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WORTMANN FX 66-17AII-182 AIRFOIL (AS TESTED AT NASA) (fx6617ai-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: WORTMANN FX 66-17AII-182 AIRFOIL (AS TESTED AT NASA) (fx6617ai-il)
Reynolds number: 50,000
Max Cl/Cd: 8.28 at α=4.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx6617ai-il-50000-n5.txt
Download as CSV file: xf-fx6617ai-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: WORTMANN FX 66-17AII-182 AIRFOIL (AS TESTED AT N
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.750  -0.3790   0.09630   0.09030  -0.0687   0.9577   0.0525
 -11.500  -0.3856   0.08892   0.08282  -0.0751   0.9134   0.0522
 -11.250  -0.3985   0.08168   0.07541  -0.0812   0.8838   0.0518
 -11.000  -0.4152   0.07536   0.06886  -0.0860   0.8601   0.0515
 -10.750  -0.4327   0.07006   0.06330  -0.0894   0.8400   0.0512
 -10.500  -0.4485   0.06557   0.05851  -0.0918   0.8230   0.0511
 -10.250  -0.4619   0.06175   0.05436  -0.0931   0.8086   0.0510
 -10.000  -0.4726   0.05861   0.05087  -0.0932   0.7967   0.0510
  -9.750  -0.4764   0.05553   0.04740  -0.0931   0.7859   0.0513
  -9.500  -0.4759   0.05269   0.04410  -0.0929   0.7762   0.0518
  -9.250  -0.4703   0.05009   0.04105  -0.0924   0.7680   0.0528
  -9.000  -0.4551   0.04796   0.03882  -0.0923   0.7593   0.0544
  -8.750  -0.4394   0.04607   0.03668  -0.0919   0.7523   0.0562
  -8.500  -0.4215   0.04418   0.03454  -0.0916   0.7447   0.0579
  -8.250  -0.4006   0.04233   0.03235  -0.0910   0.7382   0.0594
  -8.000  -0.3769   0.04072   0.03043  -0.0905   0.7319   0.0613
  -7.750  -0.3520   0.03941   0.02883  -0.0899   0.7256   0.0641
  -7.500  -0.3279   0.03828   0.02771  -0.0892   0.7206   0.0681
  -7.250  -0.3039   0.03738   0.02667  -0.0885   0.7148   0.0725
  -7.000  -0.2805   0.03655   0.02565  -0.0874   0.7095   0.0766
  -6.750  -0.2629   0.03557   0.02469  -0.0864   0.7051   0.0822
  -6.500  -0.2456   0.03477   0.02380  -0.0855   0.7000   0.0904
  -6.250  -0.2314   0.03380   0.02287  -0.0846   0.6950   0.1000
  -6.000  -0.2176   0.03268   0.02178  -0.0837   0.6909   0.1157
  -5.750  -0.2058   0.03124   0.02059  -0.0830   0.6873   0.1473
  -5.500  -0.1993   0.02945   0.01958  -0.0825   0.6827   0.2355
  -5.250  -0.1885   0.02909   0.02034  -0.0796   0.6785   0.4003
  -5.000  -0.1669   0.02986   0.02108  -0.0776   0.6748   0.4811
  -4.750  -0.1453   0.03149   0.02259  -0.0745   0.6713   0.5412
  -4.500  -0.1264   0.03312   0.02413  -0.0713   0.6665   0.5789
  -4.250  -0.1046   0.03401   0.02485  -0.0690   0.6626   0.6001
  -4.000  -0.0817   0.03445   0.02506  -0.0675   0.6594   0.6163
  -3.750  -0.0582   0.03454   0.02487  -0.0667   0.6568   0.6304
  -3.500  -0.0382   0.03492   0.02513  -0.0656   0.6526   0.6402
  -3.250  -0.0181   0.03511   0.02517  -0.0648   0.6485   0.6505
  -3.000   0.0035   0.03511   0.02496  -0.0645   0.6451   0.6621
  -2.750   0.0273   0.03522   0.02489  -0.0635   0.6423   0.6708
  -2.500   0.0494   0.03528   0.02478  -0.0631   0.6395   0.6806
  -2.250   0.0657   0.03570   0.02513  -0.0624   0.6353   0.6893
  -2.000   0.0854   0.03593   0.02525  -0.0620   0.6318   0.6969
  -1.750   0.1078   0.03603   0.02520  -0.0618   0.6287   0.7044
  -1.500   0.1324   0.03601   0.02500  -0.0619   0.6262   0.7115
  -1.250   0.1531   0.03628   0.02517  -0.0615   0.6231   0.7180
  -1.000   0.1665   0.03699   0.02585  -0.0613   0.6185   0.7254
  -0.750   0.1846   0.03746   0.02627  -0.0607   0.6152   0.7311
  -0.500   0.2076   0.03773   0.02640  -0.0610   0.6124   0.7383
  -0.250   0.2327   0.03785   0.02641  -0.0610   0.6102   0.7442
   0.000   0.2496   0.03852   0.02702  -0.0607   0.6067   0.7506
   0.250   0.2571   0.03982   0.02833  -0.0601   0.6014   0.7574
   0.500   0.2742   0.04053   0.02901  -0.0596   0.5982   0.7634
   0.750   0.2982   0.04098   0.02936  -0.0602   0.5958   0.7705
   1.000   0.3233   0.04121   0.02952  -0.0601   0.5938   0.7764
   1.250   0.3200   0.04339   0.03177  -0.0590   0.5875   0.7833
   1.500   0.3316   0.04464   0.03302  -0.0586   0.5833   0.7898
   1.750   0.3514   0.04540   0.03374  -0.0586   0.5807   0.7966
   2.000   0.3766   0.04586   0.03415  -0.0590   0.5786   0.8038
   2.500   0.3742   0.05022   0.03860  -0.0573   0.5675   0.8184
   2.750   0.3922   0.05115   0.03953  -0.0571   0.5648   0.8259
   3.000   0.4173   0.05173   0.04009  -0.0575   0.5628   0.8342
   3.500   0.4210   0.05600   0.04446  -0.0564   0.5527   0.8519
   3.750   0.4382   0.05709   0.04558  -0.0564   0.5498   0.8623
   4.000   0.4611   0.05777   0.04630  -0.0564   0.5475   0.8732
   4.250   0.4843   0.05846   0.04702  -0.0564   0.5452   0.8862
   4.500   0.4704   0.06165   0.05035  -0.0556   0.5381   0.9025
   5.000   0.5143   0.06375   0.05257  -0.0574   0.5320   1.0002
   5.500   0.5329   0.06825   0.05708  -0.0593   0.5225   1.0002
   5.750   0.5534   0.06978   0.05859  -0.0605   0.5190   1.0002
   6.000   0.5807   0.07089   0.05968  -0.0617   0.5163   1.0002
   6.250   0.5883   0.07321   0.06203  -0.0622   0.5116   1.0002
   6.500   0.5944   0.07556   0.06440  -0.0626   0.5064   1.0002
   6.750   0.6154   0.07699   0.06583  -0.0634   0.5029   1.0002
   7.000   0.6422   0.07808   0.06693  -0.0642   0.5004   1.0002
   7.250   0.6370   0.08113   0.07004  -0.0641   0.4941   1.0002
   7.500   0.6505   0.08298   0.07192  -0.0644   0.4896   1.0002
   7.750   0.6737   0.08425   0.07322  -0.0650   0.4865   1.0002
   8.000   0.6845   0.08634   0.07535  -0.0652   0.4823   1.0002
   8.250   0.6853   0.08898   0.07804  -0.0651   0.4762   1.0002
   8.500   0.7050   0.09045   0.07958  -0.0655   0.4726   1.0002
   8.750   0.7308   0.09159   0.08077  -0.0659   0.4701   1.0002
   9.000   0.7195   0.09505   0.08430  -0.0656   0.4627   1.0002
   9.250   0.7360   0.09672   0.08605  -0.0659   0.4585   1.0002
   9.500   0.7606   0.09790   0.08732  -0.0662   0.4557   1.0002
   9.750   0.7523   0.10123   0.09073  -0.0660   0.4486   1.0002
  10.000   0.7668   0.10303   0.09262  -0.0662   0.4441   1.0002
  10.250   0.7913   0.10421   0.09390  -0.0664   0.4411   1.0002
  10.500   0.7830   0.10753   0.09730  -0.0664   0.4337   1.0002
  10.750   0.7986   0.10926   0.09916  -0.0665   0.4291   1.0002
  11.000   0.8244   0.11034   0.10036  -0.0667   0.4262   1.0002
  11.250   0.8130   0.11375   0.10385  -0.0667   0.4176   1.0002
  11.500   0.8333   0.11514   0.10537  -0.0668   0.4134   1.0002
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