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FX 69-PR-281 (fx69pr281-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: FX 69-PR-281 (fx69pr281-il)
Reynolds number: 100,000
Max Cl/Cd: 21.49 at α=3.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx69pr281-il-100000.txt
Download as CSV file: xf-fx69pr281-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 69-PR-281                                    
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -13.750   0.0122   0.17103   0.16560  -0.0546   0.9679   0.1709
 -13.500   0.0410   0.16723   0.16179  -0.0601   0.9633   0.1749
 -13.250   0.0341   0.16543   0.15996  -0.0660   0.9552   0.1785
 -13.000   0.0781   0.15946   0.15401  -0.0699   0.9495   0.1798
 -12.750   0.1154   0.15509   0.14963  -0.0748   0.9458   0.1825
 -12.500   0.1345   0.15196   0.14650  -0.0781   0.9361   0.1870
 -12.250   0.1342   0.14929   0.14380  -0.0842   0.9310   0.1906
 -12.000   0.1813   0.14350   0.13802  -0.0886   0.9280   0.1923
 -11.750   0.2087   0.14001   0.13453  -0.0912   0.9187   0.1953
 -11.500   0.2234   0.13708   0.13155  -0.0968   0.9136   0.2018
 -11.250   0.2453   0.13239   0.12683  -0.1029   0.9102   0.2040
 -11.000   0.2867   0.12765   0.12208  -0.1065   0.9012   0.2063
 -10.750   0.3262   0.12335   0.11774  -0.1126   0.8952   0.2111
 -10.500   0.3171   0.12184   0.11614  -0.1204   0.8907   0.2175
 -10.250   0.3690   0.11591   0.11017  -0.1237   0.8779   0.2192
 -10.000   0.4196   0.11134   0.10552  -0.1302   0.8696   0.2234
  -9.750   0.4266   0.10996   0.10407  -0.1335   0.8558   0.2308
  -9.500   0.4415   0.10646   0.10045  -0.1394   0.8465   0.2338
  -9.250   0.4787   0.10288   0.09681  -0.1407   0.8302   0.2361
  -9.000   0.5162   0.09984   0.09361  -0.1449   0.8179   0.2412
  -8.750   0.4485   0.10415   0.09792  -0.1434   0.8044   0.2496
  -8.500   0.5076   0.09751   0.09111  -0.1468   0.7921   0.2511
  -8.250   0.5334   0.09484   0.08843  -0.1451   0.7756   0.2534
  -8.000   0.5645   0.09244   0.08587  -0.1469   0.7639   0.2581
  -7.750   0.5577   0.09224   0.08570  -0.1447   0.7505   0.2653
  -7.500   0.5266   0.09227   0.08568  -0.1444   0.7419   0.2699
  -7.250   0.5694   0.08857   0.08188  -0.1446   0.7297   0.2723
  -7.000   0.5905   0.08680   0.08008  -0.1436   0.7173   0.2760
  -6.750   0.6070   0.08539   0.07852  -0.1442   0.7080   0.2827
  -6.500   0.5447   0.08760   0.08082  -0.1414   0.7013   0.2904
  -6.250   0.5873   0.08375   0.07692  -0.1410   0.6890   0.2924
  -6.000   0.6259   0.08115   0.07414  -0.1420   0.6793   0.2960
  -5.750   0.6346   0.08029   0.07335  -0.1395   0.6685   0.3011
  -5.500   0.5400   0.08539   0.07856  -0.1349   0.6640   0.3125
  -5.250   0.6038   0.07940   0.07240  -0.1370   0.6539   0.3145
  -5.000   0.6366   0.07704   0.07002  -0.1361   0.6435   0.3171
  -4.750   0.6580   0.07555   0.06851  -0.1348   0.6329   0.3211
  -4.500   0.6742   0.07437   0.06719  -0.1346   0.6250   0.3280
  -4.250   0.5982   0.07668   0.06959  -0.1304   0.6219   0.3381
  -4.000   0.6341   0.07363   0.06659  -0.1289   0.6100   0.3400
  -3.750   0.6748   0.07119   0.06399  -0.1295   0.6006   0.3433
  -3.500   0.6933   0.07008   0.06285  -0.1281   0.5917   0.3476
  -3.250   0.6949   0.06963   0.06245  -0.1255   0.5827   0.3547
  -3.000   0.5848   0.07270   0.06572  -0.1167   0.5811   0.3644
  -2.750   0.5037   0.06216   0.05516  -0.1171   0.5804   0.3132
  -2.500   0.5299   0.06010   0.05295  -0.1173   0.5733   0.3142
  -2.250   0.5395   0.05927   0.05213  -0.1147   0.5655   0.3153
  -2.000   0.5442   0.05887   0.05181  -0.1107   0.5566   0.3169
  -1.750   0.4803   0.05306   0.04596  -0.1105   0.5538   0.3069
  -1.500   0.4207   0.04303   0.03537  -0.1173   0.5515   0.3112
  -1.250   0.4607   0.04134   0.03345  -0.1203   0.5452   0.3158
  -1.000   0.4538   0.04169   0.03398  -0.1148   0.5366   0.3176
  -0.750   0.4664   0.04166   0.03399  -0.1121   0.5285   0.3204
  -0.500   0.5065   0.04069   0.03281  -0.1145   0.5220   0.3256
  -0.250   0.5237   0.03954   0.03147  -0.1151   0.5153   0.3311
   0.000   0.5249   0.03867   0.03045  -0.1133   0.5073   0.3357
   0.250   0.5558   0.03766   0.02928  -0.1144   0.5006   0.3402
   0.500   0.6064   0.03740   0.02888  -0.1172   0.4948   0.3453
   0.750   0.5915   0.03787   0.02955  -0.1111   0.4876   0.3476
   1.000   0.6016   0.03788   0.02956  -0.1087   0.4807   0.3516
   1.250   0.6457   0.03713   0.02852  -0.1118   0.4749   0.3586
   1.500   0.6921   0.03660   0.02763  -0.1155   0.4693   0.3653
   1.750   0.6736   0.03718   0.02846  -0.1090   0.4629   0.3673
   2.000   0.6775   0.03747   0.02884  -0.1055   0.4571   0.3706
   2.250   0.7172   0.03727   0.02854  -0.1071   0.4519   0.3769
   2.500   0.7793   0.03698   0.02792  -0.1123   0.4471   0.3860
   2.750   0.7473   0.03797   0.02914  -0.1042   0.4419   0.3877
   3.000   0.7369   0.03880   0.03000  -0.0994   0.4364   0.3911
   3.250   0.7615   0.03867   0.02983  -0.0992   0.4318   0.3969
   3.500   0.8199   0.03815   0.02919  -0.1030   0.4276   0.4055
   3.750   0.8328   0.03887   0.02991  -0.1013   0.4234   0.4116
   4.000   0.7812   0.04139   0.03272  -0.0920   0.4184   0.4117
   4.250   0.7638   0.04331   0.03473  -0.0876   0.4133   0.4153
   4.500   0.8093   0.04275   0.03395  -0.0897   0.4094   0.4251
   4.750   0.8817   0.04125   0.03234  -0.0942   0.4061   0.4375
   5.000   0.8572   0.04361   0.03486  -0.0889   0.4021   0.4408
   5.250   0.5441   0.06851   0.06053  -0.0722   0.3842   0.4115
   5.500   0.6153   0.06419   0.05598  -0.0730   0.3843   0.4247
   5.750   0.7000   0.05868   0.05047  -0.0738   0.3846   0.4401
   6.000   0.8275   0.05164   0.04314  -0.0785   0.3848   0.4639
   6.250   0.1087   0.13086   0.12443  -0.0793   0.3909   0.3745
   6.500   0.1346   0.13296   0.12650  -0.0799   0.3876   0.3807
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