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RUTAN CANARD AIRFOIL (amsoil1-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: RUTAN CANARD AIRFOIL (amsoil1-il)
Reynolds number: 500,000
Max Cl/Cd: 86.18 at α=3.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-amsoil1-il-500000.txt
Download as CSV file: xf-amsoil1-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.000  -0.5208   0.13101   0.12851  -0.0053   1.0000   0.0341
 -11.750  -0.5182   0.12685   0.12435  -0.0074   1.0000   0.0353
 -10.250  -0.8329   0.03333   0.02922  -0.0557   0.9999   0.0310
 -10.000  -0.8176   0.02895   0.02417  -0.0572   0.9893   0.0317
  -9.750  -0.7952   0.02604   0.02089  -0.0584   0.9815   0.0324
  -9.500  -0.7672   0.02514   0.01996  -0.0593   0.9735   0.0330
  -9.250  -0.7414   0.02454   0.01932  -0.0594   0.9644   0.0337
  -9.000  -0.7185   0.02377   0.01844  -0.0589   0.9556   0.0344
  -8.750  -0.6984   0.02263   0.01709  -0.0579   0.9462   0.0352
  -8.500  -0.6776   0.02150   0.01572  -0.0569   0.9378   0.0359
  -8.250  -0.6557   0.02068   0.01465  -0.0559   0.9300   0.0365
  -8.000  -0.6338   0.01929   0.01314  -0.0552   0.9232   0.0373
  -7.750  -0.6094   0.01875   0.01259  -0.0547   0.9164   0.0381
  -7.500  -0.5854   0.01827   0.01202  -0.0540   0.9105   0.0390
  -7.250  -0.5596   0.01764   0.01130  -0.0538   0.9040   0.0399
  -7.000  -0.5343   0.01702   0.01056  -0.0533   0.8981   0.0408
  -6.750  -0.5089   0.01653   0.00992  -0.0528   0.8929   0.0416
  -6.500  -0.4832   0.01560   0.00896  -0.0526   0.8872   0.0427
  -6.250  -0.4569   0.01518   0.00854  -0.0523   0.8816   0.0438
  -6.000  -0.4308   0.01481   0.00810  -0.0519   0.8766   0.0450
  -5.750  -0.4036   0.01438   0.00762  -0.0518   0.8716   0.0462
  -5.500  -0.3763   0.01401   0.00718  -0.0517   0.8662   0.0473
  -5.250  -0.3505   0.01336   0.00652  -0.0513   0.8613   0.0488
  -5.000  -0.3235   0.01307   0.00623  -0.0511   0.8567   0.0504
  -4.750  -0.2956   0.01277   0.00592  -0.0511   0.8515   0.0522
  -4.500  -0.2679   0.01250   0.00559  -0.0510   0.8465   0.0538
  -4.250  -0.2415   0.01201   0.00510  -0.0508   0.8420   0.0560
  -4.000  -0.2136   0.01179   0.00489  -0.0507   0.8374   0.0585
  -3.750  -0.1852   0.01160   0.00467  -0.0508   0.8324   0.0612
  -3.500  -0.1579   0.01120   0.00431  -0.0507   0.8276   0.0649
  -3.250  -0.1299   0.01104   0.00411  -0.0506   0.8233   0.0688
  -3.000  -0.1019   0.01075   0.00387  -0.0507   0.8190   0.0740
  -2.750  -0.0732   0.01056   0.00369  -0.0508   0.8142   0.0800
  -2.500  -0.0450   0.01035   0.00351  -0.0508   0.8096   0.0872
  -2.250  -0.0169   0.01015   0.00333  -0.0508   0.8054   0.0954
  -2.000   0.0118   0.01000   0.00321  -0.0510   0.8009   0.1047
  -1.750   0.0407   0.00984   0.00310  -0.0511   0.7962   0.1159
  -1.500   0.0692   0.00964   0.00297  -0.0512   0.7916   0.1318
  -1.250   0.0975   0.00944   0.00285  -0.0513   0.7873   0.1573
  -1.000   0.1260   0.00915   0.00277  -0.0516   0.7826   0.2088
  -0.750   0.1507   0.00766   0.00259  -0.0519   0.7775   0.5757
  -0.500   0.1762   0.00724   0.00269  -0.0512   0.7729   0.7309
  -0.250   0.2031   0.00720   0.00276  -0.0507   0.7687   0.7810
   0.000   0.2307   0.00718   0.00283  -0.0503   0.7642   0.8100
   0.250   0.2583   0.00718   0.00288  -0.0499   0.7593   0.8323
   0.500   0.2856   0.00719   0.00291  -0.0495   0.7546   0.8505
   0.750   0.3122   0.00719   0.00292  -0.0488   0.7472   0.8668
   1.000   0.3385   0.00712   0.00284  -0.0480   0.7358   0.8813
   1.250   0.3645   0.00710   0.00282  -0.0472   0.7257   0.8961
   1.500   0.3898   0.00708   0.00278  -0.0462   0.7164   0.9110
   1.750   0.4144   0.00704   0.00279  -0.0451   0.7063   0.9252
   2.000   0.4374   0.00702   0.00274  -0.0435   0.6957   0.9408
   2.250   0.4603   0.00697   0.00270  -0.0419   0.6831   0.9585
   2.500   0.4890   0.00695   0.00268  -0.0418   0.6703   0.9714
   2.750   0.5229   0.00697   0.00267  -0.0430   0.6563   0.9782
   3.000   0.5575   0.00702   0.00268  -0.0443   0.6382   0.9850
   3.250   0.5932   0.00713   0.00268  -0.0460   0.6124   0.9907
   3.500   0.6291   0.00730   0.00273  -0.0478   0.5760   0.9958
   3.750   0.6610   0.00768   0.00283  -0.0489   0.5110   1.0000
   4.000   0.6757   0.00855   0.00313  -0.0470   0.3906   1.0000
   4.250   0.6919   0.00986   0.00371  -0.0457   0.2468   1.0000
   4.500   0.7140   0.01064   0.00413  -0.0452   0.1803   1.0000
   4.750   0.7384   0.01117   0.00446  -0.0449   0.1462   1.0000
   5.000   0.7635   0.01162   0.00477  -0.0447   0.1250   1.0000
   5.250   0.7889   0.01202   0.00509  -0.0444   0.1109   1.0000
   5.500   0.8139   0.01245   0.00543  -0.0441   0.1000   1.0000
   5.750   0.8393   0.01281   0.00574  -0.0438   0.0917   1.0000
   6.000   0.8645   0.01320   0.00610  -0.0435   0.0846   1.0000
   6.250   0.8883   0.01370   0.00653  -0.0430   0.0781   1.0000
   6.500   0.9136   0.01403   0.00687  -0.0427   0.0735   1.0000
   6.750   0.9363   0.01460   0.00738  -0.0420   0.0688   1.0000
   7.000   0.9611   0.01494   0.00774  -0.0416   0.0653   1.0000
   7.250   0.9841   0.01544   0.00820  -0.0410   0.0621   1.0000
   7.500   1.0062   0.01599   0.00877  -0.0402   0.0596   1.0000
   7.750   1.0294   0.01643   0.00922  -0.0396   0.0573   1.0000
   8.000   1.0517   0.01692   0.00969  -0.0389   0.0552   1.0000
   8.250   1.0706   0.01769   0.01045  -0.0377   0.0532   1.0000
   8.500   1.0931   0.01812   0.01094  -0.0370   0.0517   1.0000
   8.750   1.1142   0.01865   0.01148  -0.0361   0.0502   1.0000
   9.000   1.1346   0.01920   0.01204  -0.0351   0.0489   1.0000
   9.250   1.1520   0.01997   0.01280  -0.0337   0.0475   1.0000
   9.500   1.1686   0.02073   0.01359  -0.0322   0.0463   1.0000
   9.750   1.1867   0.02128   0.01421  -0.0308   0.0453   1.0000
  10.000   1.2040   0.02193   0.01491  -0.0295   0.0442   1.0000
  10.250   1.2210   0.02261   0.01562  -0.0281   0.0433   1.0000
  10.500   1.2374   0.02336   0.01636  -0.0268   0.0423   1.0000
  10.750   1.2514   0.02451   0.01749  -0.0253   0.0412   1.0000
  11.000   1.2678   0.02533   0.01840  -0.0241   0.0405   1.0000
  11.250   1.2842   0.02612   0.01928  -0.0229   0.0397   1.0000
  11.500   1.2999   0.02699   0.02022  -0.0217   0.0389   1.0000
  11.750   1.3152   0.02788   0.02117  -0.0205   0.0381   1.0000
  12.000   1.3299   0.02879   0.02211  -0.0194   0.0374   1.0000
  12.250   1.3438   0.02982   0.02315  -0.0182   0.0366   1.0000
  12.500   1.3568   0.03136   0.02470  -0.0168   0.0357   1.0000
  12.750   1.3694   0.03239   0.02587  -0.0156   0.0353   1.0000
  13.000   1.3814   0.03357   0.02716  -0.0144   0.0347   1.0000
  13.250   1.3927   0.03483   0.02853  -0.0132   0.0341   1.0000
  13.500   1.4033   0.03615   0.02994  -0.0121   0.0335   1.0000
  13.750   1.4133   0.03751   0.03138  -0.0110   0.0329   1.0000
  14.000   1.4229   0.03891   0.03284  -0.0100   0.0324   1.0000
  14.250   1.4321   0.04038   0.03434  -0.0090   0.0320   1.0000
  14.500   1.4403   0.04219   0.03617  -0.0079   0.0314   1.0000
  14.750   1.4442   0.04435   0.03847  -0.0067   0.0309   1.0000
  15.000   1.4470   0.04638   0.04067  -0.0058   0.0305   1.0000
  15.250   1.4490   0.04859   0.04305  -0.0050   0.0301   1.0000
  15.500   1.4503   0.05097   0.04557  -0.0043   0.0297   1.0000
  15.750   1.4505   0.05350   0.04823  -0.0038   0.0293   1.0000
  16.000   1.4494   0.05623   0.05110  -0.0034   0.0290   1.0000
  16.250   1.4477   0.05908   0.05408  -0.0033   0.0286   1.0000
  16.500   1.4459   0.06205   0.05715  -0.0033   0.0283   1.0000
  16.750   1.4437   0.06516   0.06036  -0.0035   0.0281   1.0000
  17.000   1.4414   0.06841   0.06370  -0.0039   0.0278   1.0000
  17.250   1.4385   0.07183   0.06720  -0.0045   0.0276   1.0000
  17.500   1.4334   0.07565   0.07111  -0.0052   0.0273   1.0000
  17.750   1.4217   0.08048   0.07607  -0.0062   0.0271   1.0000
  18.000   1.4030   0.08671   0.08249  -0.0084   0.0269   1.0000
  18.250   1.3841   0.09342   0.08942  -0.0116   0.0268   1.0000
  18.500   1.3619   0.10107   0.09728  -0.0155   0.0267   1.0000
  18.750   1.3353   0.11002   0.10646  -0.0207   0.0267   1.0000
  19.000   1.3021   0.12097   0.11766  -0.0275   0.0267   1.0000
  19.250   1.2535   0.13619   0.13316  -0.0376   0.0267   1.0000
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