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

FX60-100 10.0% smoothed (fx60100sm-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: FX60-100 10.0% smoothed (fx60100sm-il)
Reynolds number: 1,000,000
Max Cl/Cd: 120.06 at α=4.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx60100sm-il-1000000.txt
Download as CSV file: xf-fx60100sm-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX60-100 10.0% smoothed                         
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.2994   0.09393   0.09238  -0.0383   1.0000   0.0108
 -10.250  -0.2984   0.09061   0.08907  -0.0387   1.0000   0.0109
 -10.000  -0.2977   0.08748   0.08594  -0.0389   1.0000   0.0111
  -6.000  -0.1664   0.01299   0.00846  -0.1169   0.9334   0.0094
  -5.750  -0.1393   0.01192   0.00725  -0.1168   0.9273   0.0096
  -5.500  -0.1119   0.01128   0.00651  -0.1168   0.9207   0.0100
  -5.250  -0.0845   0.01026   0.00536  -0.1169   0.9141   0.0105
  -5.000  -0.0566   0.00953   0.00457  -0.1171   0.9076   0.0112
  -4.750  -0.0285   0.00912   0.00411  -0.1172   0.9007   0.0117
  -4.500  -0.0002   0.00875   0.00367  -0.1172   0.8941   0.0123
  -4.250   0.0283   0.00840   0.00325  -0.1173   0.8869   0.0130
  -4.000   0.0567   0.00819   0.00299  -0.1174   0.8801   0.0139
  -3.750   0.0857   0.00771   0.00242  -0.1176   0.8725   0.0161
  -3.500   0.1143   0.00749   0.00215  -0.1176   0.8653   0.0184
  -3.250   0.1431   0.00724   0.00183  -0.1177   0.8573   0.0226
  -3.000   0.1720   0.00693   0.00157  -0.1179   0.8495   0.0465
  -2.750   0.2013   0.00600   0.00125  -0.1188   0.8411   0.2341
  -2.500   0.2300   0.00569   0.00116  -0.1191   0.8326   0.3180
  -2.250   0.2583   0.00558   0.00112  -0.1192   0.8239   0.3608
  -2.000   0.2868   0.00552   0.00108  -0.1192   0.8142   0.3852
  -1.750   0.3152   0.00548   0.00106  -0.1192   0.8046   0.4087
  -1.500   0.3434   0.00548   0.00104  -0.1191   0.7945   0.4292
  -1.250   0.3717   0.00547   0.00102  -0.1191   0.7833   0.4410
  -1.000   0.4000   0.00548   0.00100  -0.1190   0.7716   0.4520
  -0.750   0.4282   0.00550   0.00099  -0.1189   0.7592   0.4640
  -0.500   0.4563   0.00553   0.00099  -0.1188   0.7461   0.4757
  -0.250   0.4843   0.00556   0.00099  -0.1187   0.7324   0.4869
   0.000   0.5123   0.00560   0.00101  -0.1186   0.7181   0.4982
   0.250   0.5402   0.00566   0.00103  -0.1185   0.7030   0.5091
   0.500   0.5680   0.00572   0.00105  -0.1184   0.6863   0.5202
   0.750   0.5957   0.00580   0.00110  -0.1183   0.6682   0.5316
   1.000   0.6232   0.00589   0.00114  -0.1181   0.6498   0.5430
   1.250   0.6508   0.00598   0.00120  -0.1180   0.6302   0.5551
   1.500   0.6779   0.00612   0.00127  -0.1178   0.6062   0.5675
   1.750   0.7048   0.00628   0.00135  -0.1175   0.5783   0.5806
   2.000   0.7318   0.00644   0.00144  -0.1173   0.5514   0.5941
   2.250   0.7588   0.00660   0.00155  -0.1171   0.5259   0.6083
   2.500   0.7857   0.00678   0.00167  -0.1169   0.5011   0.6234
   2.750   0.8127   0.00693   0.00179  -0.1168   0.4789   0.6393
   3.000   0.8397   0.00710   0.00192  -0.1166   0.4564   0.6565
   3.250   0.8662   0.00730   0.00207  -0.1163   0.4298   0.6753
   3.500   0.8928   0.00751   0.00224  -0.1161   0.4044   0.6962
   3.750   0.9193   0.00770   0.00241  -0.1159   0.3799   0.7205
   4.000   0.9454   0.00791   0.00260  -0.1156   0.3541   0.7493
   4.250   0.9709   0.00814   0.00282  -0.1152   0.3237   0.7880
   4.500   0.9935   0.00828   0.00305  -0.1142   0.2918   0.8736
   4.750   1.0157   0.00846   0.00323  -0.1130   0.2627   1.0000
   5.000   1.0410   0.00887   0.00349  -0.1126   0.2320   1.0000
   5.250   1.0659   0.00933   0.00379  -0.1122   0.1998   1.0000
   5.500   1.0905   0.00981   0.00411  -0.1118   0.1680   1.0000
   5.750   1.1153   0.01026   0.00443  -0.1114   0.1429   1.0000
   6.000   1.1401   0.01069   0.00476  -0.1110   0.1228   1.0000
   6.250   1.1649   0.01112   0.00510  -0.1105   0.1068   1.0000
   6.500   1.1899   0.01151   0.00544  -0.1101   0.0950   1.0000
   6.750   1.2152   0.01185   0.00576  -0.1097   0.0871   1.0000
   7.000   1.2398   0.01225   0.00613  -0.1093   0.0786   1.0000
   7.250   1.2648   0.01258   0.00645  -0.1089   0.0728   1.0000
   7.500   1.2892   0.01298   0.00684  -0.1084   0.0662   1.0000
   7.750   1.3142   0.01330   0.00715  -0.1080   0.0616   1.0000
   8.000   1.3378   0.01376   0.00757  -0.1074   0.0550   1.0000
   8.250   1.3627   0.01404   0.00789  -0.1069   0.0521   1.0000
   8.500   1.3862   0.01446   0.00830  -0.1064   0.0476   1.0000
   8.750   1.4098   0.01487   0.00872  -0.1058   0.0435   1.0000
   9.000   1.4332   0.01526   0.00913  -0.1051   0.0396   1.0000
   9.250   1.4554   0.01578   0.00961  -0.1044   0.0344   1.0000
   9.500   1.4776   0.01626   0.01009  -0.1036   0.0298   1.0000
   9.750   1.4984   0.01685   0.01067  -0.1026   0.0241   1.0000
  10.000   1.5175   0.01760   0.01138  -0.1014   0.0178   1.0000
  10.250   1.5355   0.01842   0.01219  -0.1001   0.0129   1.0000
  10.500   1.5525   0.01929   0.01308  -0.0986   0.0099   1.0000
  10.750   1.5690   0.02015   0.01396  -0.0970   0.0082   1.0000
  11.000   1.5841   0.02107   0.01496  -0.0952   0.0070   1.0000
  11.250   1.5994   0.02183   0.01580  -0.0934   0.0064   1.0000
  11.500   1.6108   0.02268   0.01671  -0.0910   0.0059   1.0000
  11.750   1.6184   0.02372   0.01782  -0.0881   0.0055   1.0000
  12.000   1.6204   0.02518   0.01942  -0.0846   0.0050   1.0000
  12.250   1.6294   0.02619   0.02053  -0.0823   0.0049   1.0000
  12.500   1.6374   0.02733   0.02176  -0.0800   0.0048   1.0000
  12.750   1.6441   0.02860   0.02314  -0.0778   0.0046   1.0000
  13.000   1.6493   0.03006   0.02469  -0.0756   0.0045   1.0000
  13.250   1.6539   0.03163   0.02637  -0.0736   0.0044   1.0000
  13.500   1.6570   0.03342   0.02827  -0.0717   0.0043   1.0000
  13.750   1.6596   0.03534   0.03029  -0.0700   0.0042   1.0000
  14.000   1.6607   0.03751   0.03258  -0.0685   0.0041   1.0000
  14.250   1.6608   0.03988   0.03506  -0.0672   0.0040   1.0000
  14.500   1.6591   0.04259   0.03788  -0.0662   0.0039   1.0000
  14.750   1.6561   0.04562   0.04103  -0.0655   0.0038   1.0000
  15.000   1.6510   0.04906   0.04460  -0.0652   0.0038   1.0000
  15.250   1.6434   0.05305   0.04874  -0.0653   0.0037   1.0000
  15.500   1.6341   0.05752   0.05335  -0.0660   0.0036   1.0000
  15.750   1.6221   0.06270   0.05868  -0.0672   0.0036   1.0000
  16.000   1.6088   0.06847   0.06460  -0.0690   0.0035   1.0000
  16.250   1.5936   0.07491   0.07120  -0.0715   0.0035   1.0000
  16.500   1.5771   0.08194   0.07838  -0.0746   0.0035   1.0000
  16.750   1.5592   0.08961   0.08621  -0.0782   0.0035   1.0000
  17.000   1.5405   0.09774   0.09450  -0.0823   0.0035   1.0000
  17.250   1.5204   0.10649   0.10340  -0.0869   0.0035   1.0000
  17.500   1.5016   0.11520   0.11227  -0.0916   0.0035   1.0000
  17.750   1.4833   0.12405   0.12125  -0.0965   0.0035   1.0000
<< Back to FX60-100 10.0% smoothed (fx60100sm-il)

Polar data table (+)

Polar graphs


<< Back to FX60-100 10.0% smoothed (fx60100sm-il)