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RUTAN CANARD AIRFOIL (amsoil1-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: RUTAN CANARD AIRFOIL (amsoil1-il)
Reynolds number: 100,000
Max Cl/Cd: 48.61 at α=5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-amsoil1-il-100000.txt
Download as CSV file: xf-amsoil1-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: RUTAN CANARD AIRFOIL                            
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.4492   0.10596   0.10062  -0.0231   1.0000   0.1257
  -9.250  -0.4843   0.10217   0.09696  -0.0335   1.0000   0.1302
  -9.000  -0.4762   0.09701   0.09185  -0.0334   1.0000   0.1321
  -8.750  -0.4497   0.09424   0.08905  -0.0297   1.0000   0.1351
  -8.500  -0.4425   0.09112   0.08596  -0.0303   1.0000   0.1392
  -8.250  -0.4624   0.08702   0.08197  -0.0362   1.0000   0.1447
  -8.000  -0.5294   0.08484   0.07979  -0.0406   1.0000   0.1466
  -7.750  -0.5441   0.08117   0.07619  -0.0380   1.0000   0.1478
  -7.500  -0.5138   0.07783   0.07300  -0.0343   1.0000   0.1505
  -7.250  -0.5180   0.07615   0.07138  -0.0307   1.0000   0.1529
  -7.000  -0.5311   0.07434   0.06958  -0.0279   1.0000   0.1561
  -6.750  -0.5819   0.07396   0.06875  -0.0284   1.0000   0.1641
  -6.500  -0.5738   0.06864   0.06366  -0.0263   1.0000   0.1664
  -6.250  -0.5643   0.06641   0.06156  -0.0233   1.0000   0.1699
  -6.000  -0.5674   0.06463   0.05961  -0.0227   1.0000   0.1799
  -5.750  -0.5670   0.06099   0.05593  -0.0217   1.0000   0.1858
  -5.500  -0.5585   0.05878   0.05376  -0.0198   1.0000   0.1909
  -5.250  -0.5358   0.05516   0.04995  -0.0231   0.9958   0.2059
  -5.000  -0.4924   0.04098   0.03379  -0.0318   0.9916   0.1180
  -4.750  -0.4591   0.03737   0.02974  -0.0338   0.9875   0.1111
  -4.500  -0.4231   0.03431   0.02619  -0.0361   0.9841   0.1094
  -4.250  -0.3903   0.03229   0.02377  -0.0376   0.9795   0.1112
  -4.000  -0.3547   0.03041   0.02147  -0.0394   0.9752   0.1124
  -3.750  -0.3149   0.02917   0.01974  -0.0417   0.9716   0.1154
  -3.500  -0.2853   0.02767   0.01825  -0.0427   0.9670   0.1197
  -3.250  -0.2505   0.02674   0.01722  -0.0443   0.9623   0.1244
  -3.000  -0.2104   0.02595   0.01619  -0.0467   0.9586   0.1315
  -2.750  -0.1814   0.02515   0.01549  -0.0474   0.9536   0.1388
  -2.500  -0.1489   0.02460   0.01484  -0.0484   0.9487   0.1482
  -2.250  -0.1107   0.02396   0.01431  -0.0506   0.9448   0.1618
  -2.000  -0.0797   0.02342   0.01392  -0.0516   0.9400   0.1775
  -1.750  -0.0518   0.02298   0.01364  -0.0520   0.9344   0.1973
  -1.500  -0.0164   0.02239   0.01332  -0.0537   0.9303   0.2310
  -1.250   0.0156   0.02008   0.01318  -0.0550   0.9279   0.6311
  -1.000   0.0091   0.02033   0.01407  -0.0449   0.9202   0.8747
  -0.750   0.1538   0.02088   0.01435  -0.0635   0.9279   0.9969
  -0.500   0.1681   0.02115   0.01453  -0.0622   0.9187   1.0000
  -0.250   0.2022   0.02130   0.01458  -0.0641   0.9132   1.0000
   0.000   0.2089   0.02164   0.01486  -0.0612   0.9040   1.0000
   0.250   0.2348   0.02188   0.01502  -0.0616   0.8974   1.0000
   0.500   0.2787   0.02209   0.01516  -0.0650   0.8938   1.0000
   0.750   0.2653   0.02260   0.01563  -0.0585   0.8817   1.0000
   1.000   0.3060   0.02285   0.01584  -0.0612   0.8775   1.0000
   1.250   0.3085   0.02344   0.01638  -0.0576   0.8675   1.0000
   1.500   0.3432   0.02375   0.01666  -0.0592   0.8617   1.0000
   1.750   0.3888   0.02395   0.01687  -0.0624   0.8581   1.0000
   2.000   0.3899   0.02469   0.01758  -0.0586   0.8462   1.0000
   2.250   0.4351   0.02478   0.01770  -0.0616   0.8414   1.0000
   2.500   0.4581   0.02495   0.01788  -0.0605   0.8279   1.0000
   2.750   0.5075   0.02383   0.01680  -0.0617   0.8114   1.0000
   3.000   0.5515   0.02245   0.01545  -0.0615   0.7947   1.0000
   3.250   0.5883   0.02128   0.01431  -0.0604   0.7801   1.0000
   3.500   0.6247   0.02009   0.01313  -0.0593   0.7685   1.0000
   3.750   0.6490   0.01966   0.01275  -0.0574   0.7531   1.0000
   4.000   0.6752   0.01904   0.01217  -0.0556   0.7373   1.0000
   4.250   0.7024   0.01826   0.01143  -0.0536   0.7196   1.0000
   4.500   0.7304   0.01732   0.01051  -0.0515   0.6984   1.0000
   4.750   0.7535   0.01664   0.00988  -0.0491   0.6666   1.0000
   5.000   0.7754   0.01595   0.00911  -0.0461   0.6099   1.0000
   5.250   0.7806   0.01657   0.00842  -0.0403   0.3722   1.0000
   5.500   0.7808   0.01896   0.00963  -0.0364   0.2438   1.0000
   5.750   0.7941   0.02041   0.01065  -0.0342   0.2073   1.0000
   6.000   0.8125   0.02158   0.01160  -0.0328   0.1849   1.0000
   6.250   0.8333   0.02273   0.01256  -0.0317   0.1687   1.0000
   6.500   0.8564   0.02395   0.01359  -0.0310   0.1559   1.0000
   6.750   0.8807   0.02497   0.01457  -0.0304   0.1452   1.0000
   7.000   0.9070   0.02626   0.01582  -0.0302   0.1368   1.0000
   7.250   0.9329   0.02746   0.01691  -0.0300   0.1292   1.0000
   7.500   0.9603   0.02894   0.01844  -0.0298   0.1233   1.0000
   7.750   0.9862   0.03021   0.01979  -0.0295   0.1179   1.0000
   8.000   1.0148   0.03218   0.02159  -0.0300   0.1131   1.0000
   8.250   1.0374   0.03355   0.02330  -0.0290   0.1096   1.0000
   8.500   1.0611   0.03522   0.02517  -0.0284   0.1063   1.0000
   8.750   1.0851   0.03684   0.02683  -0.0281   0.1030   1.0000
   9.000   1.1086   0.03944   0.02946  -0.0280   0.1001   1.0000
   9.250   1.1250   0.04156   0.03204  -0.0264   0.0986   1.0000
   9.500   1.1397   0.04405   0.03495  -0.0248   0.0970   1.0000
   9.750   1.1521   0.04664   0.03792  -0.0231   0.0952   1.0000
  10.000   1.1633   0.04927   0.04085  -0.0215   0.0935   1.0000
  10.250   1.1708   0.05240   0.04432  -0.0196   0.0928   1.0000
  10.500   1.1721   0.05609   0.04840  -0.0173   0.0928   1.0000
  10.750   1.1669   0.06008   0.05277  -0.0146   0.0929   1.0000
  11.000   1.1535   0.06441   0.05748  -0.0116   0.0935   1.0000
  11.250   1.1281   0.06902   0.06245  -0.0081   0.0947   1.0000
  11.500   1.0983   0.07374   0.06743  -0.0053   0.0960   1.0000
  11.750   1.0701   0.07897   0.07287  -0.0040   0.0973   1.0000
  12.000   1.0469   0.08458   0.07862  -0.0040   0.0985   1.0000
  12.250   1.0374   0.09013   0.08424  -0.0045   0.0996   1.0000
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