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ULTIMATE (ultimate-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: ULTIMATE (ultimate-il)
Reynolds number: 200,000
Max Cl/Cd: 47.82 at α=5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-ultimate-il-200000.txt
Download as CSV file: xf-ultimate-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: ULTIMATE                                        
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -12.750  -0.8463   0.08776   0.08403  -0.0179   1.0000   0.0386
 -12.500  -0.8689   0.08041   0.07659  -0.0217   1.0000   0.0378
 -12.250  -0.8937   0.07387   0.06989  -0.0249   1.0000   0.0372
 -12.000  -0.9189   0.06811   0.06395  -0.0268   1.0000   0.0366
 -11.750  -0.9433   0.06308   0.05871  -0.0271   1.0000   0.0359
 -11.500  -0.9686   0.05843   0.05380  -0.0257   1.0000   0.0351
 -11.250  -0.9953   0.05414   0.04916  -0.0222   1.0000   0.0342
 -11.000  -1.0177   0.05047   0.04511  -0.0174   1.0000   0.0335
 -10.750  -1.0211   0.04769   0.04207  -0.0145   1.0000   0.0338
 -10.500  -1.0212   0.04483   0.03893  -0.0118   1.0000   0.0341
 -10.250  -1.0200   0.04157   0.03528  -0.0088   1.0000   0.0339
 -10.000  -1.0137   0.03844   0.03174  -0.0063   1.0000   0.0337
  -9.750  -1.0008   0.03588   0.02888  -0.0045   1.0000   0.0340
  -9.500  -0.9845   0.03365   0.02642  -0.0031   1.0000   0.0345
  -9.250  -0.9659   0.03163   0.02416  -0.0019   1.0000   0.0353
  -9.000  -0.9461   0.02992   0.02225  -0.0008   1.0000   0.0365
  -8.750  -0.9259   0.02862   0.02076   0.0003   1.0000   0.0382
  -8.500  -0.9056   0.02768   0.01959   0.0016   1.0000   0.0395
  -8.250  -0.8815   0.02487   0.01677   0.0017   1.0000   0.0414
  -8.000  -0.8611   0.02353   0.01544   0.0027   1.0000   0.0434
  -7.750  -0.8413   0.02247   0.01432   0.0039   1.0000   0.0460
  -7.500  -0.8212   0.02167   0.01343   0.0052   1.0000   0.0490
  -7.250  -0.8072   0.02022   0.01200   0.0074   1.0000   0.0525
  -7.000  -0.7917   0.01931   0.01109   0.0094   1.0000   0.0565
  -6.750  -0.7754   0.01862   0.01033   0.0115   1.0000   0.0612
  -6.500  -0.7660   0.01763   0.00939   0.0147   1.0000   0.0686
  -6.250  -0.7558   0.01684   0.00863   0.0180   1.0000   0.0790
  -6.000  -0.7489   0.01584   0.00784   0.0217   1.0000   0.1086
  -5.750  -0.7494   0.01437   0.00711   0.0264   1.0000   0.2196
  -5.500  -0.7419   0.01364   0.00679   0.0300   1.0000   0.3043
  -5.250  -0.7288   0.01329   0.00661   0.0326   1.0000   0.3550
  -5.000  -0.7135   0.01306   0.00644   0.0348   1.0000   0.3934
  -4.750  -0.6971   0.01286   0.00629   0.0368   1.0000   0.4244
  -4.500  -0.6797   0.01267   0.00617   0.0387   1.0000   0.4539
  -4.250  -0.6618   0.01249   0.00608   0.0404   1.0000   0.4813
  -4.000  -0.6306   0.01227   0.00598   0.0393   0.9966   0.5194
  -3.750  -0.5931   0.01206   0.00597   0.0372   0.9910   0.5666
  -3.500  -0.5534   0.01192   0.00593   0.0345   0.9856   0.6026
  -3.250  -0.5158   0.01179   0.00586   0.0324   0.9791   0.6330
  -3.000  -0.4749   0.01169   0.00582   0.0297   0.9740   0.6638
  -2.750  -0.4390   0.01158   0.00577   0.0280   0.9665   0.6922
  -2.500  -0.3973   0.01148   0.00572   0.0252   0.9615   0.7204
  -2.250  -0.3630   0.01138   0.00567   0.0241   0.9532   0.7465
  -2.000  -0.3242   0.01128   0.00561   0.0221   0.9471   0.7701
  -1.750  -0.2938   0.01118   0.00555   0.0219   0.9371   0.7921
  -1.500  -0.2587   0.01106   0.00548   0.0209   0.9299   0.8108
  -1.250  -0.2291   0.01096   0.00540   0.0211   0.9195   0.8285
  -1.000  -0.2007   0.01086   0.00532   0.0215   0.9088   0.8457
  -0.750  -0.1721   0.01074   0.00521   0.0220   0.8989   0.8622
  -0.500  -0.1437   0.01063   0.00510   0.0225   0.8879   0.8782
  -0.250  -0.1131   0.01056   0.00503   0.0224   0.8752   0.8931
   0.000  -0.0780   0.01053   0.00500   0.0213   0.8626   0.9064
   0.250  -0.0393   0.01055   0.00501   0.0194   0.8495   0.9178
   0.500  -0.0007   0.01060   0.00504   0.0174   0.8355   0.9285
   0.750   0.0452   0.01073   0.00516   0.0139   0.8207   0.9338
   1.000   0.0838   0.01083   0.00523   0.0119   0.8045   0.9423
   1.250   0.1267   0.01099   0.00537   0.0091   0.7875   0.9467
   1.500   0.1645   0.01112   0.00548   0.0072   0.7699   0.9541
   1.750   0.2041   0.01127   0.00558   0.0050   0.7520   0.9601
   2.000   0.2410   0.01142   0.00568   0.0032   0.7329   0.9684
   2.250   0.2800   0.01157   0.00578   0.0009   0.7103   0.9756
   2.500   0.3184   0.01174   0.00585  -0.0013   0.6891   0.9830
   2.750   0.3583   0.01190   0.00600  -0.0040   0.6679   0.9902
   3.000   0.4008   0.01204   0.00612  -0.0073   0.6484   0.9965
   3.250   0.4375   0.01209   0.00615  -0.0095   0.6301   1.0000
   3.500   0.4599   0.01205   0.00607  -0.0088   0.6088   1.0000
   3.750   0.4820   0.01201   0.00596  -0.0080   0.5829   1.0000
   4.000   0.5044   0.01199   0.00589  -0.0073   0.5552   1.0000
   4.250   0.5269   0.01202   0.00585  -0.0065   0.5252   1.0000
   4.500   0.5497   0.01209   0.00587  -0.0057   0.4936   1.0000
   4.750   0.5726   0.01223   0.00592  -0.0050   0.4591   1.0000
   5.000   0.5953   0.01245   0.00602  -0.0043   0.4123   1.0000
   5.250   0.6159   0.01303   0.00621  -0.0034   0.3106   1.0000
   5.500   0.6284   0.01537   0.00721  -0.0022   0.0954   1.0000
   5.750   0.6474   0.01641   0.00810  -0.0010   0.0716   1.0000
   6.000   0.6663   0.01734   0.00900   0.0004   0.0625   1.0000
   6.250   0.6859   0.01812   0.00981   0.0016   0.0568   1.0000
   6.500   0.7018   0.01951   0.01115   0.0034   0.0526   1.0000
   6.750   0.7224   0.02021   0.01193   0.0046   0.0495   1.0000
   7.000   0.7421   0.02109   0.01283   0.0059   0.0462   1.0000
   7.250   0.7612   0.02231   0.01400   0.0073   0.0439   1.0000
   7.500   0.7811   0.02451   0.01618   0.0085   0.0420   1.0000
   7.750   0.8028   0.02543   0.01727   0.0096   0.0408   1.0000
   8.000   0.8239   0.02647   0.01847   0.0108   0.0387   1.0000
   8.250   0.8448   0.02787   0.01999   0.0119   0.0373   1.0000
   8.500   0.8654   0.02954   0.02180   0.0130   0.0364   1.0000
   8.750   0.8851   0.03144   0.02388   0.0142   0.0357   1.0000
   9.000   0.9032   0.03365   0.02633   0.0156   0.0354   1.0000
   9.250   0.9168   0.03649   0.02958   0.0177   0.0358   1.0000
   9.500   0.9260   0.03962   0.03313   0.0202   0.0362   1.0000
   9.750   0.9330   0.04263   0.03649   0.0226   0.0362   1.0000
  10.000   0.9315   0.04654   0.04084   0.0258   0.0370   1.0000
  10.250   0.9228   0.05155   0.04626   0.0291   0.0394   1.0000
  10.500   0.8456   0.04346   0.03866   0.0373   0.0397   1.0000
  10.750   0.8273   0.04764   0.04297   0.0410   0.0407   1.0000
  11.000   0.7710   0.07759   0.07381   0.0382   0.0745   1.0000
  11.250   0.7406   0.08461   0.08090   0.0344   0.0750   1.0000
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