Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

WORTMANN FX 73-170 A (fx73170a-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: WORTMANN FX 73-170 A (fx73170a-il)
Reynolds number: 500,000
Max Cl/Cd: 110.27 at α=7.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx73170a-il-500000-n5.txt
Download as CSV file: xf-fx73170a-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: WORTMANN FX 73-170 A                            
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -12.500   0.0800   0.09170   0.08791  -0.1232   0.7062   0.0126
 -12.250   0.0888   0.08973   0.08591  -0.1239   0.7044   0.0129
 -11.250   0.0079   0.08977   0.08575  -0.1313   0.7080   0.0092
 -11.000   0.0160   0.08751   0.08348  -0.1327   0.7059   0.0090
 -10.750   0.0210   0.08443   0.08039  -0.1344   0.7041   0.0088
 -10.500   0.0217   0.08031   0.07627  -0.1366   0.7023   0.0087
 -10.250   0.0254   0.07703   0.07300  -0.1385   0.7004   0.0085
 -10.000   0.0191   0.07156   0.06759  -0.1414   0.6987   0.0085
  -9.750   0.0169   0.06719   0.06324  -0.1441   0.6966   0.0083
  -9.500   0.0168   0.06327   0.05933  -0.1469   0.6945   0.0077
  -9.250  -0.0073   0.05406   0.05016  -0.1550   0.6926   0.0078
  -9.000  -0.1991   0.02889   0.02391  -0.1454   0.6901   0.0068
  -8.750  -0.1941   0.02735   0.02219  -0.1432   0.6882   0.0070
  -8.500  -0.1944   0.02443   0.01886  -0.1400   0.6864   0.0070
  -8.250  -0.1790   0.02351   0.01783  -0.1388   0.6845   0.0072
  -8.000  -0.1689   0.02135   0.01530  -0.1366   0.6825   0.0071
  -7.750  -0.1504   0.02051   0.01432  -0.1356   0.6804   0.0074
  -7.500  -0.1315   0.01954   0.01317  -0.1346   0.6784   0.0075
  -7.250  -0.1118   0.01857   0.01201  -0.1336   0.6764   0.0077
  -7.000  -0.0908   0.01776   0.01102  -0.1327   0.6745   0.0081
  -6.500  -0.0469   0.01628   0.00923  -0.1312   0.6711   0.0088
  -6.250  -0.0244   0.01565   0.00848  -0.1306   0.6694   0.0090
  -6.000  -0.0019   0.01506   0.00780  -0.1299   0.6676   0.0091
  -5.750   0.0209   0.01456   0.00724  -0.1292   0.6658   0.0095
  -5.500   0.0435   0.01408   0.00672  -0.1286   0.6641   0.0098
  -5.250   0.0675   0.01377   0.00637  -0.1282   0.6624   0.0104
  -5.000   0.0926   0.01359   0.00614  -0.1279   0.6607   0.0115
  -4.750   0.1163   0.01325   0.00572  -0.1274   0.6590   0.0118
  -4.500   0.1395   0.01286   0.00527  -0.1268   0.6574   0.0126
  -4.250   0.1633   0.01257   0.00498  -0.1263   0.6556   0.0136
  -4.000   0.1877   0.01232   0.00471  -0.1259   0.6540   0.0145
  -3.750   0.2124   0.01211   0.00445  -0.1255   0.6524   0.0158
  -3.500   0.2367   0.01187   0.00421  -0.1251   0.6507   0.0175
  -3.250   0.2619   0.01171   0.00403  -0.1248   0.6492   0.0207
  -3.000   0.2870   0.01154   0.00385  -0.1245   0.6476   0.0250
  -2.750   0.3121   0.01138   0.00368  -0.1242   0.6462   0.0302
  -2.500   0.3374   0.01123   0.00353  -0.1240   0.6446   0.0398
  -2.250   0.3626   0.01108   0.00340  -0.1237   0.6432   0.0555
  -2.000   0.3864   0.01086   0.00332  -0.1233   0.6417   0.0915
  -1.750   0.4081   0.01051   0.00323  -0.1225   0.6400   0.1709
  -1.500   0.4264   0.00995   0.00314  -0.1212   0.6384   0.3187
  -1.250   0.4429   0.00940   0.00307  -0.1195   0.6369   0.4714
  -1.000   0.4586   0.00896   0.00305  -0.1173   0.6353   0.6069
  -0.750   0.4767   0.00878   0.00319  -0.1153   0.6338   0.7073
  -0.500   0.4993   0.00885   0.00335  -0.1141   0.6324   0.7598
  -0.250   0.5232   0.00897   0.00345  -0.1133   0.6311   0.7862
   0.000   0.5481   0.00908   0.00351  -0.1128   0.6296   0.8010
   0.250   0.5746   0.00917   0.00358  -0.1126   0.6282   0.8096
   0.500   0.5990   0.00924   0.00363  -0.1121   0.6267   0.8165
   0.750   0.6247   0.00928   0.00368  -0.1119   0.6253   0.8200
   1.000   0.6504   0.00934   0.00372  -0.1117   0.6238   0.8230
   1.250   0.6761   0.00940   0.00377  -0.1116   0.6223   0.8262
   1.500   0.7016   0.00946   0.00381  -0.1114   0.6208   0.8294
   1.750   0.7269   0.00952   0.00384  -0.1111   0.6193   0.8324
   2.000   0.7531   0.00956   0.00389  -0.1111   0.6178   0.8347
   2.250   0.7793   0.00962   0.00393  -0.1111   0.6163   0.8374
   2.500   0.8059   0.00969   0.00398  -0.1111   0.6150   0.8402
   2.750   0.8329   0.00977   0.00404  -0.1113   0.6137   0.8432
   3.000   0.8580   0.00986   0.00414  -0.1111   0.6125   0.8461
   3.250   0.8819   0.00994   0.00425  -0.1106   0.6110   0.8488
   3.500   0.9063   0.01002   0.00436  -0.1103   0.6094   0.8513
   3.750   0.9306   0.01009   0.00447  -0.1099   0.6076   0.8539
   4.000   0.9552   0.01018   0.00459  -0.1096   0.6059   0.8566
   4.250   0.9799   0.01027   0.00470  -0.1094   0.6044   0.8594
   4.500   1.0048   0.01036   0.00480  -0.1092   0.6029   0.8619
   4.750   1.0305   0.01044   0.00489  -0.1092   0.6013   0.8642
   5.000   1.0578   0.01052   0.00501  -0.1095   0.5998   0.8666
   5.250   1.0853   0.01063   0.00513  -0.1099   0.5983   0.8689
   5.500   1.1065   0.01075   0.00533  -0.1090   0.5963   0.8718
   5.750   1.1280   0.01086   0.00552  -0.1082   0.5939   0.8748
   6.000   1.1487   0.01096   0.00567  -0.1072   0.5911   0.8783
   6.250   1.1716   0.01104   0.00580  -0.1067   0.5884   0.8813
   6.500   1.1975   0.01112   0.00591  -0.1068   0.5857   0.8843
   6.750   1.2204   0.01125   0.00609  -0.1063   0.5821   0.8879
   7.000   1.2392   0.01144   0.00638  -0.1052   0.5774   0.8923
   7.250   1.2630   0.01159   0.00659  -0.1050   0.5730   0.8965
   7.500   1.2913   0.01171   0.00675  -0.1058   0.5697   0.9010
   7.750   1.3136   0.01199   0.00715  -0.1057   0.5638   0.9075
   8.000   1.3398   0.01223   0.00745  -0.1064   0.5569   0.9139
   8.250   1.3650   0.01259   0.00791  -0.1071   0.5475   0.9227
   8.500   1.3939   0.01300   0.00838  -0.1088   0.5375   0.9335
   8.750   1.4214   0.01388   0.00929  -0.1112   0.5126   0.9548
   9.000   1.4291   0.01539   0.01071  -0.1099   0.4828   1.0000
   9.250   1.4176   0.01763   0.01278  -0.1059   0.4467   1.0000
   9.500   1.4033   0.02026   0.01524  -0.1018   0.4136   1.0000
   9.750   1.3889   0.02302   0.01787  -0.0979   0.3833   1.0000
  10.000   1.3807   0.02545   0.02021  -0.0948   0.3605   1.0000
  10.250   1.3689   0.02824   0.02287  -0.0915   0.3331   1.0000
  10.500   1.3573   0.03116   0.02565  -0.0885   0.3038   1.0000
  10.750   1.3517   0.03373   0.02813  -0.0861   0.2800   1.0000
  11.000   1.3471   0.03629   0.03059  -0.0840   0.2569   1.0000
  11.250   1.3438   0.03880   0.03300  -0.0820   0.2335   1.0000
  11.500   1.3422   0.04122   0.03532  -0.0803   0.2115   1.0000
  11.750   1.3396   0.04374   0.03775  -0.0785   0.1874   1.0000
  12.000   1.3377   0.04626   0.04016  -0.0769   0.1646   1.0000
  12.250   1.3376   0.04866   0.04245  -0.0754   0.1434   1.0000
  12.500   1.3385   0.05102   0.04472  -0.0741   0.1239   1.0000
  12.750   1.3351   0.05375   0.04729  -0.0726   0.0986   1.0000
  13.000   1.3415   0.05567   0.04921  -0.0718   0.0896   1.0000
  13.250   1.3433   0.05804   0.05150  -0.0707   0.0731   1.0000
  13.500   1.3449   0.06045   0.05382  -0.0697   0.0580   1.0000
  13.750   1.3469   0.06284   0.05616  -0.0688   0.0464   1.0000
  14.000   1.3515   0.06502   0.05832  -0.0681   0.0384   1.0000
  14.250   1.3564   0.06720   0.06050  -0.0674   0.0325   1.0000
  14.500   1.3628   0.06926   0.06258  -0.0669   0.0294   1.0000
  14.750   1.3704   0.07121   0.06458  -0.0664   0.0273   1.0000
  15.000   1.3768   0.07331   0.06672  -0.0660   0.0245   1.0000
  15.250   1.3828   0.07545   0.06891  -0.0655   0.0229   1.0000
  15.500   1.3894   0.07752   0.07102  -0.0652   0.0209   1.0000
  15.750   1.3958   0.07966   0.07323  -0.0649   0.0197   1.0000
  16.000   1.4003   0.08204   0.07565  -0.0645   0.0177   1.0000
  16.250   1.4061   0.08426   0.07793  -0.0643   0.0160   1.0000
  16.500   1.4112   0.08661   0.08034  -0.0640   0.0147   1.0000
  16.750   1.4152   0.08909   0.08286  -0.0638   0.0133   1.0000
  17.000   1.4199   0.09149   0.08534  -0.0637   0.0124   1.0000
  17.250   1.4231   0.09409   0.08799  -0.0636   0.0106   1.0000
  17.500   1.4262   0.09671   0.09067  -0.0635   0.0097   1.0000
  17.750   1.4285   0.09947   0.09351  -0.0635   0.0082   1.0000
  18.250   1.4321   0.10521   0.09938  -0.0637   0.0069   1.0000
  18.500   1.4332   0.10819   0.10244  -0.0639   0.0063   1.0000
  18.750   1.4340   0.11124   0.10557  -0.0642   0.0059   1.0000
  19.000   1.4336   0.11443   0.10883  -0.0645   0.0054   1.0000
<< Back to WORTMANN FX 73-170 A (fx73170a-il)

Polar data table (+)

Polar graphs


<< Back to WORTMANN FX 73-170 A (fx73170a-il)