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FX 61-163 AIRFOIL (fx61163-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: FX 61-163 AIRFOIL (fx61163-il)
Reynolds number: 500,000
Max Cl/Cd: 103.07 at α=6.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx61163-il-500000.txt
Download as CSV file: xf-fx61163-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 61-163 AIRFOIL                               
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.750  -0.3976   0.12666   0.12434  -0.0356   1.0001   0.0176
 -12.500  -0.4006   0.11920   0.11690  -0.0400   1.0001   0.0185
  -9.250  -0.4341   0.02883   0.02527  -0.0935   0.8215   0.0218
  -9.000  -0.4323   0.02634   0.02244  -0.0929   0.7920   0.0226
  -8.250  -0.4388   0.02514   0.01920  -0.0912   0.7723   0.0143
  -8.000  -0.4153   0.02452   0.01833  -0.0908   0.7551   0.0140
  -7.750  -0.3932   0.02229   0.01593  -0.0899   0.7424   0.0137
  -7.500  -0.3702   0.02088   0.01431  -0.0892   0.7315   0.0137
  -7.250  -0.3466   0.01980   0.01307  -0.0885   0.7220   0.0137
  -7.000  -0.3222   0.01897   0.01211  -0.0881   0.7132   0.0139
  -6.750  -0.3019   0.01748   0.01053  -0.0868   0.7060   0.0144
  -6.500  -0.2792   0.01659   0.00962  -0.0864   0.6988   0.0151
  -6.250  -0.2554   0.01586   0.00880  -0.0863   0.6928   0.0153
  -6.000  -0.2306   0.01514   0.00802  -0.0864   0.6872   0.0156
  -5.750  -0.2047   0.01448   0.00731  -0.0868   0.6817   0.0161
  -5.500  -0.1778   0.01393   0.00665  -0.0873   0.6769   0.0168
  -5.250  -0.1499   0.01341   0.00607  -0.0880   0.6720   0.0179
  -5.000  -0.1215   0.01289   0.00546  -0.0887   0.6673   0.0194
  -4.750  -0.0924   0.01243   0.00494  -0.0895   0.6631   0.0232
  -4.500  -0.0615   0.01130   0.00420  -0.0916   0.6591   0.1138
  -4.250  -0.0201   0.00879   0.00316  -0.0981   0.6546   0.4826
  -4.000   0.0117   0.00861   0.00315  -0.0992   0.6506   0.5476
  -3.750   0.0422   0.00872   0.00324  -0.0998   0.6469   0.5844
  -3.500   0.0723   0.00899   0.00349  -0.1001   0.6433   0.6129
  -3.250   0.1014   0.00928   0.00376  -0.1001   0.6395   0.6282
  -3.000   0.1292   0.00956   0.00403  -0.0998   0.6360   0.6371
  -2.750   0.1589   0.00973   0.00410  -0.1001   0.6328   0.6439
  -2.500   0.1875   0.00987   0.00421  -0.1002   0.6296   0.6474
  -2.250   0.2169   0.00991   0.00422  -0.1005   0.6260   0.6509
  -2.000   0.2472   0.00996   0.00419  -0.1012   0.6222   0.6555
  -1.750   0.2762   0.01003   0.00420  -0.1014   0.6186   0.6589
  -1.500   0.3049   0.01016   0.00428  -0.1016   0.6151   0.6616
  -1.250   0.3339   0.01020   0.00432  -0.1018   0.6118   0.6646
  -1.000   0.3637   0.01026   0.00435  -0.1023   0.6085   0.6685
  -0.750   0.3942   0.01030   0.00432  -0.1031   0.6053   0.6722
  -0.500   0.4227   0.01036   0.00436  -0.1032   0.6022   0.6743
  -0.250   0.4516   0.01045   0.00443  -0.1035   0.5990   0.6765
   0.000   0.4805   0.01048   0.00448  -0.1038   0.5957   0.6790
   0.250   0.5100   0.01051   0.00450  -0.1042   0.5920   0.6819
   0.500   0.5400   0.01056   0.00449  -0.1049   0.5883   0.6852
   0.750   0.5698   0.01062   0.00450  -0.1054   0.5846   0.6876
   1.000   0.5980   0.01062   0.00455  -0.1056   0.5809   0.6894
   1.250   0.6266   0.01066   0.00461  -0.1058   0.5773   0.6915
   1.500   0.6556   0.01071   0.00466  -0.1061   0.5739   0.6939
   1.750   0.6851   0.01082   0.00473  -0.1066   0.5704   0.6965
   2.000   0.7144   0.01083   0.00477  -0.1071   0.5665   0.6993
   2.250   0.7441   0.01085   0.00480  -0.1076   0.5624   0.7018
   2.500   0.7724   0.01087   0.00484  -0.1078   0.5587   0.7036
   2.750   0.8008   0.01094   0.00492  -0.1081   0.5545   0.7054
   3.000   0.8288   0.01094   0.00498  -0.1082   0.5492   0.7076
   3.250   0.8574   0.01097   0.00504  -0.1085   0.5444   0.7099
   3.500   0.8865   0.01107   0.00511  -0.1089   0.5404   0.7123
   3.750   0.9153   0.01107   0.00518  -0.1093   0.5349   0.7145
   4.000   0.9441   0.01109   0.00520  -0.1097   0.5289   0.7167
   4.250   0.9716   0.01111   0.00527  -0.1097   0.5229   0.7185
   4.500   0.9993   0.01113   0.00536  -0.1098   0.5167   0.7203
   4.750   1.0267   0.01119   0.00543  -0.1099   0.5095   0.7222
   5.000   1.0542   0.01119   0.00549  -0.1100   0.5000   0.7242
   5.250   1.0818   0.01125   0.00558  -0.1101   0.4908   0.7264
   5.500   1.1092   0.01135   0.00566  -0.1102   0.4815   0.7288
   5.750   1.1370   0.01144   0.00579  -0.1104   0.4706   0.7309
   6.000   1.1638   0.01152   0.00592  -0.1104   0.4608   0.7326
   6.250   1.1899   0.01166   0.00609  -0.1103   0.4509   0.7344
   6.500   1.2156   0.01183   0.00628  -0.1101   0.4388   0.7364
   6.750   1.2409   0.01204   0.00650  -0.1098   0.4243   0.7384
   7.000   1.2653   0.01231   0.00675  -0.1095   0.4052   0.7406
   7.250   1.2885   0.01268   0.00705  -0.1089   0.3824   0.7429
   7.500   1.3115   0.01309   0.00738  -0.1084   0.3597   0.7450
   7.750   1.3325   0.01358   0.00780  -0.1076   0.3352   0.7467
   8.000   1.3523   0.01411   0.00825  -0.1066   0.3072   0.7486
   8.250   1.3699   0.01478   0.00880  -0.1052   0.2762   0.7505
   8.500   1.3859   0.01555   0.00943  -0.1036   0.2421   0.7525
   8.750   1.4001   0.01642   0.01014  -0.1018   0.2106   0.7545
   9.000   1.4108   0.01743   0.01098  -0.0996   0.1789   0.7566
   9.250   1.4208   0.01837   0.01182  -0.0971   0.1531   0.7588
   9.500   1.4267   0.01935   0.01268  -0.0940   0.1308   0.7609
   9.750   1.4314   0.02051   0.01375  -0.0911   0.1084   0.7630
  10.000   1.4362   0.02172   0.01489  -0.0883   0.0896   0.7649
  10.250   1.4403   0.02305   0.01618  -0.0858   0.0737   0.7670
  10.500   1.4429   0.02462   0.01770  -0.0834   0.0611   0.7692
  10.750   1.4476   0.02620   0.01930  -0.0817   0.0523   0.7715
  11.000   1.4527   0.02794   0.02105  -0.0804   0.0432   0.7739
  11.250   1.4528   0.03022   0.02330  -0.0791   0.0328   0.7762
  11.500   1.4546   0.03247   0.02558  -0.0781   0.0266   0.7784
  11.750   1.4561   0.03485   0.02803  -0.0772   0.0218   0.7806
  12.000   1.4568   0.03740   0.03063  -0.0765   0.0178   0.7829
  12.250   1.4574   0.04001   0.03330  -0.0758   0.0140   0.7852
  12.500   1.4550   0.04293   0.03628  -0.0752   0.0107   0.7876
  13.000   1.4521   0.04868   0.04218  -0.0740   0.0077   0.7922
  13.250   1.4510   0.05152   0.04513  -0.0736   0.0070   0.7947
  13.500   1.4482   0.05463   0.04833  -0.0732   0.0065   0.7975
  13.750   1.4439   0.05799   0.05180  -0.0729   0.0061   0.8002
  14.000   1.4410   0.06128   0.05520  -0.0727   0.0059   0.8030
  14.250   1.4388   0.06459   0.05862  -0.0727   0.0058   0.8057
  14.500   1.4357   0.06805   0.06222  -0.0728   0.0056   0.8084
  14.750   1.4323   0.07162   0.06591  -0.0729   0.0055   0.8115
  15.000   1.4281   0.07537   0.06978  -0.0732   0.0054   0.8148
  15.250   1.4238   0.07923   0.07375  -0.0737   0.0052   0.8183
  15.500   1.4193   0.08318   0.07784  -0.0742   0.0051   0.8217
  15.750   1.4139   0.08728   0.08207  -0.0748   0.0050   0.8255
  16.000   1.4084   0.09146   0.08638  -0.0756   0.0049   0.8299
  16.250   1.4021   0.09587   0.09091  -0.0765   0.0048   0.8347
  16.500   1.3962   0.10025   0.09541  -0.0776   0.0047   0.8401
  16.750   1.3887   0.10494   0.10022  -0.0788   0.0046   0.8464
  17.000   1.3805   0.10974   0.10516  -0.0801   0.0045   0.8534
  17.250   1.3711   0.11484   0.11039  -0.0816   0.0044   0.8621
  17.500   1.3630   0.11971   0.11542  -0.0831   0.0044   0.8738
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