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WORTMANN FX 66-17A-175 AIRFOIL (fx66a175-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: WORTMANN FX 66-17A-175 AIRFOIL (fx66a175-il)
Reynolds number: 500,000
Max Cl/Cd: 100.65 at α=7.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx66a175-il-500000-n5.txt
Download as CSV file: xf-fx66a175-il-500000-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 =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.750  -0.4156   0.06184   0.05773  -0.0951   0.6195   0.0045
 -12.500  -0.4491   0.05392   0.04960  -0.0997   0.6166   0.0044
 -12.250  -0.4578   0.05009   0.04564  -0.1018   0.6116   0.0045
 -12.000  -0.4834   0.04445   0.03977  -0.1042   0.6075   0.0045
 -11.750  -0.4848   0.04189   0.03710  -0.1053   0.6019   0.0046
 -11.500  -0.4964   0.03825   0.03325  -0.1063   0.5969   0.0045
 -11.250  -0.4948   0.03614   0.03103  -0.1070   0.5915   0.0047
 -11.000  -0.5016   0.03318   0.02785  -0.1073   0.5864   0.0047
 -10.750  -0.5009   0.03112   0.02564  -0.1075   0.5815   0.0049
 -10.500  -0.5038   0.02893   0.02327  -0.1070   0.5770   0.0049
 -10.250  -0.5052   0.02742   0.02158  -0.1051   0.5723   0.0050
 -10.000  -0.4975   0.02604   0.02000  -0.1039   0.5678   0.0052
  -9.750  -0.4862   0.02472   0.01851  -0.1028   0.5634   0.0053
  -9.500  -0.4723   0.02357   0.01718  -0.1018   0.5588   0.0055
  -9.250  -0.4563   0.02255   0.01600  -0.1009   0.5548   0.0057
  -9.000  -0.4376   0.02173   0.01502  -0.1002   0.5510   0.0059
  -8.750  -0.4182   0.02094   0.01409  -0.0996   0.5472   0.0060
  -8.500  -0.4007   0.01995   0.01303  -0.0988   0.5435   0.0066
  -8.000  -0.3575   0.01877   0.01169  -0.0979   0.5369   0.0072
  -7.750  -0.3358   0.01810   0.01094  -0.0974   0.5336   0.0075
  -7.500  -0.3137   0.01746   0.01020  -0.0969   0.5302   0.0080
  -7.250  -0.2913   0.01687   0.00949  -0.0964   0.5271   0.0083
  -7.000  -0.2681   0.01633   0.00884  -0.0959   0.5243   0.0087
  -6.750  -0.2440   0.01584   0.00827  -0.0956   0.5215   0.0090
  -6.500  -0.2217   0.01511   0.00745  -0.0951   0.5186   0.0095
  -6.250  -0.1972   0.01468   0.00697  -0.0949   0.5156   0.0104
  -6.000  -0.1721   0.01432   0.00654  -0.0946   0.5128   0.0112
  -5.750  -0.1467   0.01397   0.00610  -0.0944   0.5102   0.0121
  -5.500  -0.1207   0.01362   0.00567  -0.0943   0.5074   0.0129
  -5.250  -0.0949   0.01324   0.00522  -0.0941   0.5045   0.0142
  -5.000  -0.0687   0.01294   0.00487  -0.0940   0.5018   0.0160
  -4.750  -0.0421   0.01272   0.00458  -0.0939   0.4994   0.0186
  -4.500  -0.0158   0.01246   0.00428  -0.0938   0.4971   0.0260
  -4.250   0.0106   0.01212   0.00400  -0.0938   0.4950   0.0452
  -4.000   0.0368   0.01173   0.00372  -0.0938   0.4927   0.0800
  -3.750   0.0622   0.01122   0.00342  -0.0938   0.4903   0.1444
  -3.500   0.0862   0.01044   0.00303  -0.0938   0.4880   0.2613
  -3.250   0.1103   0.00984   0.00292  -0.0936   0.4858   0.4025
  -3.000   0.1384   0.00991   0.00296  -0.0937   0.4837   0.4349
  -2.750   0.1667   0.01000   0.00300  -0.0937   0.4818   0.4512
  -2.500   0.1953   0.01009   0.00305  -0.0938   0.4798   0.4641
  -2.250   0.2239   0.01020   0.00308  -0.0940   0.4776   0.4737
  -2.000   0.2522   0.01024   0.00310  -0.0940   0.4755   0.4795
  -1.750   0.2805   0.01027   0.00308  -0.0942   0.4734   0.4827
  -1.500   0.3088   0.01032   0.00305  -0.0943   0.4714   0.4858
  -1.250   0.3371   0.01036   0.00301  -0.0944   0.4696   0.4882
  -1.000   0.3652   0.01039   0.00298  -0.0945   0.4678   0.4897
  -0.750   0.3936   0.01039   0.00297  -0.0947   0.4661   0.4910
  -0.500   0.4219   0.01040   0.00296  -0.0949   0.4642   0.4923
  -0.250   0.4502   0.01042   0.00296  -0.0950   0.4621   0.4936
   0.000   0.4783   0.01045   0.00296  -0.0952   0.4601   0.4950
   0.250   0.5063   0.01049   0.00296  -0.0953   0.4581   0.4965
   0.500   0.5342   0.01054   0.00298  -0.0954   0.4563   0.4980
   0.750   0.5620   0.01061   0.00300  -0.0955   0.4545   0.4994
   1.000   0.5901   0.01065   0.00304  -0.0957   0.4527   0.5009
   1.250   0.6182   0.01070   0.00308  -0.0958   0.4508   0.5024
   1.500   0.6462   0.01074   0.00312  -0.0960   0.4488   0.5040
   1.750   0.6739   0.01078   0.00318  -0.0961   0.4468   0.5055
   2.000   0.7016   0.01083   0.00324  -0.0962   0.4450   0.5071
   2.250   0.7292   0.01090   0.00331  -0.0963   0.4433   0.5086
   2.500   0.7566   0.01098   0.00339  -0.0963   0.4417   0.5101
   2.750   0.7839   0.01108   0.00348  -0.0964   0.4400   0.5117
   3.000   0.8116   0.01115   0.00357  -0.0965   0.4385   0.5134
   3.250   0.8392   0.01121   0.00367  -0.0966   0.4369   0.5153
   3.500   0.8668   0.01129   0.00379  -0.0967   0.4352   0.5173
   3.750   0.8942   0.01137   0.00390  -0.0968   0.4337   0.5194
   4.000   0.9213   0.01144   0.00403  -0.0969   0.4321   0.5215
   4.250   0.9484   0.01153   0.00416  -0.0969   0.4306   0.5235
   4.500   0.9754   0.01163   0.00430  -0.0970   0.4292   0.5256
   4.750   1.0023   0.01174   0.00443  -0.0970   0.4278   0.5277
   5.000   1.0291   0.01187   0.00459  -0.0970   0.4265   0.5301
   5.250   1.0559   0.01201   0.00476  -0.0970   0.4252   0.5325
   5.500   1.0828   0.01210   0.00494  -0.0971   0.4239   0.5349
   5.750   1.1095   0.01220   0.00513  -0.0971   0.4226   0.5373
   6.000   1.1361   0.01231   0.00533  -0.0971   0.4212   0.5400
   6.250   1.1626   0.01243   0.00553  -0.0971   0.4197   0.5429
   6.500   1.1890   0.01256   0.00573  -0.0970   0.4183   0.5459
   6.750   1.2151   0.01269   0.00594  -0.0970   0.4169   0.5490
   7.000   1.2401   0.01277   0.00607  -0.0966   0.4132   0.5524
   7.250   1.2635   0.01276   0.00616  -0.0960   0.4035   0.5562
   7.500   1.2858   0.01283   0.00625  -0.0952   0.3917   0.5604
   7.750   1.3074   0.01299   0.00643  -0.0943   0.3806   0.5646
   8.000   1.3280   0.01322   0.00669  -0.0933   0.3657   0.5696
   8.250   1.3392   0.01380   0.00711  -0.0907   0.3226   0.5748
   8.500   1.3110   0.01592   0.00869  -0.0819   0.2334   0.5782
   8.750   1.2866   0.01792   0.01042  -0.0743   0.1786   0.5825
   9.000   1.2513   0.02063   0.01288  -0.0664   0.1241   0.5870
   9.500   1.2065   0.02690   0.01903  -0.0589   0.0655   0.5986
   9.750   1.1741   0.03204   0.02408  -0.0568   0.0307   0.6041
  10.000   1.1570   0.03602   0.02808  -0.0555   0.0134   0.6125
  10.250   1.1506   0.03906   0.03119  -0.0546   0.0085   0.6226
  10.500   1.1498   0.04157   0.03382  -0.0540   0.0073   0.6381
  10.750   1.1472   0.04426   0.03666  -0.0533   0.0060   0.6579
  11.000   1.1461   0.04678   0.03935  -0.0527   0.0055   0.6920
  11.500   1.1614   0.05206   0.04535  -0.0554   0.0044   1.0000
  11.750   1.1620   0.05479   0.04815  -0.0552   0.0043   1.0000
  12.000   1.1650   0.05732   0.05072  -0.0551   0.0038   1.0000
  12.250   1.1660   0.06012   0.05358  -0.0550   0.0038   1.0000
  12.500   1.1657   0.06311   0.05664  -0.0550   0.0035   1.0000
  12.750   1.1651   0.06621   0.05981  -0.0550   0.0033   1.0000
  13.000   1.1677   0.06897   0.06264  -0.0551   0.0032   1.0000
  13.250   1.1704   0.07174   0.06547  -0.0552   0.0031   1.0000
  13.500   1.1725   0.07464   0.06844  -0.0554   0.0029   1.0000
  13.750   1.1744   0.07760   0.07148  -0.0556   0.0029   1.0000
  14.000   1.1761   0.08062   0.07457  -0.0559   0.0028   1.0000
  14.250   1.1776   0.08367   0.07768  -0.0563   0.0027   1.0000
  14.500   1.1799   0.08667   0.08076  -0.0567   0.0028   1.0000
  14.750   1.1816   0.08980   0.08395  -0.0571   0.0026   1.0000
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