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RUTAN CANARD AIRFOIL (amsoil1-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: RUTAN CANARD AIRFOIL (amsoil1-il)
Reynolds number: 50,000
Max Cl/Cd: 31.87 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-amsoil1-il-50000-n5.txt
Download as CSV file: xf-amsoil1-il-50000-n5.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 =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.4881   0.09652   0.08875  -0.0375   1.0000   0.0785
  -9.250  -0.4858   0.09235   0.08462  -0.0393   1.0000   0.0779
  -9.000  -0.4897   0.08740   0.07971  -0.0425   1.0000   0.0774
  -8.750  -0.4996   0.08245   0.07481  -0.0456   1.0000   0.0770
  -8.500  -0.5119   0.07793   0.07030  -0.0474   1.0000   0.0768
  -8.250  -0.5240   0.07364   0.06598  -0.0482   1.0000   0.0768
  -8.000  -0.5370   0.06987   0.06214  -0.0477   1.0000   0.0768
  -7.750  -0.5502   0.06652   0.05870  -0.0459   1.0000   0.0769
  -7.500  -0.5612   0.06336   0.05540  -0.0438   1.0000   0.0770
  -7.250  -0.5691   0.06024   0.05210  -0.0415   1.0000   0.0771
  -7.000  -0.5734   0.05711   0.04874  -0.0394   1.0000   0.0772
  -6.750  -0.5742   0.05396   0.04530  -0.0375   1.0000   0.0774
  -6.500  -0.5726   0.05066   0.04157  -0.0357   1.0000   0.0782
  -6.250  -0.5653   0.04815   0.03880  -0.0342   1.0000   0.0796
  -6.000  -0.5537   0.04659   0.03719  -0.0328   1.0000   0.0812
  -5.750  -0.5261   0.04400   0.03427  -0.0346   0.9948   0.0833
  -5.500  -0.4979   0.04122   0.03103  -0.0362   0.9893   0.0849
  -5.250  -0.4671   0.03867   0.02790  -0.0380   0.9843   0.0882
  -5.000  -0.4377   0.03674   0.02565  -0.0393   0.9790   0.0912
  -4.750  -0.4062   0.03522   0.02397  -0.0408   0.9740   0.0940
  -4.500  -0.3737   0.03377   0.02223  -0.0422   0.9693   0.0981
  -4.250  -0.3428   0.03241   0.02051  -0.0431   0.9639   0.1027
  -4.000  -0.3093   0.03133   0.01941  -0.0447   0.9595   0.1071
  -3.750  -0.2777   0.03042   0.01829  -0.0456   0.9546   0.1133
  -3.500  -0.2469   0.02955   0.01740  -0.0463   0.9492   0.1195
  -3.250  -0.2122   0.02885   0.01660  -0.0476   0.9450   0.1280
  -3.000  -0.1810   0.02820   0.01598  -0.0484   0.9403   0.1369
  -2.750  -0.1515   0.02770   0.01540  -0.0488   0.9345   0.1483
  -2.500  -0.1177   0.02716   0.01487  -0.0501   0.9300   0.1629
  -2.250  -0.0862   0.02664   0.01441  -0.0512   0.9254   0.1806
  -2.000  -0.0614   0.02617   0.01405  -0.0510   0.9189   0.2020
  -1.750  -0.0300   0.02547   0.01363  -0.0523   0.9141   0.2407
  -1.500  -0.0041   0.02353   0.01341  -0.0528   0.9107   0.4931
  -1.250   0.0017   0.02343   0.01423  -0.0456   0.9035   0.8046
  -1.000   0.0389   0.02374   0.01453  -0.0450   0.8997   0.9141
  -0.750   0.1588   0.02397   0.01443  -0.0618   0.9042   1.0000
  -0.500   0.1819   0.02411   0.01443  -0.0616   0.8971   1.0000
  -0.250   0.2020   0.02430   0.01451  -0.0609   0.8897   1.0000
   0.000   0.2190   0.02453   0.01464  -0.0596   0.8814   1.0000
   0.250   0.2483   0.02471   0.01471  -0.0603   0.8762   1.0000
   0.500   0.2564   0.02507   0.01500  -0.0574   0.8661   1.0000
   0.750   0.2833   0.02530   0.01516  -0.0577   0.8602   1.0000
   1.000   0.2989   0.02568   0.01548  -0.0560   0.8519   1.0000
   1.250   0.3218   0.02602   0.01577  -0.0556   0.8448   1.0000
   1.500   0.3537   0.02627   0.01599  -0.0565   0.8401   1.0000
   1.750   0.3648   0.02683   0.01652  -0.0543   0.8302   1.0000
   2.000   0.3942   0.02714   0.01683  -0.0547   0.8245   1.0000
   2.250   0.4140   0.02764   0.01733  -0.0538   0.8165   1.0000
   2.500   0.4383   0.02806   0.01778  -0.0535   0.8089   1.0000
   2.750   0.4724   0.02829   0.01806  -0.0545   0.8039   1.0000
   3.000   0.4859   0.02895   0.01876  -0.0527   0.7927   1.0000
   3.250   0.5223   0.02899   0.01887  -0.0536   0.7863   1.0000
   3.500   0.5479   0.02888   0.01885  -0.0524   0.7706   1.0000
   3.750   0.5863   0.02763   0.01765  -0.0513   0.7489   1.0000
   4.000   0.6119   0.02667   0.01675  -0.0486   0.7217   1.0000
   4.250   0.6443   0.02553   0.01568  -0.0467   0.6986   1.0000
   4.500   0.6653   0.02520   0.01543  -0.0444   0.6746   1.0000
   4.750   0.6893   0.02465   0.01498  -0.0422   0.6478   1.0000
   5.000   0.7095   0.02432   0.01473  -0.0398   0.6132   1.0000
   5.250   0.7279   0.02408   0.01453  -0.0370   0.5632   1.0000
   5.500   0.7514   0.02358   0.01360  -0.0340   0.4506   1.0000
   5.750   0.7589   0.02482   0.01361  -0.0299   0.3039   1.0000
   6.000   0.7640   0.02658   0.01477  -0.0271   0.2437   1.0000
   6.250   0.7739   0.02809   0.01595  -0.0250   0.2113   1.0000
   6.500   0.7861   0.02947   0.01709  -0.0232   0.1902   1.0000
   6.750   0.8011   0.03071   0.01821  -0.0216   0.1737   1.0000
   7.000   0.8191   0.03183   0.01927  -0.0204   0.1597   1.0000
   7.250   0.8395   0.03292   0.02034  -0.0194   0.1481   1.0000
   7.500   0.8625   0.03402   0.02138  -0.0187   0.1385   1.0000
   7.750   0.8884   0.03508   0.02245  -0.0183   0.1295   1.0000
   8.000   0.9182   0.03622   0.02365  -0.0183   0.1218   1.0000
   8.250   0.9460   0.03742   0.02483  -0.0183   0.1152   1.0000
   8.500   0.9754   0.03883   0.02633  -0.0184   0.1094   1.0000
   8.750   1.0026   0.04031   0.02792  -0.0184   0.1045   1.0000
   9.000   1.0297   0.04187   0.02936  -0.0186   0.1004   1.0000
   9.250   1.0511   0.04373   0.03161  -0.0179   0.0964   1.0000
   9.500   1.0727   0.04567   0.03376  -0.0173   0.0932   1.0000
   9.750   1.0934   0.04748   0.03564  -0.0168   0.0903   1.0000
  10.000   1.1109   0.04965   0.03799  -0.0161   0.0878   1.0000
  10.250   1.1208   0.05224   0.04102  -0.0145   0.0853   1.0000
  10.500   1.1301   0.05492   0.04403  -0.0130   0.0835   1.0000
  10.750   1.1379   0.05750   0.04687  -0.0115   0.0818   1.0000
  11.000   1.1464   0.05986   0.04939  -0.0102   0.0801   1.0000
  11.250   1.1582   0.06213   0.05170  -0.0093   0.0785   1.0000
  11.500   1.1450   0.06551   0.05547  -0.0064   0.0776   1.0000
  11.750   1.1268   0.06912   0.05945  -0.0036   0.0769   1.0000
  12.000   1.1060   0.07321   0.06386  -0.0017   0.0765   1.0000
  12.250   1.0818   0.07792   0.06887  -0.0008   0.0763   1.0000
  12.500   1.0538   0.08348   0.07469  -0.0010   0.0763   1.0000
  12.750   1.0215   0.09022   0.08166  -0.0028   0.0764   1.0000
  13.000   0.9850   0.09859   0.09022  -0.0065   0.0768   1.0000
  13.250   0.9443   0.10936   0.10114  -0.0127   0.0773   1.0000
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