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WORTMANN FX 66-17AII-182 AIRFOIL (AS TESTED AT NASA) (fx6617ai-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: WORTMANN FX 66-17AII-182 AIRFOIL (AS TESTED AT NASA) (fx6617ai-il)
Reynolds number: 100,000
Max Cl/Cd: 29.33 at α=5.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx6617ai-il-100000-n5.txt
Download as CSV file: xf-fx6617ai-il-100000-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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.000  -0.4007   0.08996   0.08463  -0.0627   0.7461   0.0313
 -11.750  -0.4470   0.07670   0.07120  -0.0724   0.7438   0.0305
 -11.500  -0.4815   0.06831   0.06254  -0.0784   0.7374   0.0300
 -11.250  -0.5067   0.06227   0.05622  -0.0822   0.7296   0.0298
 -11.000  -0.5249   0.05757   0.05122  -0.0847   0.7215   0.0297
 -10.750  -0.5372   0.05367   0.04703  -0.0862   0.7135   0.0298
 -10.500  -0.5450   0.05043   0.04348  -0.0870   0.7061   0.0299
 -10.250  -0.5477   0.04793   0.04069  -0.0867   0.6991   0.0302
 -10.000  -0.5438   0.04561   0.03807  -0.0865   0.6924   0.0309
  -9.750  -0.5369   0.04337   0.03548  -0.0862   0.6866   0.0318
  -9.500  -0.5267   0.04116   0.03290  -0.0858   0.6805   0.0326
  -9.250  -0.5130   0.03904   0.03039  -0.0854   0.6753   0.0332
  -9.000  -0.4956   0.03707   0.02806  -0.0850   0.6707   0.0337
  -8.750  -0.4757   0.03533   0.02601  -0.0847   0.6655   0.0342
  -8.500  -0.4541   0.03372   0.02417  -0.0844   0.6607   0.0348
  -8.250  -0.4317   0.03221   0.02257  -0.0841   0.6567   0.0357
  -8.000  -0.4092   0.03100   0.02129  -0.0838   0.6519   0.0366
  -7.750  -0.3869   0.02995   0.02016  -0.0834   0.6473   0.0379
  -7.500  -0.3646   0.02905   0.01913  -0.0831   0.6434   0.0400
  -7.250  -0.3419   0.02823   0.01813  -0.0826   0.6401   0.0421
  -7.000  -0.3208   0.02726   0.01717  -0.0821   0.6362   0.0439
  -6.750  -0.3002   0.02640   0.01629  -0.0817   0.6326   0.0459
  -6.500  -0.2790   0.02565   0.01547  -0.0812   0.6292   0.0484
  -6.250  -0.2570   0.02501   0.01466  -0.0808   0.6262   0.0521
  -6.000  -0.2361   0.02424   0.01389  -0.0806   0.6231   0.0573
  -5.750  -0.2136   0.02361   0.01319  -0.0803   0.6193   0.0645
  -5.500  -0.1916   0.02289   0.01248  -0.0801   0.6159   0.0769
  -5.250  -0.1707   0.02193   0.01174  -0.0800   0.6130   0.1134
  -5.000  -0.1527   0.02050   0.01091  -0.0800   0.6106   0.2299
  -4.750  -0.1342   0.01950   0.01068  -0.0795   0.6084   0.3860
  -4.500  -0.1100   0.01957   0.01099  -0.0789   0.6053   0.4651
  -4.250  -0.0844   0.01993   0.01140  -0.0782   0.6022   0.5133
  -4.000  -0.0583   0.02048   0.01186  -0.0775   0.5992   0.5507
  -3.750  -0.0321   0.02107   0.01238  -0.0765   0.5965   0.5730
  -3.500  -0.0052   0.02141   0.01256  -0.0760   0.5942   0.5877
  -3.250   0.0220   0.02153   0.01249  -0.0760   0.5918   0.5986
  -3.000   0.0484   0.02171   0.01262  -0.0758   0.5889   0.6050
  -2.750   0.0755   0.02177   0.01254  -0.0761   0.5862   0.6141
  -2.500   0.1019   0.02197   0.01268  -0.0757   0.5838   0.6208
  -2.250   0.1293   0.02204   0.01259  -0.0759   0.5814   0.6301
  -2.000   0.1564   0.02214   0.01260  -0.0757   0.5793   0.6351
  -1.750   0.1846   0.02217   0.01246  -0.0761   0.5774   0.6411
  -1.500   0.2111   0.02226   0.01249  -0.0764   0.5746   0.6468
  -1.250   0.2371   0.02240   0.01263  -0.0763   0.5719   0.6509
  -1.000   0.2639   0.02252   0.01269  -0.0765   0.5695   0.6562
  -0.750   0.2915   0.02261   0.01268  -0.0770   0.5673   0.6620
  -0.500   0.3183   0.02272   0.01274  -0.0770   0.5653   0.6657
  -0.250   0.3460   0.02281   0.01275  -0.0773   0.5635   0.6705
   0.000   0.3748   0.02288   0.01268  -0.0779   0.5618   0.6766
   0.250   0.3996   0.02313   0.01297  -0.0778   0.5591   0.6803
   0.500   0.4244   0.02340   0.01329  -0.0777   0.5563   0.6847
   0.750   0.4505   0.02365   0.01353  -0.0780   0.5539   0.6901
   1.000   0.4769   0.02387   0.01374  -0.0782   0.5518   0.6949
   1.250   0.5032   0.02407   0.01393  -0.0782   0.5499   0.6991
   1.500   0.5307   0.02423   0.01405  -0.0786   0.5482   0.7041
   1.750   0.5592   0.02437   0.01413  -0.0790   0.5466   0.7095
   2.000   0.5840   0.02467   0.01447  -0.0789   0.5444   0.7137
   2.250   0.6057   0.02522   0.01513  -0.0787   0.5413   0.7187
   2.500   0.6299   0.02570   0.01565  -0.0789   0.5387   0.7243
   2.750   0.6537   0.02608   0.01610  -0.0787   0.5365   0.7285
   3.000   0.6791   0.02638   0.01643  -0.0788   0.5345   0.7337
   3.250   0.7064   0.02662   0.01666  -0.0791   0.5328   0.7394
   3.500   0.7335   0.02678   0.01684  -0.0792   0.5312   0.7441
   3.750   0.7590   0.02712   0.01721  -0.0793   0.5295   0.7495
   4.000   0.7732   0.02830   0.01859  -0.0786   0.5256   0.7555
   4.250   0.7916   0.02908   0.01950  -0.0780   0.5226   0.7605
   4.500   0.8143   0.02961   0.02009  -0.0779   0.5201   0.7665
   4.750   0.8397   0.02995   0.02048  -0.0780   0.5182   0.7726
   5.000   0.8659   0.03019   0.02078  -0.0780   0.5166   0.7786
   5.250   0.8934   0.03046   0.02107  -0.0784   0.5153   0.7857
   5.500   0.8892   0.03286   0.02376  -0.0760   0.5095   0.7919
   5.750   0.9021   0.03405   0.02509  -0.0752   0.5057   0.7996
   6.000   0.9228   0.03461   0.02575  -0.0747   0.5034   0.8071
   6.250   0.9468   0.03502   0.02624  -0.0747   0.5018   0.8158
   6.500   0.9729   0.03520   0.02651  -0.0746   0.5005   0.8246
   7.000   0.9392   0.04155   0.03328  -0.0688   0.4869   0.8508
   7.250   0.9647   0.04154   0.03341  -0.0684   0.4857   0.8701
   7.500   0.9938   0.04132   0.03334  -0.0683   0.4847   0.9067
   8.500   0.8933   0.06274   0.05502  -0.0660   0.4439   1.0002
   9.000   0.8994   0.06796   0.06034  -0.0657   0.4323   1.0002
   9.250   0.9169   0.06910   0.06155  -0.0656   0.4294   1.0002
   9.500   0.9400   0.06962   0.06214  -0.0656   0.4276   1.0002
   9.750   0.9657   0.06982   0.06242  -0.0655   0.4263   1.0002
  10.250   0.9641   0.07578   0.06852  -0.0651   0.4131   1.0002
  10.500   0.9894   0.07595   0.06881  -0.0649   0.4117   1.0002
  12.000   1.0077   0.09107   0.08450  -0.0639   0.3729   1.0002
  12.250   1.0433   0.08901   0.08257  -0.0631   0.3699   1.0002
  12.750   1.0657   0.09035   0.08411  -0.0620   0.3500   1.0002
  13.000   1.1122   0.08542   0.07932  -0.0607   0.3396   1.0002
  13.250   1.1131   0.08771   0.08170  -0.0606   0.3244   1.0002
  13.500   1.1129   0.09050   0.08457  -0.0607   0.3083   1.0002
  13.750   1.1169   0.09285   0.08703  -0.0607   0.2920   1.0002
  14.000   1.1291   0.09402   0.08826  -0.0605   0.2721   1.0002
  14.250   1.1698   0.08992   0.08352  -0.0587   0.1912   1.0002
  14.750   1.1375   0.09986   0.09265  -0.0591   0.1092   1.0002
  15.000   1.1248   0.10479   0.09738  -0.0596   0.0873   1.0002
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