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S4233-136-84 (s4233-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: S4233-136-84 (s4233-il)
Reynolds number: 200,000
Max Cl/Cd: 77.75 at α=7.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s4233-il-200000.txt
Download as CSV file: xf-s4233-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S4233-136-84                                    
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.2368   0.08180   0.07884  -0.0604   0.9849   0.0684
  -9.500  -0.2250   0.07744   0.07447  -0.0633   0.9803   0.0707
  -9.250  -0.3761   0.08142   0.07843  -0.0610   0.9915   0.0666
  -9.000  -0.3495   0.07956   0.07655  -0.0611   0.9875   0.0682
  -8.750  -0.3307   0.07507   0.07205  -0.0668   0.9822   0.0707
  -8.500  -0.2656   0.04689   0.04389  -0.0926   0.9499   0.0806
  -8.250  -0.2697   0.04329   0.04023  -0.0943   0.9370   0.0819
  -8.000  -0.2807   0.03998   0.03681  -0.0943   0.9236   0.0832
  -7.750  -0.2900   0.03662   0.03330  -0.0939   0.9118   0.0855
  -7.500  -0.3586   0.03539   0.03022  -0.0974   0.9158   0.0459
  -7.250  -0.3514   0.03045   0.02415  -0.0940   0.9051   0.0352
  -7.000  -0.3309   0.02823   0.02169  -0.0930   0.8989   0.0344
  -6.750  -0.3123   0.02605   0.01924  -0.0918   0.8899   0.0340
  -6.500  -0.2905   0.02427   0.01717  -0.0906   0.8843   0.0339
  -6.250  -0.2682   0.02308   0.01576  -0.0896   0.8757   0.0344
  -6.000  -0.2452   0.02163   0.01410  -0.0886   0.8699   0.0355
  -5.750  -0.2224   0.02030   0.01274  -0.0878   0.8625   0.0365
  -5.500  -0.1990   0.01925   0.01165  -0.0868   0.8561   0.0373
  -5.250  -0.1758   0.01840   0.01076  -0.0859   0.8497   0.0386
  -5.000  -0.1526   0.01765   0.00995  -0.0850   0.8426   0.0403
  -4.750  -0.1287   0.01697   0.00916  -0.0840   0.8377   0.0427
  -4.500  -0.1065   0.01620   0.00840  -0.0833   0.8296   0.0468
  -4.250  -0.0823   0.01555   0.00771  -0.0826   0.8241   0.0570
  -4.000  -0.0636   0.01394   0.00686  -0.0817   0.8172   0.1984
  -3.750  -0.0411   0.01320   0.00658  -0.0811   0.8109   0.3202
  -3.500  -0.0174   0.01271   0.00641  -0.0804   0.8062   0.4204
  -3.250   0.0061   0.01249   0.00646  -0.0796   0.7985   0.5028
  -3.000   0.0311   0.01235   0.00642  -0.0787   0.7933   0.5658
  -2.750   0.0561   0.01235   0.00650  -0.0779   0.7870   0.6111
  -2.500   0.0819   0.01234   0.00648  -0.0772   0.7807   0.6425
  -2.250   0.1085   0.01229   0.00637  -0.0765   0.7762   0.6683
  -2.000   0.1340   0.01235   0.00642  -0.0759   0.7688   0.6927
  -1.750   0.1602   0.01230   0.00636  -0.0751   0.7633   0.7142
  -1.500   0.1862   0.01231   0.00633  -0.0745   0.7578   0.7353
  -1.250   0.2118   0.01232   0.00633  -0.0738   0.7511   0.7557
  -1.000   0.2381   0.01226   0.00623  -0.0731   0.7463   0.7743
  -0.750   0.2629   0.01229   0.00628  -0.0723   0.7395   0.7921
  -0.500   0.2884   0.01225   0.00622  -0.0715   0.7336   0.8097
  -0.250   0.3142   0.01222   0.00615  -0.0707   0.7287   0.8276
   0.000   0.3380   0.01224   0.00620  -0.0697   0.7214   0.8461
   0.250   0.3632   0.01218   0.00611  -0.0688   0.7163   0.8653
   0.500   0.3867   0.01219   0.00615  -0.0676   0.7098   0.8843
   0.750   0.4117   0.01216   0.00611  -0.0667   0.7036   0.9041
   1.000   0.4407   0.01211   0.00600  -0.0665   0.6987   0.9249
   1.250   0.4738   0.01215   0.00607  -0.0675   0.6911   0.9448
   1.500   0.5159   0.01210   0.00595  -0.0703   0.6856   0.9611
   1.750   0.5602   0.01215   0.00598  -0.0739   0.6783   0.9761
   2.000   0.6077   0.01211   0.00589  -0.0781   0.6717   0.9884
   2.250   0.6508   0.01213   0.00588  -0.0817   0.6647   1.0000
   2.500   0.6665   0.01220   0.00591  -0.0799   0.6577   1.0000
   2.750   0.6881   0.01230   0.00594  -0.0790   0.6516   1.0000
   3.000   0.7107   0.01242   0.00605  -0.0783   0.6437   1.0000
   3.250   0.7374   0.01251   0.00604  -0.0782   0.6379   1.0000
   3.500   0.7614   0.01266   0.00623  -0.0777   0.6293   1.0000
   3.750   0.7893   0.01274   0.00623  -0.0777   0.6233   1.0000
   4.000   0.8135   0.01290   0.00646  -0.0772   0.6143   1.0000
   4.250   0.8416   0.01299   0.00647  -0.0772   0.6079   1.0000
   4.500   0.8660   0.01316   0.00671  -0.0768   0.5986   1.0000
   4.750   0.8933   0.01327   0.00679  -0.0767   0.5914   1.0000
   5.000   0.9185   0.01342   0.00698  -0.0763   0.5822   1.0000
   5.250   0.9446   0.01356   0.00715  -0.0761   0.5738   1.0000
   5.500   0.9709   0.01368   0.00727  -0.0758   0.5649   1.0000
   5.750   0.9957   0.01385   0.00750  -0.0754   0.5551   1.0000
   6.000   1.0221   0.01399   0.00761  -0.0751   0.5460   1.0000
   6.250   1.0467   0.01413   0.00782  -0.0746   0.5352   1.0000
   6.500   1.0709   0.01431   0.00805  -0.0741   0.5240   1.0000
   6.750   1.0953   0.01446   0.00823  -0.0735   0.5124   1.0000
   7.000   1.1193   0.01462   0.00841  -0.0729   0.4999   1.0000
   7.250   1.1425   0.01480   0.00860  -0.0721   0.4865   1.0000
   7.500   1.1651   0.01501   0.00883  -0.0713   0.4727   1.0000
   7.750   1.1864   0.01526   0.00912  -0.0702   0.4575   1.0000
   8.000   1.2061   0.01553   0.00945  -0.0690   0.4404   1.0000
   8.250   1.2251   0.01585   0.00981  -0.0676   0.4226   1.0000
   8.500   1.2425   0.01622   0.01019  -0.0660   0.4031   1.0000
   8.750   1.2575   0.01667   0.01060  -0.0641   0.3815   1.0000
   9.000   1.2689   0.01722   0.01112  -0.0617   0.3556   1.0000
   9.250   1.2773   0.01788   0.01171  -0.0589   0.3280   1.0000
   9.500   1.2808   0.01864   0.01239  -0.0554   0.3010   1.0000
   9.750   1.2829   0.01959   0.01324  -0.0519   0.2743   1.0000
  10.000   1.2844   0.02073   0.01428  -0.0488   0.2480   1.0000
  10.250   1.2843   0.02209   0.01552  -0.0458   0.2201   1.0000
  10.500   1.2824   0.02370   0.01702  -0.0430   0.1904   1.0000
  10.750   1.2793   0.02557   0.01874  -0.0404   0.1610   1.0000
  11.000   1.2744   0.02773   0.02074  -0.0380   0.1318   1.0000
  11.250   1.2686   0.03012   0.02298  -0.0358   0.1052   1.0000
  11.500   1.2600   0.03290   0.02557  -0.0338   0.0792   1.0000
  11.750   1.2495   0.03603   0.02856  -0.0319   0.0588   1.0000
  12.000   1.2393   0.03933   0.03180  -0.0304   0.0462   1.0000
  12.250   1.2319   0.04253   0.03502  -0.0292   0.0405   1.0000
  12.500   1.2275   0.04554   0.03808  -0.0284   0.0364   1.0000
  12.750   1.2194   0.04906   0.04164  -0.0277   0.0341   1.0000
  13.000   1.2199   0.05180   0.04450  -0.0272   0.0321   1.0000
  13.250   1.2199   0.05467   0.04745  -0.0268   0.0304   1.0000
  13.500   1.2193   0.05765   0.05048  -0.0266   0.0290   1.0000
  13.750   1.2158   0.06090   0.05372  -0.0261   0.0275   1.0000
  14.000   1.2212   0.06335   0.05630  -0.0259   0.0264   1.0000
  14.250   1.2264   0.06580   0.05886  -0.0258   0.0255   1.0000
  14.500   1.2317   0.06826   0.06140  -0.0255   0.0245   1.0000
  14.750   1.2384   0.07056   0.06378  -0.0252   0.0239   1.0000
  15.000   1.2454   0.07284   0.06611  -0.0249   0.0232   1.0000
  15.250   1.2547   0.07488   0.06817  -0.0244   0.0226   1.0000
  15.500   1.2714   0.07619   0.06950  -0.0228   0.0219   1.0000
  15.750   1.2788   0.07888   0.07238  -0.0225   0.0216   1.0000
  16.000   1.2839   0.08184   0.07553  -0.0225   0.0215   1.0000
  16.250   1.2827   0.08563   0.07955  -0.0231   0.0213   1.0000
  16.500   1.2818   0.08950   0.08364  -0.0237   0.0212   1.0000
  16.750   1.2774   0.09390   0.08827  -0.0247   0.0212   1.0000
  17.000   1.2695   0.09888   0.09347  -0.0263   0.0211   1.0000
  17.250   1.2602   0.10419   0.09902  -0.0282   0.0211   1.0000
  17.500   1.2481   0.11001   0.10507  -0.0307   0.0210   1.0000
  17.750   1.2346   0.11629   0.11157  -0.0338   0.0210   1.0000
  18.000   1.2205   0.12292   0.11842  -0.0371   0.0211   1.0000
  18.250   1.2045   0.13013   0.12583  -0.0412   0.0212   1.0000
  18.500   1.1875   0.13782   0.13372  -0.0458   0.0212   1.0000
  18.750   1.1699   0.14598   0.14207  -0.0509   0.0214   1.0000
  19.000   1.1526   0.15441   0.15065  -0.0562   0.0216   1.0000
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