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WORTMANN FX 66-17A-175 AIRFOIL (fx66a175-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: WORTMANN FX 66-17A-175 AIRFOIL (fx66a175-il)
Reynolds number: 50,000
Max Cl/Cd: 12.31 at α=1.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx66a175-il-50000-n5.txt
Download as CSV file: xf-fx66a175-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: WORTMANN FX 66-17A-175 AIRFOIL                  
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -11.500  -0.2682   0.11719   0.11131  -0.0523   1.0000   0.0439
 -11.250  -0.2685   0.11315   0.10741  -0.0537   1.0000   0.0433
 -11.000  -0.2704   0.10900   0.10340  -0.0552   1.0000   0.0426
 -10.750  -0.2601   0.10232   0.09677  -0.0614   0.9279   0.0419
 -10.250  -0.2464   0.08591   0.08017  -0.0783   0.8615   0.0401
 -10.000  -0.2575   0.07686   0.07095  -0.0871   0.8397   0.0390
  -9.750  -0.2838   0.06836   0.06215  -0.0956   0.8203   0.0376
  -9.500  -0.3040   0.06275   0.05619  -0.1008   0.8016   0.0371
  -9.250  -0.3188   0.05915   0.05226  -0.1028   0.7854   0.0368
  -9.000  -0.3259   0.05598   0.04874  -0.1035   0.7723   0.0367
  -8.750  -0.3265   0.05304   0.04550  -0.1037   0.7606   0.0371
  -8.500  -0.3216   0.05050   0.04269  -0.1038   0.7502   0.0381
  -8.250  -0.3127   0.04819   0.04009  -0.1036   0.7413   0.0393
  -8.000  -0.3025   0.04598   0.03758  -0.1033   0.7321   0.0411
  -7.750  -0.2891   0.04373   0.03488  -0.1029   0.7241   0.0428
  -7.500  -0.2720   0.04153   0.03226  -0.1023   0.7164   0.0444
  -7.250  -0.2508   0.03955   0.02988  -0.1015   0.7093   0.0457
  -7.000  -0.2262   0.03793   0.02787  -0.1005   0.7023   0.0474
  -6.750  -0.2035   0.03650   0.02647  -0.0995   0.6959   0.0512
  -6.500  -0.1823   0.03550   0.02532  -0.0984   0.6894   0.0564
  -6.250  -0.1610   0.03452   0.02411  -0.0969   0.6841   0.0612
  -6.000  -0.1461   0.03354   0.02318  -0.0954   0.6775   0.0663
  -5.750  -0.1302   0.03253   0.02204  -0.0942   0.6721   0.0761
  -5.500  -0.1159   0.03139   0.02093  -0.0933   0.6667   0.0904
  -5.250  -0.1032   0.02993   0.01968  -0.0928   0.6611   0.1191
  -5.000  -0.0951   0.02743   0.01824  -0.0926   0.6570   0.2471
  -4.750  -0.0782   0.02883   0.02027  -0.0891   0.6516   0.4423
  -4.500  -0.0577   0.03051   0.02170  -0.0863   0.6463   0.5039
  -4.250  -0.0359   0.03210   0.02317  -0.0822   0.6421   0.5406
  -4.000  -0.0160   0.03261   0.02345  -0.0802   0.6372   0.5632
  -3.750   0.0054   0.03282   0.02344  -0.0788   0.6324   0.5780
  -3.500   0.0293   0.03280   0.02314  -0.0780   0.6285   0.5894
  -3.250   0.0521   0.03279   0.02292  -0.0772   0.6244   0.5978
  -3.000   0.0732   0.03274   0.02266  -0.0770   0.6197   0.6070
  -2.750   0.0966   0.03273   0.02244  -0.0763   0.6160   0.6136
  -2.500   0.1227   0.03257   0.02198  -0.0769   0.6131   0.6211
  -2.250   0.1435   0.03269   0.02200  -0.0763   0.6091   0.6257
  -2.000   0.1650   0.03281   0.02197  -0.0761   0.6048   0.6314
  -1.750   0.1895   0.03282   0.02176  -0.0763   0.6013   0.6368
  -1.500   0.2156   0.03279   0.02154  -0.0763   0.5985   0.6413
  -1.250   0.2357   0.03311   0.02177  -0.0762   0.5942   0.6458
  -1.000   0.2573   0.03341   0.02194  -0.0764   0.5902   0.6503
  -0.750   0.2805   0.03362   0.02202  -0.0762   0.5871   0.6538
  -0.500   0.3064   0.03377   0.02202  -0.0764   0.5847   0.6578
  -0.250   0.3283   0.03420   0.02234  -0.0765   0.5817   0.6616
   0.000   0.3431   0.03501   0.02313  -0.0760   0.5773   0.6654
   0.250   0.3638   0.03549   0.02355  -0.0757   0.5739   0.6691
   0.500   0.3892   0.03578   0.02374  -0.0759   0.5712   0.6732
   0.750   0.4176   0.03600   0.02380  -0.0766   0.5691   0.6776
   1.000   0.4218   0.03753   0.02541  -0.0751   0.5639   0.6811
   1.250   0.4362   0.03852   0.02640  -0.0744   0.5602   0.6850
   1.500   0.4587   0.03910   0.02692  -0.0745   0.5574   0.6897
   1.750   0.4859   0.03946   0.02719  -0.0749   0.5553   0.6946
   2.000   0.4835   0.04149   0.02931  -0.0730   0.5499   0.6985
   2.250   0.4913   0.04301   0.03085  -0.0720   0.5455   0.7033
   2.500   0.5122   0.04381   0.03161  -0.0721   0.5428   0.7088
   2.750   0.5385   0.04420   0.03199  -0.0723   0.5408   0.7141
   3.000   0.5090   0.04806   0.03597  -0.0690   0.5332   0.7184
   3.250   0.5186   0.04965   0.03757  -0.0685   0.5298   0.7243
   3.500   0.5407   0.05041   0.03835  -0.0685   0.5275   0.7308
   3.750   0.5691   0.05083   0.03877  -0.0689   0.5259   0.7387
   4.000   0.5297   0.05605   0.04412  -0.0668   0.5170   0.7441
   4.250   0.5459   0.05742   0.04553  -0.0668   0.5145   0.7531
   4.500   0.5665   0.05842   0.04661  -0.0669   0.5126   0.7633
   4.750   0.5641   0.06107   0.04938  -0.0663   0.5082   0.7739
   5.000   0.5638   0.06347   0.05190  -0.0658   0.5034   0.7881
   5.250   0.5790   0.06479   0.05339  -0.0656   0.5005   0.8124
   5.500   0.5989   0.06569   0.05456  -0.0660   0.4983   0.9818
   5.750   0.6236   0.06678   0.05558  -0.0665   0.4967   1.0000
   6.000   0.6043   0.07078   0.05958  -0.0661   0.4899   1.0000
   6.250   0.6194   0.07257   0.06138  -0.0666   0.4866   1.0000
   6.500   0.6412   0.07394   0.06272  -0.0671   0.4841   1.0000
   6.750   0.6575   0.07564   0.06441  -0.0674   0.4811   1.0000
   7.000   0.6503   0.07879   0.06758  -0.0672   0.4753   1.0000
   7.250   0.6654   0.08056   0.06936  -0.0674   0.4720   1.0000
   7.500   0.6883   0.08181   0.07064  -0.0677   0.4694   1.0000
   7.750   0.6884   0.08455   0.07342  -0.0676   0.4646   1.0000
   8.000   0.6931   0.08701   0.07592  -0.0677   0.4602   1.0000
   8.250   0.7110   0.08858   0.07753  -0.0678   0.4568   1.0000
   8.500   0.7363   0.08971   0.07871  -0.0680   0.4544   1.0000
   8.750   0.7244   0.09324   0.08233  -0.0679   0.4478   1.0000
   9.000   0.7383   0.09509   0.08425  -0.0680   0.4437   1.0000
   9.250   0.7622   0.09627   0.08551  -0.0681   0.4407   1.0000
   9.500   0.7565   0.09937   0.08868  -0.0681   0.4338   1.0000
   9.750   0.7703   0.10119   0.09059  -0.0682   0.4291   1.0000
  10.000   0.7952   0.10229   0.09182  -0.0682   0.4261   1.0000
  10.250   0.7870   0.10559   0.09521  -0.0683   0.4184   1.0000
  10.500   0.8045   0.10718   0.09691  -0.0684   0.4140   1.0000
  10.750   0.8193   0.10903   0.09887  -0.0685   0.4098   1.0000
  11.000   0.8175   0.11192   0.10187  -0.0687   0.4025   1.0000
  11.250   0.8404   0.11315   0.10325  -0.0687   0.3988   1.0000
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