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ULTIMATE (ultimate-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: ULTIMATE (ultimate-il)
Reynolds number: 100,000
Max Cl/Cd: 36.13 at α=5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-ultimate-il-100000-n5.txt
Download as CSV file: xf-ultimate-il-100000-n5.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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -13.750  -0.7677   0.11815   0.11315   0.0041   1.0000   0.0278
 -13.500  -0.8600   0.09141   0.08607  -0.0144   1.0000   0.0254
 -13.250  -0.8956   0.08157   0.07596  -0.0210   1.0000   0.0251
 -13.000  -0.9202   0.07473   0.06887  -0.0248   1.0000   0.0250
 -12.750  -0.9407   0.06915   0.06303  -0.0270   1.0000   0.0249
 -12.500  -0.9562   0.06463   0.05829  -0.0280   1.0000   0.0250
 -12.250  -0.9694   0.06066   0.05408  -0.0281   1.0000   0.0251
 -12.000  -0.9786   0.05735   0.05057  -0.0275   1.0000   0.0254
 -11.750  -0.9853   0.05450   0.04752  -0.0263   1.0000   0.0257
 -11.500  -0.9901   0.05195   0.04474  -0.0246   1.0000   0.0262
 -11.250  -0.9924   0.04968   0.04228  -0.0226   1.0000   0.0269
 -11.000  -0.9935   0.04752   0.03989  -0.0201   1.0000   0.0277
 -10.750  -0.9931   0.04531   0.03741  -0.0174   1.0000   0.0284
 -10.500  -0.9885   0.04307   0.03486  -0.0151   1.0000   0.0293
 -10.250  -0.9788   0.04081   0.03227  -0.0132   1.0000   0.0300
 -10.000  -0.9655   0.03871   0.02985  -0.0117   1.0000   0.0307
  -9.750  -0.9489   0.03650   0.02749  -0.0106   1.0000   0.0316
  -9.500  -0.9326   0.03474   0.02569  -0.0096   1.0000   0.0328
  -9.250  -0.9170   0.03336   0.02422  -0.0083   1.0000   0.0346
  -9.000  -0.9002   0.03203   0.02274  -0.0070   1.0000   0.0368
  -8.750  -0.8821   0.03069   0.02122  -0.0058   1.0000   0.0386
  -8.500  -0.8658   0.02921   0.01968  -0.0043   1.0000   0.0402
  -8.250  -0.8520   0.02789   0.01836  -0.0025   1.0000   0.0424
  -8.000  -0.8366   0.02684   0.01723  -0.0008   1.0000   0.0457
  -7.750  -0.8206   0.02586   0.01611   0.0009   1.0000   0.0490
  -7.500  -0.8080   0.02467   0.01491   0.0032   1.0000   0.0522
  -7.250  -0.7931   0.02372   0.01389   0.0051   1.0000   0.0570
  -7.000  -0.7786   0.02276   0.01289   0.0072   1.0000   0.0639
  -6.750  -0.7635   0.02187   0.01195   0.0092   1.0000   0.0732
  -6.500  -0.7506   0.02083   0.01104   0.0116   1.0000   0.0900
  -6.250  -0.7393   0.01974   0.01023   0.0141   1.0000   0.1298
  -6.000  -0.7288   0.01871   0.00957   0.0169   1.0000   0.1902
  -5.750  -0.7182   0.01789   0.00909   0.0197   1.0000   0.2528
  -5.500  -0.7057   0.01733   0.00876   0.0223   1.0000   0.3073
  -5.250  -0.6917   0.01693   0.00847   0.0248   1.0000   0.3519
  -5.000  -0.6771   0.01660   0.00823   0.0272   1.0000   0.3920
  -4.750  -0.6637   0.01625   0.00805   0.0298   1.0000   0.4355
  -4.500  -0.6493   0.01595   0.00790   0.0323   1.0000   0.4747
  -4.250  -0.6315   0.01571   0.00773   0.0341   0.9996   0.5052
  -4.000  -0.5950   0.01551   0.00754   0.0321   0.9937   0.5335
  -3.750  -0.5585   0.01532   0.00736   0.0302   0.9869   0.5617
  -3.500  -0.5219   0.01516   0.00721   0.0283   0.9799   0.5903
  -3.250  -0.4835   0.01503   0.00711   0.0260   0.9735   0.6195
  -3.000  -0.4488   0.01491   0.00702   0.0247   0.9651   0.6475
  -2.750  -0.4128   0.01481   0.00692   0.0231   0.9574   0.6746
  -2.500  -0.3793   0.01471   0.00682   0.0220   0.9482   0.6999
  -2.250  -0.3462   0.01462   0.00675   0.0211   0.9385   0.7221
  -2.000  -0.3115   0.01453   0.00663   0.0199   0.9301   0.7437
  -1.750  -0.2786   0.01445   0.00656   0.0191   0.9198   0.7631
  -1.500  -0.2448   0.01438   0.00650   0.0182   0.9098   0.7813
  -1.250  -0.2092   0.01431   0.00641   0.0169   0.9010   0.7986
  -1.000  -0.1764   0.01426   0.00637   0.0162   0.8897   0.8153
  -0.750  -0.1434   0.01423   0.00633   0.0155   0.8784   0.8312
  -0.500  -0.1099   0.01420   0.00628   0.0147   0.8671   0.8465
  -0.250  -0.0762   0.01417   0.00624   0.0138   0.8554   0.8609
   0.000  -0.0424   0.01416   0.00623   0.0129   0.8422   0.8747
   0.250  -0.0082   0.01416   0.00624   0.0118   0.8279   0.8876
   0.500   0.0266   0.01418   0.00626   0.0105   0.8131   0.9001
   0.750   0.0645   0.01421   0.00631   0.0087   0.7976   0.9103
   1.000   0.1036   0.01425   0.00636   0.0066   0.7818   0.9192
   1.250   0.1407   0.01429   0.00640   0.0048   0.7656   0.9289
   1.500   0.1812   0.01437   0.00649   0.0024   0.7485   0.9358
   1.750   0.2180   0.01445   0.00658   0.0007   0.7310   0.9446
   2.000   0.2558   0.01457   0.00671  -0.0012   0.7134   0.9533
   2.250   0.2941   0.01470   0.00685  -0.0032   0.6958   0.9632
   2.500   0.3312   0.01486   0.00700  -0.0051   0.6778   0.9750
   3.000   0.4036   0.01517   0.00730  -0.0088   0.6355   0.9952
   3.250   0.4376   0.01525   0.00737  -0.0103   0.6148   1.0000
   3.500   0.4599   0.01528   0.00741  -0.0095   0.5973   1.0000
   3.750   0.4825   0.01534   0.00749  -0.0087   0.5800   1.0000
   4.000   0.5050   0.01542   0.00761  -0.0078   0.5618   1.0000
   4.250   0.5267   0.01553   0.00768  -0.0067   0.5358   1.0000
   4.500   0.5476   0.01567   0.00774  -0.0055   0.4946   1.0000
   4.750   0.5679   0.01593   0.00779  -0.0042   0.4417   1.0000
   5.000   0.5885   0.01629   0.00796  -0.0030   0.3826   1.0000
   5.250   0.6081   0.01686   0.00821  -0.0019   0.3040   1.0000
   5.500   0.6249   0.01798   0.00876  -0.0007   0.2018   1.0000
   6.000   0.6575   0.02058   0.01050   0.0020   0.0751   1.0000
   6.250   0.6753   0.02156   0.01143   0.0034   0.0634   1.0000
   6.500   0.6936   0.02242   0.01237   0.0047   0.0562   1.0000
   6.750   0.7097   0.02351   0.01347   0.0064   0.0521   1.0000
   7.000   0.7274   0.02440   0.01449   0.0080   0.0485   1.0000
   7.250   0.7441   0.02537   0.01549   0.0095   0.0447   1.0000
   7.500   0.7583   0.02673   0.01679   0.0113   0.0421   1.0000
   7.750   0.7763   0.02782   0.01803   0.0128   0.0404   1.0000
   8.000   0.7945   0.02901   0.01933   0.0143   0.0384   1.0000
   8.250   0.8123   0.03019   0.02058   0.0156   0.0362   1.0000
   8.500   0.8295   0.03148   0.02187   0.0168   0.0342   1.0000
   8.750   0.8477   0.03333   0.02373   0.0180   0.0329   1.0000
   9.000   0.8664   0.03498   0.02562   0.0193   0.0320   1.0000
   9.250   0.8837   0.03687   0.02780   0.0206   0.0311   1.0000
   9.500   0.8987   0.03883   0.03003   0.0222   0.0301   1.0000
   9.750   0.9115   0.04072   0.03215   0.0238   0.0289   1.0000
  10.000   0.9227   0.04247   0.03406   0.0254   0.0277   1.0000
  10.250   0.9323   0.04433   0.03606   0.0271   0.0268   1.0000
  10.500   0.9397   0.04664   0.03852   0.0288   0.0262   1.0000
  10.750   0.9433   0.04957   0.04162   0.0307   0.0258   1.0000
  11.000   0.9388   0.05231   0.04470   0.0336   0.0256   1.0000
  11.250   0.9285   0.05505   0.04775   0.0368   0.0255   1.0000
  11.500   0.9137   0.05793   0.05089   0.0398   0.0254   1.0000
  11.750   0.8980   0.06126   0.05446   0.0416   0.0253   1.0000
  12.000   0.8809   0.06509   0.05852   0.0424   0.0253   1.0000
  12.250   0.8626   0.06950   0.06314   0.0419   0.0253   1.0000
  12.500   0.8425   0.07466   0.06850   0.0402   0.0254   1.0000
  12.750   0.8219   0.08055   0.07453   0.0375   0.0254   1.0000
  13.000   0.8008   0.08723   0.08136   0.0337   0.0256   1.0000
  13.250   0.7794   0.09471   0.08896   0.0292   0.0257   1.0000
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