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FX 73-CL3-152 (fx73cl3152-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: FX 73-CL3-152 (fx73cl3152-il)
Reynolds number: 200,000
Max Cl/Cd: 63.96 at α=5.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx73cl3152-il-200000.txt
Download as CSV file: xf-fx73cl3152-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 73-CL3-152                                   
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000   0.1049   0.10690   0.10325  -0.0999   0.9494   0.0562
  -9.750   0.1249   0.10332   0.09965  -0.1052   0.9454   0.0584
  -9.500   0.1379   0.09962   0.09594  -0.1132   0.9415   0.0596
  -9.250   0.1643   0.09591   0.09222  -0.1143   0.9355   0.0603
  -9.000   0.1878   0.09280   0.08909  -0.1172   0.9287   0.0615
  -8.750   0.2141   0.08936   0.08561  -0.1222   0.9232   0.0636
  -8.500   0.2051   0.08796   0.08420  -0.1267   0.9096   0.0662
  -8.250   0.2212   0.08452   0.08075  -0.1278   0.9002   0.0668
  -8.000   0.2452   0.08162   0.07781  -0.1276   0.8898   0.0677
  -7.750   0.2566   0.07972   0.07589  -0.1271   0.8765   0.0691
  -7.500   0.2653   0.07776   0.07390  -0.1275   0.8626   0.0717
  -7.250   0.2665   0.06419   0.06041  -0.1168   0.7808   0.0749
  -7.000   0.2620   0.07348   0.06957  -0.1286   0.8302   0.0749
  -6.750   0.2749   0.07155   0.06760  -0.1268   0.8093   0.0759
  -6.500   0.2815   0.06989   0.06590  -0.1251   0.7812   0.0772
  -6.250   0.2858   0.06818   0.06407  -0.1241   0.7454   0.0791
  -6.000   0.2573   0.06618   0.06195  -0.1303   0.7145   0.0829
  -5.750   0.2720   0.06420   0.05970  -0.1261   0.6828   0.0836
  -5.500   0.2852   0.06279   0.05808  -0.1236   0.6568   0.0845
  -5.250   0.2965   0.06144   0.05657  -0.1226   0.6374   0.0861
  -5.000   0.3062   0.05983   0.05483  -0.1233   0.6223   0.0889
  -4.750   0.3143   0.05595   0.05086  -0.1317   0.6114   0.0936
  -4.500   0.3601   0.02774   0.02127  -0.1752   0.6103   0.0661
  -4.250   0.3882   0.02486   0.01790  -0.1776   0.5983   0.0658
  -4.000   0.4166   0.02281   0.01522  -0.1792   0.5884   0.0667
  -3.750   0.4418   0.02214   0.01461  -0.1790   0.5784   0.0686
  -3.500   0.4693   0.02139   0.01355  -0.1793   0.5705   0.0705
  -3.250   0.4971   0.02038   0.01221  -0.1795   0.5630   0.0723
  -3.000   0.5251   0.01969   0.01112  -0.1795   0.5561   0.0740
  -2.750   0.5523   0.01917   0.01052  -0.1795   0.5503   0.0770
  -2.500   0.5792   0.01883   0.01009  -0.1793   0.5442   0.0806
  -2.250   0.6063   0.01834   0.00945  -0.1790   0.5384   0.0839
  -2.000   0.6336   0.01811   0.00917  -0.1788   0.5333   0.0881
  -1.750   0.6615   0.01792   0.00883  -0.1787   0.5288   0.0939
  -1.500   0.6882   0.01773   0.00870  -0.1784   0.5242   0.1005
  -1.250   0.7153   0.01752   0.00849  -0.1781   0.5199   0.1086
  -1.000   0.7428   0.01742   0.00836  -0.1779   0.5159   0.1210
  -0.750   0.7714   0.01744   0.00832  -0.1779   0.5121   0.1389
  -0.500   0.7983   0.01740   0.00835  -0.1776   0.5083   0.1641
  -0.250   0.8248   0.01745   0.00847  -0.1773   0.5044   0.1912
   0.000   0.8520   0.01757   0.00858  -0.1771   0.5008   0.2165
   0.250   0.8794   0.01768   0.00870  -0.1769   0.4975   0.2394
   0.500   0.9073   0.01785   0.00884  -0.1768   0.4943   0.2618
   0.750   0.9353   0.01811   0.00908  -0.1768   0.4911   0.2845
   1.000   0.9605   0.01822   0.00929  -0.1762   0.4878   0.3079
   1.250   0.9865   0.01837   0.00950  -0.1758   0.4845   0.3330
   1.500   1.0131   0.01852   0.00967  -0.1755   0.4813   0.3587
   1.750   1.0401   0.01865   0.00984  -0.1752   0.4783   0.3848
   2.000   1.0681   0.01885   0.01003  -0.1751   0.4753   0.4154
   2.250   1.0962   0.01919   0.01041  -0.1752   0.4724   0.4487
   2.500   1.1200   0.01932   0.01071  -0.1744   0.4696   0.4851
   2.750   1.1441   0.01949   0.01102  -0.1736   0.4664   0.5262
   3.000   1.1693   0.01967   0.01131  -0.1731   0.4633   0.5730
   3.250   1.1959   0.01985   0.01158  -0.1728   0.4605   0.6237
   3.500   1.2249   0.02004   0.01181  -0.1729   0.4578   0.6826
   3.750   1.2586   0.02016   0.01204  -0.1741   0.4551   0.7736
   4.000   1.2917   0.02039   0.01240  -0.1754   0.4521   1.0000
   4.250   1.3158   0.02074   0.01277  -0.1749   0.4491   1.0000
   4.500   1.3407   0.02112   0.01313  -0.1744   0.4461   1.0000
   4.750   1.3665   0.02148   0.01346  -0.1742   0.4433   1.0000
   5.000   1.3933   0.02184   0.01375  -0.1740   0.4407   1.0000
   5.250   1.4213   0.02222   0.01403  -0.1741   0.4382   1.0000
   5.500   1.4508   0.02283   0.01452  -0.1746   0.4355   1.0000
   5.750   1.4716   0.02325   0.01503  -0.1735   0.4328   1.0000
   6.000   1.4927   0.02368   0.01553  -0.1725   0.4297   1.0000
   6.250   1.5153   0.02412   0.01601  -0.1717   0.4267   1.0000
   6.500   1.5394   0.02452   0.01641  -0.1712   0.4240   1.0000
   6.750   1.5654   0.02490   0.01676  -0.1710   0.4215   1.0000
   7.000   1.5933   0.02533   0.01711  -0.1711   0.4192   1.0000
   7.250   1.6214   0.02605   0.01777  -0.1714   0.4167   1.0000
   7.500   1.6375   0.02658   0.01847  -0.1697   0.4140   1.0000
   7.750   1.6550   0.02713   0.01912  -0.1682   0.4107   1.0000
   8.000   1.6749   0.02760   0.01965  -0.1671   0.4076   1.0000
   8.250   1.6975   0.02801   0.02006  -0.1664   0.4048   1.0000
   8.500   1.7234   0.02839   0.02043  -0.1662   0.4024   1.0000
   8.750   1.7524   0.02887   0.02084  -0.1666   0.4002   1.0000
   9.000   1.7727   0.02968   0.02172  -0.1658   0.3976   1.0000
   9.250   1.7828   0.03046   0.02268  -0.1633   0.3947   1.0000
   9.500   1.7959   0.03117   0.02352  -0.1612   0.3915   1.0000
   9.750   1.8130   0.03172   0.02412  -0.1598   0.3886   1.0000
  10.000   1.8344   0.03211   0.02453  -0.1590   0.3860   1.0000
  10.250   1.8616   0.03246   0.02486  -0.1591   0.3838   1.0000
  10.500   1.8935   0.03304   0.02537  -0.1601   0.3816   1.0000
  10.750   1.8953   0.03417   0.02671  -0.1565   0.3789   1.0000
  11.000   1.8946   0.03530   0.02805  -0.1527   0.3759   1.0000
  11.250   1.8969   0.03624   0.02911  -0.1492   0.3729   1.0000
  11.500   1.9082   0.03687   0.02980  -0.1470   0.3703   1.0000
  11.750   1.9278   0.03728   0.03023  -0.1460   0.3680   1.0000
  12.000   1.9585   0.03756   0.03051  -0.1467   0.3660   1.0000
  12.250   1.9930   0.03818   0.03109  -0.1482   0.3638   1.0000
  12.500   1.9516   0.04046   0.03368  -0.1393   0.3608   1.0000
  12.750   1.9243   0.04289   0.03634  -0.1333   0.3574   1.0000
  13.000   1.9181   0.04461   0.03818  -0.1300   0.3544   1.0000
  13.250   1.9402   0.04464   0.03822  -0.1294   0.3517   1.0000
  13.500   2.0050   0.04222   0.03561  -0.1329   0.3486   1.0000
  13.750   1.9795   0.04479   0.03837  -0.1277   0.3450   1.0000
  14.000   1.9118   0.05069   0.04459  -0.1204   0.3407   1.0000
  14.250   1.9094   0.05244   0.04643  -0.1184   0.3371   1.0000
  14.500   1.9487   0.05100   0.04495  -0.1188   0.3346   1.0000
  14.750   2.0121   0.04818   0.04200  -0.1210   0.3323   1.0000
  15.000   1.6433   0.09024   0.08486  -0.1133   0.3156   1.0000
  15.250   1.6915   0.08618   0.08081  -0.1121   0.3152   1.0000
  15.500   1.7458   0.08148   0.07613  -0.1109   0.3148   1.0000
  15.750   1.8104   0.07579   0.07042  -0.1099   0.3144   1.0000
  16.000   1.9217   0.06543   0.05994  -0.1098   0.3147   1.0000
  16.750   1.8378   0.08280   0.07767  -0.1083   0.3003   1.0000
  17.000   1.3475   0.16796   0.16312  -0.1370   0.2319   1.0000
  17.250   1.3698   0.16706   0.16226  -0.1361   0.2305   1.0000
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