0.0698   0.9622   0.0545
  -7.000  -0.4213   0.05181   0.04797  -0.0713   0.9552   0.0579
  -6.500  -0.3787   0.04453   0.04021  -0.0759   0.9383   0.0693
  -6.250  -0.3493   0.04077   0.03590  -0.0793   0.9332   0.0784
  -6.000  -0.3260   0.03792   0.03305  -0.0798   0.9231   0.0816
  -5.750  -0.2834   0.02969   0.02307  -0.0785   0.9195   0.0350
  -5.500  -0.2559   0.02605   0.01935  -0.0785   0.9115   0.0309
  -5.250  -0.2174   0.02341   0.01617  -0.0793   0.9071   0.0271
  -5.000  -0.1776   0.02127   0.01389  -0.0810   0.9043   0.0260
  -4.750  -0.1476   0.01977   0.01228  -0.0809   0.8947   0.0254
  -4.500  -0.1067   0.01826   0.01070  -0.0830   0.8901   0.0251
  -4.250  -0.0724   0.01711   0.00953  -0.0842   0.8802   0.0254
  -4.000  -0.0261   0.01592   0.00828  -0.0880   0.8740   0.0264
  -3.500   0.0511   0.01436   0.00650  -0.0928   0.8498   0.0335
  -3.250   0.0863   0.01229   0.00543  -0.0961   0.8364   0.2672
  -3.000   0.1185   0.01080   0.00541  -0.0980   0.8226   0.6234
  -2.750   0.1407   0.01136   0.00612  -0.0952   0.8083   0.7157
  -2.500   0.1675   0.01193   0.00655  -0.0938   0.7943   0.7440
  -2.250   0.1933   0.01253   0.00699  -0.0923   0.7804   0.7630
  -2.000   0.2119   0.01340   0.00776  -0.0886   0.7667   0.7789
  -1.750   0.2299   0.01422   0.00847  -0.0850   0.7536   0.7934
  -1.500   0.2471   0.01502   0.00919  -0.0808   0.7417   0.8037
  -1.250   0.2667   0.01589   0.00995  -0.0769   0.7312   0.8192
  -1.000   0.2903   0.01625   0.01018  -0.0749   0.7209   0.8287
  -0.750   0.3127   0.01630   0.01013  -0.0743   0.7100   0.8387
  -0.500   0.3381   0.01636   0.01007  -0.0732   0.7007   0.8423
  -0.250   0.3621   0.01642   0.01003  -0.0723   0.6910   0.8489
   0.000   0.3845   0.01645   0.00998  -0.0712   0.6818   0.8562
   0.250   0.4114   0.01648   0.00988  -0.0709   0.6737   0.8611
   0.500   0.4309   0.01648   0.00984  -0.0697   0.6643   0.8690
   0.750   0.4581   0.01645   0.00970  -0.0693   0.6564   0.8727
   1.000   0.4786   0.01645   0.00967  -0.0680   0.6472   0.8797
   1.250   0.5032   0.01644   0.00958  -0.0674   0.6399   0.8855
   1.500   0.5261   0.01640   0.00952  -0.0664   0.6315   0.8910
   1.750   0.5482   0.01646   0.00950  -0.0657   0.6246   0.8974
   2.000   0.5719   0.01635   0.00939  -0.0648   0.6166   0.9014
   2.250   0.5993   0.01638   0.00933  -0.0649   0.6103   0.9066
   2.500   0.6165   0.01635   0.00935  -0.0631   0.6027   0.9129
   2.750   0.6455   0.01632   0.00925  -0.0635   0.5962   0.9163
   3.000   0.6646   0.01631   0.00927  -0.0621   0.5886   0.9210
   3.250   0.6861   0.01634   0.00925  -0.0612   0.5818   0.9257
   3.500   0.7096   0.01626   0.00922  -0.0606   0.5744   0.9290
   3.750   0.7343   0.01625   0.00918  -0.0602   0.5673   0.9325
   4.000   0.7535   0.01630   0.00924  -0.0589   0.5605   0.9371
   4.250   0.7763   0.01626   0.00921  -0.0582   0.5533   0.9408
   4.500   0.8033   0.01628   0.00924  -0.0583   0.5468   0.9445
   4.750   0.8218   0.01629   0.00931  -0.0569   0.5395   0.9491
   5.000   0.8471   0.01638   0.00934  -0.0567   0.5332   0.9521
   5.250   0.8662   0.01625   0.00932  -0.0553   0.5237   0.9556
   5.500   0.8869   0.01618   0.00924  -0.0542   0.5139   0.9593
   5.750   0.9036   0.01610   0.00914  -0.0523   0.5038   0.9630
   6.000   0.9209   0.01598   0.00909  -0.0506   0.4930   0.9663
   6.250   0.9445   0.01596   0.00908  -0.0501   0.4838   0.9697
   6.500   0.9626   0.01592   0.00907  -0.0486   0.4742   0.9735
   6.750   0.9810   0.01588   0.00911  -0.0472   0.4633   0.9768
   7.000   1.0053   0.01590   0.00916  -0.0470   0.4532   0.9801
   7.250   1.0253   0.01592   0.00921  -0.0460   0.4427   0.9838
   7.500   1.0462   0.01597   0.00936  -0.0453   0.4315   0.9875
   7.750   1.0673   0.01604   0.00949  -0.0446   0.4198   0.9915
   8.000   1.0883   0.01618   0.00965  -0.0439   0.4098   0.9950
   8.250   1.1131   0.01633   0.00989  -0.0441   0.3977   0.9978
   8.500   1.1256   0.01642   0.01008  -0.0418   0.3871   0.9999
   8.750   1.1381   0.01663   0.01034  -0.0397   0.3763   0.9999
   9.000   1.1539   0.01692   0.01068  -0.0383   0.3640   0.9999
   9.250   1.1708   0.01731   0.01110  -0.0372   0.3503   0.9999
   9.500   1.1892   0.01776   0.01164  -0.0365   0.3355   0.9999
   9.750   1.2068   0.01830   0.01224  -0.0357   0.3189   0.9999
  10.000   1.2242   0.01892   0.01293  -0.0351   0.3004   0.9999
  10.250   1.2389   0.01973   0.01375  -0.0342   0.2793   0.9999
  10.500   1.2492   0.02083   0.01481  -0.0331   0.2493   0.9999
  10.750   1.2543   0.02235   0.01622  -0.0316   0.2168   0.9999
  11.000   1.2553   0.02433   0.01804  -0.0302   0.1788   0.9999
  11.250   1.2532   0.02675   0.02029  -0.0289   0.1418   0.9999
  11.500   1.2493   0.02952   0.02292  -0.0280   0.1103   0.9999
  11.750   1.2443   0.03261   0.02589  -0.0275   0.0865   0.9999
  12.000   1.2408   0.03574   0.02898  -0.0273   0.0662   0.9999
  12.250   1.2357   0.03917   0.03236  -0.0273   0.0571   0.9999
  12.500   1.2361   0.04224   0.03554  -0.0278   0.0500   0.9999
  12.750   1.2334   0.04570   0.03908  -0.0283   0.0455   0.9999
  13.000   1.2344   0.04884   0.04234  -0.0290   0.0424   0.9999
  13.250   1.2363   0.05194   0.04557  -0.0297   0.0398   0.9999
  13.500   1.2357   0.05535   0.04906  -0.0306   0.0378   0.9999
  13.750   1.2312   0.05927   0.05305  -0.0315   0.0361   0.9999
  14.000   1.2323   0.06263   0.05653  -0.0325   0.0348   0.9999
  14.250   1.2328   0.06606   0.06009  -0.0335   0.0336   0.9999
  14.500   1.2327   0.06955   0.06369  -0.0345   0.0326   0.9999
  14.750   1.2328   0.07313   0.06738  -0.0356   0.0316   0.9999
  15.000   1.2320   0.07676   0.07110  -0.0366   0.0306   0.9999
  15.250   1.2307   0.08043   0.07483  -0.0376   0.0296   0.9999
  15.500   1.2290   0.08376   0.07817  -0.0380   0.0282   0.9999
  15.750   1.2325   0.08719   0.08181  -0.0394   0.0270   0.9999
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