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FX 63-147 AIRFOIL (fx63147-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: FX 63-147 AIRFOIL (fx63147-il)
Reynolds number: 200,000
Max Cl/Cd: 63.81 at α=7°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx63147-il-200000-n5.txt
Download as CSV file: xf-fx63147-il-200000-n5.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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.4539   0.06447   0.06101  -0.0641   0.9969   0.0110
  -9.000  -0.4612   0.05845   0.05479  -0.0698   0.9903   0.0110
  -8.500  -0.4515   0.05326   0.04941  -0.0750   0.9733   0.0117
  -8.250  -0.4515   0.04825   0.04411  -0.0764   0.9611   0.0117
  -8.000  -0.4440   0.04533   0.04099  -0.0766   0.9497   0.0121
  -7.750  -0.4366   0.04157   0.03692  -0.0764   0.9383   0.0123
  -7.500  -0.4272   0.03693   0.03181  -0.0760   0.9281   0.0119
  -7.250  -0.4140   0.03123   0.02517  -0.0750   0.9193   0.0111
  -7.000  -0.3945   0.02898   0.02263  -0.0745   0.9091   0.0110
  -6.750  -0.3655   0.02671   0.02005  -0.0755   0.9039   0.0109
  -6.500  -0.3413   0.02490   0.01798  -0.0753   0.8938   0.0108
  -6.250  -0.3079   0.02310   0.01590  -0.0767   0.8881   0.0108
  -6.000  -0.2791   0.02166   0.01427  -0.0770   0.8778   0.0108
  -5.750  -0.2442   0.02029   0.01273  -0.0785   0.8694   0.0108
  -5.500  -0.2065   0.01905   0.01135  -0.0806   0.8604   0.0108
  -5.250  -0.1679   0.01797   0.01014  -0.0831   0.8492   0.0109
  -5.000  -0.1267   0.01701   0.00906  -0.0862   0.8372   0.0110
  -4.750  -0.0878   0.01619   0.00813  -0.0889   0.8235   0.0113
  -4.500  -0.0514   0.01556   0.00736  -0.0911   0.8087   0.0117
  -4.250  -0.0185   0.01508   0.00673  -0.0924   0.7935   0.0122
  -4.000   0.0118   0.01470   0.00619  -0.0932   0.7781   0.0130
  -3.750   0.0408   0.01440   0.00572  -0.0936   0.7637   0.0142
  -3.500   0.0687   0.01410   0.00528  -0.0939   0.7500   0.0168
  -3.250   0.0950   0.01376   0.00489  -0.0939   0.7363   0.0246
  -3.000   0.1210   0.01339   0.00460  -0.0939   0.7230   0.0686
  -2.750   0.1450   0.01189   0.00414  -0.0952   0.7104   0.3301
  -2.500   0.1745   0.01100   0.00399  -0.0966   0.6986   0.5293
  -2.250   0.1964   0.01092   0.00427  -0.0950   0.6872   0.6356
  -2.000   0.2150   0.01124   0.00470  -0.0922   0.6757   0.6988
  -1.750   0.2384   0.01157   0.00498  -0.0908   0.6649   0.7321
  -1.500   0.2599   0.01200   0.00533  -0.0887   0.6552   0.7524
  -1.250   0.2802   0.01253   0.00580  -0.0863   0.6457   0.7711
  -1.000   0.3052   0.01278   0.00594  -0.0855   0.6371   0.7802
  -0.750   0.3292   0.01296   0.00602  -0.0845   0.6288   0.7844
  -0.500   0.3580   0.01304   0.00599  -0.0849   0.6205   0.7913
  -0.250   0.3826   0.01319   0.00603  -0.0842   0.6125   0.7949
   0.000   0.4065   0.01332   0.00611  -0.0833   0.6047   0.7980
   0.250   0.4325   0.01345   0.00615  -0.0829   0.5976   0.8024
   0.500   0.4623   0.01352   0.00614  -0.0837   0.5900   0.8085
   0.750   0.4841   0.01368   0.00625  -0.0822   0.5825   0.8113
   1.000   0.5079   0.01380   0.00633  -0.0814   0.5750   0.8147
   1.250   0.5347   0.01390   0.00637  -0.0814   0.5676   0.8194
   1.500   0.5634   0.01399   0.00641  -0.0819   0.5607   0.8241
   1.750   0.5858   0.01411   0.00651  -0.0807   0.5539   0.8265
   2.000   0.6104   0.01422   0.00657  -0.0801   0.5479   0.8293
   2.250   0.6367   0.01431   0.00667  -0.0800   0.5414   0.8325
   2.500   0.6660   0.01441   0.00673  -0.0807   0.5354   0.8361
   2.750   0.6952   0.01449   0.00680  -0.0814   0.5291   0.8391
   3.000   0.7179   0.01459   0.00691  -0.0804   0.5227   0.8412
   3.250   0.7413   0.01472   0.00703  -0.0796   0.5165   0.8438
   3.500   0.7659   0.01482   0.00717  -0.0791   0.5093   0.8471
   3.750   0.7937   0.01496   0.00727  -0.0795   0.5030   0.8505
   4.000   0.8244   0.01507   0.00742  -0.0805   0.4955   0.8536
   4.250   0.8467   0.01519   0.00756  -0.0795   0.4892   0.8555
   4.500   0.8699   0.01530   0.00772  -0.0788   0.4828   0.8577
   4.750   0.8937   0.01542   0.00786  -0.0782   0.4748   0.8600
   5.000   0.9180   0.01553   0.00801  -0.0778   0.4642   0.8625
   5.250   0.9425   0.01567   0.00814  -0.0776   0.4505   0.8654
   5.500   0.9693   0.01584   0.00831  -0.0779   0.4357   0.8683
   5.750   0.9885   0.01598   0.00845  -0.0764   0.4242   0.8702
   6.000   1.0085   0.01614   0.00864  -0.0751   0.4124   0.8723
   6.250   1.0292   0.01633   0.00886  -0.0740   0.3988   0.8748
   6.500   1.0507   0.01656   0.00909  -0.0732   0.3838   0.8774
   6.750   1.0729   0.01683   0.00936  -0.0727   0.3686   0.8802
   7.000   1.0956   0.01717   0.00968  -0.0723   0.3516   0.8827
   7.250   1.1107   0.01747   0.00999  -0.0703   0.3347   0.8847
   7.500   1.1284   0.01783   0.01035  -0.0689   0.3169   0.8867
   7.750   1.1469   0.01824   0.01077  -0.0677   0.3001   0.8889
   8.000   1.1648   0.01873   0.01126  -0.0665   0.2822   0.8916
   8.250   1.1825   0.01935   0.01185  -0.0655   0.2599   0.8941
   8.500   1.1988   0.02016   0.01258  -0.0645   0.2333   0.8964
   8.750   1.2102   0.02097   0.01333  -0.0625   0.2066   0.8984
   9.000   1.2166   0.02199   0.01424  -0.0599   0.1788   0.9005
   9.250   1.2243   0.02304   0.01524  -0.0576   0.1536   0.9030
   9.500   1.2301   0.02433   0.01645  -0.0554   0.1302   0.9058
   9.750   1.2392   0.02558   0.01768  -0.0538   0.1088   0.9082
  10.000   1.2470   0.02706   0.01913  -0.0525   0.0929   0.9103
  10.250   1.2528   0.02851   0.02060  -0.0509   0.0787   0.9122
  10.500   1.2538   0.03021   0.02228  -0.0487   0.0619   0.9143
  10.750   1.2561   0.03198   0.02408  -0.0471   0.0537   0.9167
  11.000   1.2610   0.03374   0.02591  -0.0460   0.0435   0.9191
  11.250   1.2637   0.03588   0.02808  -0.0451   0.0349   0.9212
  11.500   1.2665   0.03820   0.03044  -0.0446   0.0313   0.9231
  11.750   1.2702   0.04059   0.03291  -0.0444   0.0286   0.9247
  12.000   1.2745   0.04255   0.03501  -0.0437   0.0267   0.9267
  12.250   1.2773   0.04468   0.03728  -0.0430   0.0245   0.9289
  12.500   1.2792   0.04710   0.03982  -0.0426   0.0227   0.9310
  12.750   1.2805   0.04972   0.04257  -0.0425   0.0214   0.9329
  13.000   1.2837   0.05230   0.04529  -0.0426   0.0203   0.9346
  13.250   1.2863   0.05505   0.04817  -0.0429   0.0191   0.9362
  13.500   1.2877   0.05798   0.05121  -0.0433   0.0179   0.9377
  13.750   1.2874   0.06107   0.05439  -0.0436   0.0169   0.9392
  14.000   1.2855   0.06410   0.05754  -0.0436   0.0163   0.9411
  14.250   1.2836   0.06724   0.06081  -0.0438   0.0159   0.9433
  14.500   1.2816   0.07051   0.06420  -0.0441   0.0154   0.9453
  14.750   1.2798   0.07399   0.06780  -0.0448   0.0150   0.9471
  15.000   1.2773   0.07760   0.07154  -0.0456   0.0146   0.9488
  15.250   1.2746   0.08142   0.07549  -0.0465   0.0143   0.9503
  15.750   1.2652   0.08929   0.08361  -0.0483   0.0136   0.9536
  16.000   1.2587   0.09346   0.08789  -0.0492   0.0132   0.9554
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