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FX 61-168 AIRFOIL (fx61168-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: FX 61-168 AIRFOIL (fx61168-il)
Reynolds number: 500,000
Max Cl/Cd: 101.21 at α=6.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx61168-il-500000-n5.txt
Download as CSV file: xf-fx61168-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 61-168 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
  ------ -------- --------- --------- -------- -------- --------
 -13.000  -0.5796   0.07067   0.06810  -0.0658   1.0000   0.0052
 -12.750  -0.6342   0.05890   0.05601  -0.0719   1.0000   0.0050
 -12.500  -0.6618   0.05287   0.04977  -0.0737   1.0000   0.0051
 -12.250  -0.6804   0.04724   0.04387  -0.0762   0.9992   0.0051
 -11.750  -0.6867   0.03808   0.03410  -0.0819   0.9903   0.0054
 -11.500  -0.6860   0.03494   0.03072  -0.0825   0.9812   0.0054
 -11.000  -0.6650   0.03016   0.02548  -0.0840   0.9410   0.0057
 -10.750  -0.6128   0.02737   0.02233  -0.0926   0.9193   0.0059
 -10.500  -0.5366   0.02456   0.01914  -0.1059   0.8921   0.0063
 -10.000  -0.4470   0.02260   0.01660  -0.1169   0.8021   0.0070
  -9.750  -0.4301   0.02197   0.01577  -0.1163   0.7736   0.0072
  -9.250  -0.3997   0.02065   0.01411  -0.1139   0.7337   0.0079
  -9.000  -0.3855   0.01997   0.01328  -0.1125   0.7189   0.0081
  -8.750  -0.3715   0.01933   0.01251  -0.1110   0.7068   0.0084
  -8.500  -0.3604   0.01862   0.01170  -0.1090   0.6965   0.0086
  -8.250  -0.3506   0.01791   0.01092  -0.1070   0.6877   0.0088
  -8.000  -0.3352   0.01728   0.01023  -0.1059   0.6794   0.0091
  -7.750  -0.3173   0.01676   0.00964  -0.1051   0.6721   0.0095
  -7.500  -0.2984   0.01624   0.00903  -0.1044   0.6651   0.0099
  -7.000  -0.2575   0.01530   0.00794  -0.1032   0.6539   0.0109
  -6.750  -0.2356   0.01486   0.00744  -0.1028   0.6488   0.0118
  -6.250  -0.1892   0.01404   0.00652  -0.1023   0.6402   0.0136
  -6.000  -0.1645   0.01368   0.00610  -0.1022   0.6358   0.0145
  -5.750  -0.1396   0.01331   0.00567  -0.1022   0.6316   0.0158
  -5.500  -0.1139   0.01299   0.00530  -0.1023   0.6278   0.0177
  -5.250  -0.0871   0.01271   0.00498  -0.1025   0.6243   0.0201
  -5.000  -0.0602   0.01240   0.00467  -0.1028   0.6208   0.0249
  -4.750  -0.0330   0.01211   0.00439  -0.1031   0.6176   0.0344
  -4.500  -0.0055   0.01179   0.00411  -0.1036   0.6144   0.0547
  -4.250   0.0226   0.01129   0.00378  -0.1044   0.6113   0.1059
  -4.000   0.0534   0.01000   0.00319  -0.1070   0.6078   0.2867
  -3.750   0.0873   0.00908   0.00278  -0.1097   0.6042   0.4324
  -3.500   0.1192   0.00875   0.00269  -0.1110   0.6007   0.5155
  -3.250   0.1494   0.00871   0.00276  -0.1117   0.5978   0.5648
  -3.000   0.1793   0.00876   0.00283  -0.1121   0.5950   0.5889
  -2.750   0.2087   0.00882   0.00286  -0.1124   0.5919   0.5998
  -2.500   0.2385   0.00885   0.00281  -0.1129   0.5888   0.6057
  -2.250   0.2676   0.00889   0.00281  -0.1132   0.5859   0.6096
  -2.000   0.2967   0.00896   0.00281  -0.1135   0.5830   0.6137
  -1.750   0.3263   0.00899   0.00280  -0.1139   0.5796   0.6183
  -1.500   0.3558   0.00902   0.00278  -0.1143   0.5759   0.6222
  -1.250   0.3846   0.00907   0.00281  -0.1146   0.5725   0.6255
  -1.000   0.4136   0.00913   0.00284  -0.1149   0.5696   0.6295
  -0.750   0.4428   0.00921   0.00284  -0.1152   0.5668   0.6338
  -0.500   0.4723   0.00924   0.00286  -0.1157   0.5638   0.6374
  -0.250   0.5011   0.00929   0.00293  -0.1159   0.5609   0.6403
   0.000   0.5300   0.00935   0.00297  -0.1162   0.5579   0.6432
   0.250   0.5588   0.00941   0.00301  -0.1165   0.5548   0.6462
   0.500   0.5877   0.00949   0.00303  -0.1168   0.5516   0.6490
   0.750   0.6171   0.00952   0.00306  -0.1173   0.5477   0.6516
   1.000   0.6454   0.00956   0.00311  -0.1175   0.5436   0.6535
   1.250   0.6737   0.00962   0.00317  -0.1177   0.5398   0.6555
   1.500   0.7019   0.00971   0.00324  -0.1178   0.5364   0.6575
   1.750   0.7307   0.00975   0.00331  -0.1182   0.5326   0.6596
   2.000   0.7593   0.00981   0.00337  -0.1184   0.5287   0.6620
   2.250   0.7878   0.00988   0.00344  -0.1187   0.5250   0.6644
   2.500   0.8162   0.00997   0.00350  -0.1190   0.5214   0.6666
   2.750   0.8445   0.01001   0.00359  -0.1192   0.5166   0.6681
   3.000   0.8721   0.01007   0.00368  -0.1193   0.5109   0.6698
   3.250   0.8994   0.01017   0.00378  -0.1193   0.5057   0.6716
   3.500   0.9274   0.01023   0.00388  -0.1195   0.5001   0.6736
   3.750   0.9546   0.01033   0.00399  -0.1195   0.4940   0.6755
   4.000   0.9820   0.01042   0.00409  -0.1196   0.4871   0.6774
   4.250   1.0091   0.01052   0.00420  -0.1196   0.4798   0.6795
   4.500   1.0363   0.01064   0.00433  -0.1197   0.4725   0.6815
   4.750   1.0622   0.01077   0.00446  -0.1195   0.4627   0.6831
   5.000   1.0882   0.01090   0.00461  -0.1193   0.4516   0.6846
   5.250   1.1137   0.01107   0.00479  -0.1190   0.4411   0.6863
   5.500   1.1385   0.01126   0.00498  -0.1186   0.4291   0.6881
   5.750   1.1625   0.01150   0.00519  -0.1181   0.4156   0.6900
   6.000   1.1867   0.01174   0.00542  -0.1176   0.4037   0.6920
   6.250   1.2115   0.01197   0.00566  -0.1173   0.3930   0.6939
   6.500   1.2351   0.01224   0.00592  -0.1168   0.3806   0.6957
   6.750   1.2577   0.01256   0.00620  -0.1161   0.3661   0.6974
   7.000   1.2792   0.01289   0.00653  -0.1152   0.3511   0.6990
   7.250   1.3002   0.01325   0.00688  -0.1142   0.3359   0.7006
   7.500   1.3181   0.01375   0.00730  -0.1127   0.3138   0.7021
   7.750   1.3336   0.01434   0.00779  -0.1108   0.2868   0.7038
   8.000   1.3455   0.01500   0.00833  -0.1083   0.2586   0.7057
   8.250   1.3527   0.01581   0.00898  -0.1050   0.2278   0.7077
   8.500   1.3582   0.01675   0.00976  -0.1016   0.1961   0.7095
   8.750   1.3629   0.01774   0.01060  -0.0982   0.1695   0.7112
   9.000   1.3675   0.01875   0.01150  -0.0950   0.1446   0.7127
   9.250   1.3714   0.01981   0.01249  -0.0918   0.1255   0.7144
   9.500   1.3760   0.02090   0.01352  -0.0889   0.1080   0.7161
   9.750   1.3789   0.02213   0.01471  -0.0860   0.0923   0.7180
  10.000   1.3830   0.02340   0.01597  -0.0835   0.0798   0.7198
  10.250   1.3848   0.02492   0.01745  -0.0811   0.0664   0.7215
  10.500   1.3866   0.02659   0.01911  -0.0790   0.0561   0.7233
  10.750   1.3894   0.02831   0.02084  -0.0773   0.0471   0.7251
  11.000   1.3911   0.03025   0.02278  -0.0757   0.0386   0.7267
  11.250   1.3923   0.03236   0.02490  -0.0744   0.0315   0.7284
  11.500   1.3936   0.03455   0.02712  -0.0733   0.0259   0.7302
  11.750   1.3991   0.03648   0.02911  -0.0725   0.0227   0.7321
  12.000   1.4021   0.03869   0.03138  -0.0717   0.0194   0.7339
  12.250   1.4058   0.04090   0.03365  -0.0711   0.0163   0.7358
  12.500   1.4086   0.04326   0.03606  -0.0706   0.0138   0.7376
  12.750   1.4110   0.04573   0.03858  -0.0702   0.0113   0.7394
  13.000   1.4110   0.04851   0.04141  -0.0698   0.0074   0.7411
  13.500   1.4089   0.05455   0.04757  -0.0694   0.0036   0.7443
  13.750   1.4105   0.05740   0.05052  -0.0694   0.0033   0.7460
  14.000   1.4110   0.06046   0.05367  -0.0695   0.0030   0.7478
  14.250   1.4128   0.06345   0.05677  -0.0697   0.0028   0.7500
  14.500   1.4150   0.06647   0.05989  -0.0701   0.0027   0.7522
  14.750   1.4164   0.06966   0.06319  -0.0705   0.0026   0.7544
  15.000   1.4174   0.07298   0.06662  -0.0711   0.0025   0.7566
  15.250   1.4182   0.07641   0.07015  -0.0717   0.0024   0.7586
  15.500   1.4185   0.07998   0.07384  -0.0725   0.0023   0.7606
  15.750   1.4183   0.08371   0.07771  -0.0735   0.0022   0.7627
  16.000   1.4174   0.08759   0.08170  -0.0745   0.0022   0.7650
  16.250   1.4160   0.09163   0.08586  -0.0757   0.0021   0.7673
  16.500   1.4145   0.09577   0.09012  -0.0770   0.0021   0.7697
  16.750   1.4119   0.10015   0.09462  -0.0785   0.0020   0.7720
  17.000   1.4086   0.10471   0.09931  -0.0802   0.0020   0.7744
  17.250   1.4051   0.10938   0.10411  -0.0820   0.0020   0.7769
  17.500   1.4001   0.11437   0.10924  -0.0840   0.0019   0.7796
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