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SELIG 3002-099-83 (s3002-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: SELIG 3002-099-83 (s3002-il)
Reynolds number: 100,000
Max Cl/Cd: 55.76 at α=5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s3002-il-100000-n5.txt
Download as CSV file: xf-s3002-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: SELIG 3002-099-83                               
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.3713   0.10969   0.10451  -0.0315   1.0000   0.0530
  -9.500  -0.3790   0.10664   0.10156  -0.0358   1.0000   0.0538
  -9.250  -0.3802   0.10324   0.09822  -0.0381   1.0000   0.0539
  -9.000  -0.3826   0.09971   0.09477  -0.0404   1.0000   0.0540
  -8.750  -0.3736   0.09527   0.09037  -0.0386   1.0000   0.0548
  -8.250  -0.3813   0.08383   0.07903  -0.0422   1.0000   0.0353
  -8.000  -0.3698   0.08241   0.07762  -0.0387   1.0000   0.0334
  -7.750  -0.3760   0.07951   0.07481  -0.0384   1.0000   0.0323
  -7.250  -0.4165   0.06818   0.06364  -0.0451   1.0000   0.0279
  -7.000  -0.4240   0.06557   0.06104  -0.0441   1.0000   0.0276
  -6.750  -0.4292   0.06254   0.05801  -0.0438   0.9996   0.0273
  -6.500  -0.4067   0.05624   0.05149  -0.0511   0.9920   0.0266
  -6.250  -0.3816   0.04956   0.04447  -0.0580   0.9847   0.0260
  -6.000  -0.3568   0.04340   0.03786  -0.0631   0.9770   0.0256
  -5.750  -0.3256   0.03775   0.03159  -0.0678   0.9717   0.0255
  -5.500  -0.2976   0.03371   0.02693  -0.0702   0.9644   0.0267
  -5.250  -0.2631   0.02994   0.02233  -0.0729   0.9596   0.0284
  -5.000  -0.2319   0.02764   0.01973  -0.0745   0.9543   0.0293
  -4.750  -0.1998   0.02570   0.01749  -0.0758   0.9486   0.0304
  -4.500  -0.1637   0.02392   0.01539  -0.0776   0.9447   0.0323
  -4.250  -0.1311   0.02253   0.01366  -0.0784   0.9391   0.0356
  -4.000  -0.0993   0.02132   0.01242  -0.0794   0.9333   0.0382
  -3.750  -0.0638   0.02025   0.01121  -0.0808   0.9291   0.0421
  -3.500  -0.0346   0.01934   0.01029  -0.0812   0.9220   0.0466
  -3.250  -0.0017   0.01854   0.00943  -0.0821   0.9161   0.0518
  -3.000   0.0319   0.01779   0.00867  -0.0833   0.9108   0.0602
  -2.750   0.0610   0.01717   0.00802  -0.0835   0.9028   0.0708
  -2.500   0.0955   0.01640   0.00740  -0.0847   0.8975   0.1055
  -2.250   0.1225   0.01561   0.00705  -0.0849   0.8886   0.2049
  -2.000   0.1507   0.01421   0.00688  -0.0855   0.8824   0.4984
  -1.750   0.1670   0.01402   0.00735  -0.0817   0.8725   0.7061
  -1.500   0.1941   0.01402   0.00730  -0.0804   0.8656   0.7667
  -1.250   0.2154   0.01403   0.00724  -0.0782   0.8549   0.7997
  -1.000   0.2396   0.01396   0.00709  -0.0766   0.8461   0.8271
  -0.750   0.2620   0.01385   0.00692  -0.0745   0.8365   0.8551
  -0.500   0.2807   0.01371   0.00675  -0.0716   0.8258   0.8857
  -0.250   0.3050   0.01348   0.00647  -0.0698   0.8167   0.9160
   0.000   0.3363   0.01331   0.00624  -0.0699   0.8060   0.9384
   0.250   0.3720   0.01321   0.00604  -0.0712   0.7948   0.9559
   0.500   0.4101   0.01310   0.00584  -0.0731   0.7838   0.9737
   0.750   0.4452   0.01302   0.00565  -0.0744   0.7723   1.0000
   1.000   0.4712   0.01306   0.00560  -0.0742   0.7586   1.0000
   1.250   0.4983   0.01310   0.00556  -0.0741   0.7447   1.0000
   1.500   0.5261   0.01314   0.00553  -0.0741   0.7302   1.0000
   1.750   0.5541   0.01320   0.00550  -0.0740   0.7150   1.0000
   2.000   0.5822   0.01326   0.00549  -0.0740   0.6989   1.0000
   2.250   0.6102   0.01333   0.00547  -0.0739   0.6818   1.0000
   2.500   0.6379   0.01343   0.00550  -0.0737   0.6634   1.0000
   2.750   0.6650   0.01355   0.00555  -0.0735   0.6429   1.0000
   3.000   0.6923   0.01369   0.00560  -0.0732   0.6217   1.0000
   3.250   0.7191   0.01386   0.00568  -0.0729   0.5988   1.0000
   3.500   0.7456   0.01406   0.00579  -0.0725   0.5749   1.0000
   3.750   0.7717   0.01431   0.00594  -0.0721   0.5498   1.0000
   4.000   0.7975   0.01459   0.00610  -0.0717   0.5247   1.0000
   4.250   0.8229   0.01492   0.00634  -0.0712   0.4989   1.0000
   4.500   0.8480   0.01527   0.00659  -0.0707   0.4731   1.0000
   4.750   0.8727   0.01567   0.00687  -0.0701   0.4481   1.0000
   5.000   0.8971   0.01609   0.00722  -0.0696   0.4234   1.0000
   5.250   0.9212   0.01655   0.00759  -0.0691   0.3997   1.0000
   5.500   0.9450   0.01703   0.00798  -0.0685   0.3768   1.0000
   5.750   0.9687   0.01752   0.00842  -0.0679   0.3550   1.0000
   6.000   0.9920   0.01804   0.00890  -0.0673   0.3336   1.0000
   6.250   1.0148   0.01860   0.00939  -0.0666   0.3137   1.0000
   6.500   1.0377   0.01914   0.00992  -0.0660   0.2937   1.0000
   6.750   1.0601   0.01973   0.01050  -0.0653   0.2745   1.0000
   7.000   1.0819   0.02035   0.01109  -0.0646   0.2560   1.0000
   7.250   1.1031   0.02101   0.01171  -0.0638   0.2385   1.0000
   7.500   1.1243   0.02167   0.01238  -0.0630   0.2211   1.0000
   7.750   1.1449   0.02238   0.01311  -0.0622   0.2047   1.0000
   8.000   1.1649   0.02312   0.01386  -0.0613   0.1891   1.0000
   8.250   1.1842   0.02391   0.01466  -0.0603   0.1748   1.0000
   8.500   1.2027   0.02475   0.01551  -0.0592   0.1613   1.0000
   8.750   1.2203   0.02564   0.01642  -0.0581   0.1491   1.0000
   9.000   1.2368   0.02659   0.01738  -0.0568   0.1380   1.0000
   9.250   1.2537   0.02751   0.01840  -0.0556   0.1272   1.0000
   9.500   1.2691   0.02854   0.01949  -0.0543   0.1181   1.0000
   9.750   1.2816   0.02968   0.02061  -0.0527   0.1104   1.0000
  10.000   1.2950   0.03073   0.02183  -0.0510   0.1027   1.0000
  10.250   1.3042   0.03201   0.02310  -0.0490   0.0971   1.0000
  10.500   1.3156   0.03322   0.02447  -0.0473   0.0910   1.0000
  10.750   1.3230   0.03463   0.02591  -0.0454   0.0864   1.0000
  11.000   1.3325   0.03607   0.02750  -0.0438   0.0817   1.0000
  11.250   1.3404   0.03759   0.02916  -0.0422   0.0775   1.0000
  11.500   1.3457   0.03933   0.03092  -0.0406   0.0744   1.0000
  11.750   1.3531   0.04111   0.03287  -0.0393   0.0710   1.0000
  12.000   1.3593   0.04296   0.03490  -0.0380   0.0677   1.0000
  12.250   1.3637   0.04494   0.03699  -0.0369   0.0650   1.0000
  12.500   1.3670   0.04715   0.03923  -0.0359   0.0629   1.0000
  12.750   1.3712   0.04949   0.04180  -0.0350   0.0606   1.0000
  13.000   1.3738   0.05200   0.04453  -0.0343   0.0583   1.0000
  13.250   1.3749   0.05465   0.04737  -0.0338   0.0563   1.0000
  13.500   1.3751   0.05742   0.05026  -0.0335   0.0545   1.0000
  13.750   1.3752   0.06033   0.05325  -0.0334   0.0530   1.0000
  14.000   1.3744   0.06360   0.05666  -0.0334   0.0517   1.0000
  14.250   1.3688   0.06756   0.06092  -0.0339   0.0504   1.0000
  14.500   1.3614   0.07186   0.06549  -0.0348   0.0492   1.0000
  14.750   1.3526   0.07650   0.07037  -0.0362   0.0480   1.0000
  15.000   1.3428   0.08147   0.07554  -0.0380   0.0470   1.0000
  15.250   1.3323   0.08674   0.08100  -0.0402   0.0461   1.0000
  15.500   1.3219   0.09223   0.08666  -0.0427   0.0453   1.0000
  15.750   1.3118   0.09788   0.09246  -0.0454   0.0446   1.0000
  16.000   1.3030   0.10347   0.09816  -0.0482   0.0439   1.0000
  16.500   1.2730   0.11793   0.11294  -0.0564   0.0429   1.0000
  16.750   1.2446   0.12885   0.12410  -0.0636   0.0429   1.0000
  17.000   1.2086   0.14253   0.13797  -0.0728   0.0430   1.0000
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