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FX 67-K-150/17 AIRFOIL (fx67k150-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: FX 67-K-150/17 AIRFOIL (fx67k150-il)
Reynolds number: 500,000
Max Cl/Cd: 118.25 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx67k150-il-500000-n5.txt
Download as CSV file: xf-fx67k150-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 67-K-150/17 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
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.0977   0.07743   0.07391  -0.1012   0.7223   0.0046
  -9.000  -0.0975   0.07393   0.07043  -0.1029   0.7205   0.0044
  -8.750  -0.0975   0.07040   0.06693  -0.1048   0.7187   0.0044
  -8.500  -0.1018   0.06618   0.06273  -0.1072   0.7169   0.0042
  -8.250  -0.1101   0.06131   0.05788  -0.1112   0.7152   0.0042
  -8.000  -0.1249   0.05704   0.05360  -0.1135   0.7133   0.0041
  -7.750  -0.1356   0.05373   0.05024  -0.1136   0.7111   0.0041
  -7.500  -0.1416   0.04982   0.04624  -0.1138   0.7090   0.0040
  -7.250  -0.1420   0.04616   0.04245  -0.1136   0.7069   0.0038
  -7.000  -0.1394   0.04238   0.03850  -0.1130   0.7050   0.0037
  -6.750  -0.1337   0.03856   0.03446  -0.1121   0.7034   0.0036
  -6.500  -0.1252   0.03465   0.03024  -0.1109   0.7019   0.0034
  -6.250  -0.1141   0.03067   0.02593  -0.1095   0.7004   0.0032
  -6.000  -0.1024   0.02566   0.02047  -0.1073   0.6986   0.0030
  -5.750  -0.0891   0.01976   0.01386  -0.1046   0.6967   0.0029
  -5.500  -0.0671   0.01723   0.01091  -0.1036   0.6948   0.0029
  -5.250  -0.0428   0.01586   0.00929  -0.1031   0.6930   0.0031
  -5.000  -0.0180   0.01479   0.00803  -0.1027   0.6913   0.0033
  -4.750   0.0072   0.01397   0.00706  -0.1024   0.6898   0.0036
  -4.500   0.0325   0.01327   0.00622  -0.1021   0.6884   0.0041
  -4.250   0.0583   0.01275   0.00559  -0.1020   0.6869   0.0046
  -4.000   0.0837   0.01217   0.00495  -0.1018   0.6850   0.0054
  -3.750   0.1108   0.01195   0.00475  -0.1020   0.6829   0.0068
  -3.500   0.1378   0.01168   0.00442  -0.1021   0.6809   0.0089
  -3.250   0.1649   0.01143   0.00417  -0.1023   0.6791   0.0119
  -3.000   0.1920   0.01115   0.00383  -0.1024   0.6776   0.0165
  -2.750   0.2195   0.01093   0.00356  -0.1026   0.6761   0.0208
  -2.500   0.2473   0.01080   0.00336  -0.1028   0.6746   0.0236
  -2.250   0.2747   0.01059   0.00311  -0.1030   0.6728   0.0297
  -2.000   0.3022   0.01040   0.00294  -0.1032   0.6707   0.0446
  -1.750   0.3280   0.00988   0.00278  -0.1034   0.6686   0.1570
  -1.500   0.3523   0.00913   0.00263  -0.1036   0.6667   0.3557
  -1.250   0.3743   0.00822   0.00256  -0.1033   0.6650   0.6115
  -1.000   0.3987   0.00800   0.00268  -0.1026   0.6633   0.7263
  -0.750   0.4253   0.00806   0.00278  -0.1023   0.6617   0.7753
  -0.500   0.4527   0.00812   0.00283  -0.1024   0.6598   0.7915
  -0.250   0.4808   0.00817   0.00286  -0.1026   0.6578   0.7996
   0.000   0.5088   0.00821   0.00287  -0.1029   0.6557   0.8059
   0.250   0.5369   0.00825   0.00289  -0.1032   0.6536   0.8121
   0.500   0.5652   0.00829   0.00289  -0.1035   0.6516   0.8178
   0.750   0.5932   0.00832   0.00290  -0.1038   0.6499   0.8226
   1.000   0.6216   0.00837   0.00291  -0.1041   0.6483   0.8277
   1.250   0.6495   0.00842   0.00296  -0.1045   0.6462   0.8321
   1.500   0.6771   0.00847   0.00303  -0.1047   0.6439   0.8361
   1.750   0.7051   0.00852   0.00309  -0.1050   0.6416   0.8402
   2.000   0.7333   0.00857   0.00314  -0.1054   0.6395   0.8441
   2.250   0.7610   0.00860   0.00318  -0.1057   0.6374   0.8472
   2.500   0.7889   0.00865   0.00322  -0.1060   0.6356   0.8506
   2.750   0.8167   0.00871   0.00331  -0.1063   0.6335   0.8543
   3.000   0.8443   0.00878   0.00341  -0.1067   0.6308   0.8581
   3.250   0.8713   0.00882   0.00351  -0.1068   0.6280   0.8611
   3.500   0.8985   0.00886   0.00357  -0.1070   0.6247   0.8645
   3.750   0.9256   0.00889   0.00361  -0.1072   0.6201   0.8680
   4.000   0.9519   0.00893   0.00370  -0.1072   0.6131   0.8718
   4.250   0.9783   0.00897   0.00374  -0.1072   0.6085   0.8750
   4.500   1.0044   0.00904   0.00389  -0.1073   0.6042   0.8786
   4.750   1.0308   0.00911   0.00402  -0.1074   0.5998   0.8824
   5.000   1.0570   0.00919   0.00413  -0.1074   0.5951   0.8861
   5.250   1.0822   0.00926   0.00430  -0.1072   0.5893   0.8897
   5.500   1.1056   0.00935   0.00441  -0.1067   0.5778   0.8941
   6.000   1.1299   0.01011   0.00489  -0.1015   0.4988   0.9077
   6.250   1.1126   0.01125   0.00571  -0.0937   0.4315   0.9257
   6.500   1.0894   0.01323   0.00740  -0.0867   0.3626   1.0000
   7.000   1.0629   0.01733   0.01101  -0.0775   0.2661   1.0000
   7.250   1.0533   0.01937   0.01280  -0.0736   0.2168   1.0000
   7.500   1.0365   0.02192   0.01497  -0.0691   0.1503   1.0000
   7.750   1.0054   0.02550   0.01794  -0.0634   0.0438   1.0000
   8.000   1.0125   0.02682   0.01919  -0.0618   0.0261   1.0000
   8.250   1.0173   0.02832   0.02062  -0.0599   0.0052   1.0000
   8.500   1.0289   0.02941   0.02175  -0.0587   0.0034   1.0000
   8.750   1.0420   0.03043   0.02283  -0.0578   0.0032   1.0000
   9.000   1.0544   0.03153   0.02399  -0.0568   0.0031   1.0000
   9.250   1.0663   0.03269   0.02523  -0.0558   0.0029   1.0000
   9.500   1.0776   0.03393   0.02654  -0.0548   0.0028   1.0000
   9.750   1.0886   0.03521   0.02789  -0.0538   0.0028   1.0000
  10.000   1.0984   0.03660   0.02940  -0.0527   0.0026   1.0000
  10.250   1.1082   0.03804   0.03089  -0.0518   0.0024   1.0000
  10.500   1.1154   0.03971   0.03263  -0.0507   0.0020   1.0000
  10.750   1.1209   0.04157   0.03458  -0.0495   0.0019   1.0000
  11.000   1.1259   0.04353   0.03662  -0.0484   0.0017   1.0000
  11.250   1.1345   0.04521   0.03837  -0.0476   0.0016   1.0000
  11.500   1.1395   0.04726   0.04051  -0.0465   0.0016   1.0000
  11.750   1.1483   0.04898   0.04230  -0.0459   0.0015   1.0000
  12.000   1.1538   0.05104   0.04445  -0.0450   0.0014   1.0000
  12.250   1.1589   0.05320   0.04670  -0.0442   0.0014   1.0000
  12.500   1.1642   0.05537   0.04895  -0.0434   0.0013   1.0000
  12.750   1.1693   0.05758   0.05126  -0.0427   0.0012   1.0000
  13.000   1.1750   0.05978   0.05354  -0.0420   0.0012   1.0000
  13.250   1.1809   0.06198   0.05584  -0.0414   0.0012   1.0000
  13.500   1.1866   0.06424   0.05824  -0.0408   0.0011   1.0000
  13.750   1.1926   0.06649   0.06058  -0.0402   0.0010   1.0000
  14.000   1.1991   0.06872   0.06293  -0.0398   0.0010   1.0000
  14.250   1.2050   0.07109   0.06541  -0.0393   0.0009   1.0000
  14.500   1.2108   0.07352   0.06798  -0.0389   0.0009   1.0000
  14.750   1.2162   0.07606   0.07065  -0.0386   0.0009   1.0000
  15.000   1.2202   0.07883   0.07358  -0.0383   0.0009   1.0000
  15.250   1.2227   0.08190   0.07682  -0.0381   0.0009   1.0000
  15.500   1.2250   0.08508   0.08017  -0.0381   0.0009   1.0000
  15.750   1.2242   0.08875   0.08402  -0.0383   0.0009   1.0000
  16.000   1.2216   0.09278   0.08824  -0.0387   0.0009   1.0000
  16.250   1.2171   0.09720   0.09287  -0.0392   0.0009   1.0000
  16.500   1.2107   0.10201   0.09788  -0.0402   0.0009   1.0000
  16.750   1.2019   0.10735   0.10343  -0.0415   0.0009   1.0000
  17.000   1.1918   0.11306   0.10936  -0.0432   0.0009   1.0000
  17.250   1.1795   0.11934   0.11586  -0.0453   0.0009   1.0000
  17.500   1.1656   0.12615   0.12289  -0.0480   0.0009   1.0000
  17.750   1.1510   0.13335   0.13029  -0.0512   0.0009   1.0000
  18.000   1.1356   0.14105   0.13819  -0.0550   0.0009   1.0000
  18.250   1.1205   0.14898   0.14631  -0.0592   0.0009   1.0000
  18.500   1.1042   0.15764   0.15515  -0.0642   0.0010   1.0000
  18.750   1.0877   0.16691   0.16458  -0.0697   0.0010   1.0000
  19.000   1.0727   0.17644   0.17425  -0.0755   0.0010   1.0000
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