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RUTAN WING AIRFOIL (amsoil2-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: RUTAN WING AIRFOIL (amsoil2-il)
Reynolds number: 200,000
Max Cl/Cd: 42.83 at α=6.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-amsoil2-il-200000-n5.txt
Download as CSV file: xf-amsoil2-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: RUTAN WING AIRFOIL                              
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -13.000  -0.8857   0.06818   0.06367  -0.0390   1.0000   0.0310
 -12.750  -0.9380   0.05674   0.05185  -0.0470   1.0000   0.0309
 -12.500  -0.9724   0.05006   0.04479  -0.0492   1.0000   0.0310
 -12.250  -0.9980   0.04523   0.03956  -0.0486   1.0000   0.0313
 -12.000  -1.0166   0.04154   0.03544  -0.0461   1.0000   0.0316
 -11.750  -1.0092   0.03988   0.03370  -0.0449   1.0000   0.0319
 -11.500  -0.9984   0.03847   0.03222  -0.0439   1.0000   0.0322
 -11.250  -0.9863   0.03711   0.03075  -0.0429   1.0000   0.0327
 -11.000  -0.9730   0.03575   0.02927  -0.0420   1.0000   0.0332
 -10.750  -0.9595   0.03423   0.02757  -0.0411   1.0000   0.0340
 -10.500  -0.9459   0.03249   0.02556  -0.0400   1.0000   0.0349
 -10.250  -0.9316   0.03062   0.02333  -0.0390   1.0000   0.0358
 -10.000  -0.9138   0.02923   0.02177  -0.0382   1.0000   0.0365
  -9.750  -0.8938   0.02830   0.02083  -0.0376   1.0000   0.0371
  -9.500  -0.8738   0.02741   0.01988  -0.0369   1.0000   0.0378
  -9.250  -0.8540   0.02652   0.01889  -0.0361   1.0000   0.0387
  -9.000  -0.8351   0.02559   0.01781  -0.0350   1.0000   0.0398
  -8.750  -0.8182   0.02464   0.01666  -0.0335   1.0000   0.0409
  -8.500  -0.7953   0.02376   0.01572  -0.0333   0.9969   0.0419
  -8.250  -0.7644   0.02299   0.01494  -0.0346   0.9909   0.0429
  -8.000  -0.7333   0.02222   0.01411  -0.0358   0.9850   0.0442
  -7.750  -0.7024   0.02145   0.01320  -0.0369   0.9790   0.0459
  -7.500  -0.6715   0.02066   0.01230  -0.0379   0.9732   0.0474
  -7.250  -0.6413   0.02003   0.01169  -0.0388   0.9673   0.0488
  -7.000  -0.6117   0.01943   0.01105  -0.0395   0.9608   0.0504
  -6.750  -0.5818   0.01885   0.01038  -0.0402   0.9551   0.0524
  -6.500  -0.5546   0.01828   0.00978  -0.0403   0.9478   0.0543
  -6.250  -0.5259   0.01780   0.00930  -0.0407   0.9423   0.0563
  -6.000  -0.4998   0.01734   0.00881  -0.0405   0.9349   0.0585
  -5.750  -0.4732   0.01689   0.00830  -0.0404   0.9287   0.0610
  -5.500  -0.4471   0.01648   0.00792  -0.0402   0.9227   0.0637
  -5.250  -0.4212   0.01612   0.00753  -0.0399   0.9161   0.0669
  -5.000  -0.3954   0.01571   0.00711  -0.0395   0.9106   0.0701
  -4.750  -0.3696   0.01538   0.00680  -0.0392   0.9044   0.0740
  -4.500  -0.3435   0.01507   0.00647  -0.0388   0.8982   0.0786
  -4.250  -0.3177   0.01475   0.00617  -0.0385   0.8934   0.0835
  -4.000  -0.2912   0.01448   0.00588  -0.0382   0.8880   0.0892
  -3.750  -0.2649   0.01418   0.00563  -0.0380   0.8820   0.0960
  -3.500  -0.2386   0.01391   0.00537  -0.0377   0.8768   0.1035
  -3.250  -0.2120   0.01368   0.00515  -0.0374   0.8720   0.1130
  -3.000  -0.1851   0.01340   0.00496  -0.0373   0.8660   0.1248
  -2.750  -0.1585   0.01314   0.00475  -0.0371   0.8606   0.1406
  -2.500  -0.1321   0.01285   0.00455  -0.0368   0.8562   0.1625
  -2.250  -0.1052   0.01252   0.00439  -0.0368   0.8504   0.1979
  -2.000  -0.0795   0.01197   0.00419  -0.0367   0.8451   0.2742
  -1.750  -0.0582   0.01080   0.00399  -0.0360   0.8405   0.5052
  -1.500  -0.0344   0.01042   0.00412  -0.0349   0.8359   0.6324
  -1.250  -0.0082   0.01035   0.00423  -0.0342   0.8303   0.6885
  -1.000   0.0184   0.01034   0.00431  -0.0336   0.8256   0.7237
  -0.750   0.0452   0.01036   0.00436  -0.0329   0.8214   0.7491
  -0.500   0.0720   0.01040   0.00444  -0.0323   0.8166   0.7700
  -0.250   0.0989   0.01044   0.00454  -0.0318   0.8111   0.7885
   0.000   0.1255   0.01048   0.00461  -0.0311   0.8065   0.8060
   0.250   0.1506   0.01052   0.00467  -0.0299   0.8013   0.8251
   0.500   0.1751   0.01052   0.00473  -0.0286   0.7900   0.8425
   0.750   0.2003   0.01047   0.00465  -0.0275   0.7776   0.8532
   1.000   0.2270   0.01038   0.00452  -0.0267   0.7643   0.8600
   1.250   0.2531   0.01032   0.00443  -0.0259   0.7485   0.8665
   1.500   0.2800   0.01027   0.00436  -0.0254   0.7321   0.8742
   1.750   0.3063   0.01024   0.00431  -0.0246   0.7151   0.8806
   2.000   0.3327   0.01022   0.00426  -0.0240   0.6952   0.8876
   2.250   0.3591   0.01022   0.00421  -0.0233   0.6670   0.8948
   2.500   0.3840   0.01027   0.00412  -0.0222   0.6243   0.9018
   2.750   0.4069   0.01055   0.00403  -0.0209   0.5391   0.9103
   3.000   0.4213   0.01177   0.00428  -0.0187   0.3341   0.9186
   3.250   0.4406   0.01278   0.00470  -0.0176   0.2154   0.9280
   3.500   0.4650   0.01329   0.00500  -0.0172   0.1719   0.9370
   3.750   0.4915   0.01370   0.00528  -0.0171   0.1461   0.9466
   4.000   0.5193   0.01409   0.00556  -0.0173   0.1281   0.9572
   4.250   0.5500   0.01446   0.00587  -0.0182   0.1144   0.9667
   4.500   0.5817   0.01483   0.00620  -0.0193   0.1039   0.9769
   4.750   0.6139   0.01522   0.00655  -0.0205   0.0957   0.9883
   5.000   0.6427   0.01566   0.00691  -0.0211   0.0891   1.0000
   5.250   0.6661   0.01600   0.00727  -0.0206   0.0841   1.0000
   5.500   0.6896   0.01645   0.00765  -0.0201   0.0796   1.0000
   5.750   0.7135   0.01689   0.00809  -0.0196   0.0756   1.0000
   6.000   0.7377   0.01734   0.00852  -0.0192   0.0719   1.0000
   6.250   0.7607   0.01791   0.00902  -0.0187   0.0689   1.0000
   6.500   0.7849   0.01838   0.00954  -0.0182   0.0659   1.0000
   6.750   0.8087   0.01888   0.01004  -0.0177   0.0631   1.0000
   7.000   0.8313   0.01952   0.01061  -0.0171   0.0609   1.0000
   7.250   0.8550   0.02007   0.01123  -0.0166   0.0586   1.0000
   7.500   0.8783   0.02064   0.01182  -0.0161   0.0564   1.0000
   7.750   0.9011   0.02122   0.01239  -0.0155   0.0545   1.0000
   8.000   0.9235   0.02193   0.01310  -0.0149   0.0528   1.0000
   8.250   0.9463   0.02259   0.01385  -0.0143   0.0510   1.0000
   8.500   0.9688   0.02324   0.01454  -0.0136   0.0493   1.0000
   8.750   0.9906   0.02389   0.01518  -0.0130   0.0479   1.0000
   9.000   1.0119   0.02468   0.01599  -0.0123   0.0466   1.0000
   9.250   1.0337   0.02550   0.01693  -0.0116   0.0452   1.0000
   9.500   1.0548   0.02629   0.01780  -0.0108   0.0438   1.0000
   9.750   1.0751   0.02703   0.01858  -0.0100   0.0426   1.0000
  10.000   1.0945   0.02781   0.01935  -0.0092   0.0416   1.0000
  10.250   1.1137   0.02880   0.02046  -0.0082   0.0405   1.0000
  10.500   1.1325   0.02988   0.02169  -0.0073   0.0394   1.0000
  10.750   1.1501   0.03092   0.02287  -0.0062   0.0385   1.0000
  11.000   1.1661   0.03188   0.02391  -0.0049   0.0376   1.0000
  11.250   1.1802   0.03279   0.02486  -0.0034   0.0369   1.0000
  11.500   1.1938   0.03377   0.02586  -0.0020   0.0363   1.0000
  11.750   1.2054   0.03519   0.02748  -0.0004   0.0355   1.0000
  12.000   1.2152   0.03674   0.02926   0.0012   0.0346   1.0000
  12.250   1.2239   0.03830   0.03101   0.0028   0.0339   1.0000
  12.500   1.2314   0.03989   0.03276   0.0044   0.0333   1.0000
  12.750   1.2380   0.04152   0.03452   0.0058   0.0328   1.0000
  13.000   1.2440   0.04317   0.03628   0.0072   0.0324   1.0000
  13.250   1.2495   0.04487   0.03807   0.0083   0.0320   1.0000
  13.500   1.2543   0.04668   0.03994   0.0094   0.0317   1.0000
  13.750   1.2546   0.04907   0.04247   0.0104   0.0314   1.0000
  14.000   1.2447   0.05262   0.04637   0.0113   0.0310   1.0000
  14.250   1.2320   0.05665   0.05070   0.0117   0.0306   1.0000
  14.500   1.2162   0.06125   0.05560   0.0114   0.0303   1.0000
  14.750   1.1962   0.06668   0.06131   0.0102   0.0300   1.0000
  15.000   1.1705   0.07343   0.06834   0.0077   0.0298   1.0000
  15.250   1.1333   0.08289   0.07812   0.0027   0.0298   1.0000
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