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FX 61-163 AIRFOIL (fx61163-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: FX 61-163 AIRFOIL (fx61163-il)
Reynolds number: 100,000
Max Cl/Cd: 47.75 at α=10.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx61163-il-100000.txt
Download as CSV file: xf-fx61163-il-100000.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 =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.3843   0.10360   0.09908  -0.0453   1.0001   0.1414
 -10.000  -0.3698   0.10117   0.09667  -0.0438   1.0001   0.1477
  -9.750  -0.3933   0.09613   0.09179  -0.0474   1.0001   0.1558
  -9.500  -0.3755   0.09405   0.08973  -0.0451   1.0001   0.1627
  -7.500  -0.4693   0.04247   0.03594  -0.0805   0.9369   0.0641
  -7.250  -0.4260   0.03837   0.03086  -0.0835   0.9310   0.0545
  -7.000  -0.3925   0.03461   0.02683  -0.0852   0.9216   0.0528
  -6.750  -0.3512   0.03159   0.02346  -0.0876   0.9155   0.0518
  -6.500  -0.3143   0.02948   0.02105  -0.0888   0.9065   0.0526
  -6.250  -0.2756   0.02798   0.01927  -0.0903   0.8986   0.0554
  -6.000  -0.2421   0.02585   0.01729  -0.0905   0.8910   0.0586
  -5.750  -0.2110   0.02464   0.01613  -0.0904   0.8826   0.0625
  -5.500  -0.1810   0.02362   0.01504  -0.0903   0.8743   0.0685
  -5.250  -0.1600   0.02255   0.01404  -0.0899   0.8642   0.0823
  -5.000  -0.1441   0.01925   0.01202  -0.0916   0.8559   0.2552
  -4.750  -0.1329   0.02202   0.01625  -0.0835   0.8470   0.6130
  -4.500  -0.1098   0.02643   0.02058  -0.0738   0.8414   0.6457
  -4.250  -0.0864   0.02992   0.02397  -0.0651   0.8340   0.6744
  -4.000  -0.0492   0.03167   0.02550  -0.0610   0.8290   0.6967
  -3.750  -0.0273   0.03162   0.02529  -0.0598   0.8217   0.7072
  -3.500  -0.0060   0.03134   0.02484  -0.0594   0.8150   0.7187
  -3.250   0.0165   0.03122   0.02455  -0.0586   0.8086   0.7285
  -3.000   0.0398   0.03104   0.02424  -0.0578   0.8020   0.7366
  -2.750   0.0611   0.03068   0.02370  -0.0578   0.7968   0.7468
  -2.500   0.0813   0.03062   0.02358  -0.0564   0.7896   0.7532
  -2.250   0.1006   0.03033   0.02315  -0.0561   0.7841   0.7622
  -2.000   0.1234   0.03022   0.02296  -0.0552   0.7784   0.7689
  -1.750   0.1383   0.03008   0.02275  -0.0542   0.7720   0.7773
  -1.500   0.1669   0.02983   0.02236  -0.0542   0.7676   0.7835
  -1.250   0.1751   0.02988   0.02240  -0.0526   0.7606   0.7911
  -1.000   0.2005   0.02968   0.02212  -0.0522   0.7553   0.7964
  -0.750   0.2217   0.02955   0.02189  -0.0522   0.7505   0.8033
  -0.500   0.2339   0.02962   0.02197  -0.0503   0.7432   0.8086
  -0.250   0.2605   0.02941   0.02167  -0.0504   0.7385   0.8142
   0.000   0.2721   0.02960   0.02185  -0.0493   0.7318   0.8203
   0.250   0.2929   0.02953   0.02175  -0.0483   0.7259   0.8248
   0.500   0.3231   0.02929   0.02141  -0.0491   0.7220   0.8299
   0.750   0.3287   0.02980   0.02198  -0.0474   0.7138   0.8351
   1.000   0.3547   0.02963   0.02176  -0.0471   0.7090   0.8391
   1.250   0.3741   0.02981   0.02193  -0.0466   0.7032   0.8440
   1.500   0.3923   0.03016   0.02228  -0.0468   0.6960   0.8488
   1.750   0.4230   0.02981   0.02189  -0.0469   0.6922   0.8525
   2.000   0.4286   0.03055   0.02271  -0.0448   0.6832   0.8573
   2.250   0.4616   0.03037   0.02249  -0.0461   0.6784   0.8614
   2.500   0.4751   0.03091   0.02308  -0.0451   0.6707   0.8656
   2.750   0.4991   0.03092   0.02309  -0.0448   0.6645   0.8697
   3.000   0.5381   0.03050   0.02263  -0.0464   0.6613   0.8734
   3.250   0.5446   0.03170   0.02395  -0.0454   0.6506   0.8780
   3.500   0.5776   0.03125   0.02348  -0.0457   0.6470   0.8815
   3.750   0.5826   0.03244   0.02477  -0.0441   0.6367   0.8857
   4.000   0.6202   0.03207   0.02441  -0.0455   0.6326   0.8895
   4.250   0.6292   0.03330   0.02575  -0.0447   0.6226   0.8936
   4.500   0.6613   0.03291   0.02538  -0.0450   0.6181   0.8973
   4.750   0.6722   0.03400   0.02657  -0.0441   0.6082   0.9013
   5.000   0.7094   0.03359   0.02621  -0.0454   0.6034   0.9051
   5.250   0.7487   0.03290   0.02552  -0.0464   0.5999   0.9087
   5.500   0.7520   0.03421   0.02698  -0.0445   0.5885   0.9131
   5.750   0.7973   0.03325   0.02605  -0.0462   0.5858   0.9168
   6.000   0.8003   0.03499   0.02796  -0.0450   0.5737   0.9214
   6.250   0.8451   0.03371   0.02670  -0.0461   0.5710   0.9252
   6.500   0.8488   0.03516   0.02832  -0.0445   0.5588   0.9302
   6.750   0.8900   0.03425   0.02747  -0.0458   0.5536   0.9343
   7.000   0.9058   0.03465   0.02801  -0.0447   0.5439   0.9392
   7.250   0.9575   0.03296   0.02637  -0.0466   0.5409   0.9433
   7.500   0.9651   0.03409   0.02768  -0.0453   0.5289   0.9489
   7.750   0.9808   0.03446   0.02820  -0.0442   0.5188   0.9551
   8.000   1.0318   0.03256   0.02636  -0.0459   0.5133   0.9602
   8.250   1.0486   0.03296   0.02697  -0.0452   0.5027   0.9669
   8.500   1.1086   0.03055   0.02457  -0.0479   0.4969   0.9724
   8.750   1.1318   0.03045   0.02467  -0.0478   0.4846   0.9821
   9.000   1.1631   0.02985   0.02422  -0.0485   0.4721   0.9999
   9.250   1.1989   0.02898   0.02347  -0.0495   0.4587   0.9999
   9.500   1.2337   0.02814   0.02273  -0.0505   0.4436   0.9999
   9.750   1.2651   0.02773   0.02241  -0.0512   0.4281   0.9999
  10.000   1.2960   0.02744   0.02217  -0.0519   0.4111   0.9999
  10.250   1.3150   0.02760   0.02242  -0.0514   0.3900   0.9999
  10.500   1.3297   0.02785   0.02268  -0.0502   0.3665   0.9999
  10.750   1.3360   0.02883   0.02373  -0.0487   0.3422   0.9999
  11.000   1.3419   0.03009   0.02498  -0.0475   0.3179   0.9999
  11.250   1.3443   0.03182   0.02671  -0.0466   0.2939   0.9999
  11.500   1.3431   0.03413   0.02903  -0.0460   0.2695   0.9999
  11.750   1.3399   0.03684   0.03167  -0.0456   0.2454   0.9999
  12.000   1.3344   0.03998   0.03473  -0.0455   0.2223   0.9999
  12.250   1.3277   0.04345   0.03814  -0.0456   0.2000   0.9999
  12.500   1.3199   0.04708   0.04163  -0.0457   0.1799   0.9999
  12.750   1.3119   0.05081   0.04524  -0.0457   0.1607   0.9999
  13.000   1.3036   0.05469   0.04905  -0.0458   0.1428   0.9999
  13.250   1.2957   0.05852   0.05278  -0.0459   0.1272   0.9999
  13.500   1.2895   0.06226   0.05644  -0.0460   0.1134   0.9999
  13.750   1.2849   0.06590   0.06006  -0.0461   0.1013   0.9999
  14.000   1.2827   0.06931   0.06343  -0.0462   0.0911   0.9999
  14.250   1.2797   0.07280   0.06684  -0.0465   0.0823   0.9999
  14.500   1.2732   0.07707   0.07122  -0.0478   0.0748   0.9999
  14.750   1.2687   0.08101   0.07520  -0.0486   0.0678   0.9999
  15.000   1.2632   0.08512   0.07927  -0.0497   0.0615   0.9999
  15.250   1.2599   0.08908   0.08338  -0.0504   0.0554   0.9999
  15.500   1.2612   0.09189   0.08600  -0.0499   0.0486   0.9999
  15.750   1.2548   0.09665   0.09107  -0.0511   0.0442   0.9999
  16.000   1.2560   0.09981   0.09415  -0.0513   0.0399   0.9999
  16.250   1.2578   0.10317   0.09768  -0.0509   0.0371   0.9999
  16.500   1.2552   0.10746   0.10221  -0.0518   0.0353   0.9999
  16.750   1.2512   0.11197   0.10693  -0.0531   0.0340   0.9999
  17.000   1.2464   0.11668   0.11182  -0.0548   0.0330   0.9999
  17.250   1.2418   0.12137   0.11665  -0.0567   0.0320   0.9999
  17.500   1.2389   0.12577   0.12114  -0.0584   0.0311   0.9999
  17.750   1.2326   0.13092   0.12642  -0.0606   0.0304   0.9999
  18.000   1.2190   0.13773   0.13345  -0.0644   0.0302   0.9999
  18.250   1.2023   0.14553   0.14150  -0.0696   0.0304   0.9999
  18.500   1.1226   0.17121   0.16792  -0.0887   0.0349   0.9999
  18.750   1.0848   0.18838   0.18518  -0.1004   0.0373   0.9999
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