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S4233-136-84 (s4233-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: S4233-136-84 (s4233-il)
Reynolds number: 200,000
Max Cl/Cd: 76.99 at α=6.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s4233-il-200000-n5.txt
Download as CSV file: xf-s4233-il-200000-n5.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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.3792   0.08948   0.08602  -0.0520   1.0000   0.0167
 -10.500  -0.3875   0.08351   0.08011  -0.0550   1.0000   0.0164
 -10.250  -0.4028   0.07591   0.07257  -0.0590   1.0000   0.0160
 -10.000  -0.4480   0.05468   0.05108  -0.0808   0.9641   0.0152
  -9.750  -0.4666   0.04686   0.04288  -0.0903   0.9369   0.0150
  -9.500  -0.4854   0.04259   0.03823  -0.0907   0.9156   0.0148
  -9.250  -0.4932   0.03918   0.03445  -0.0898   0.9009   0.0148
  -9.000  -0.4947   0.03605   0.03090  -0.0884   0.8887   0.0147
  -8.750  -0.4890   0.03344   0.02791  -0.0871   0.8789   0.0148
  -8.500  -0.4788   0.03109   0.02517  -0.0858   0.8702   0.0148
  -8.250  -0.4645   0.02909   0.02285  -0.0848   0.8617   0.0150
  -8.000  -0.4480   0.02730   0.02072  -0.0837   0.8545   0.0151
  -7.750  -0.4289   0.02572   0.01886  -0.0829   0.8469   0.0154
  -7.500  -0.4085   0.02431   0.01719  -0.0821   0.8400   0.0156
  -7.250  -0.3868   0.02314   0.01580  -0.0814   0.8333   0.0162
  -7.000  -0.3640   0.02215   0.01458  -0.0808   0.8263   0.0169
  -6.750  -0.3408   0.02122   0.01343  -0.0801   0.8205   0.0174
  -6.500  -0.3183   0.02005   0.01220  -0.0796   0.8133   0.0178
  -6.250  -0.2955   0.01913   0.01120  -0.0789   0.8074   0.0182
  -6.000  -0.2720   0.01835   0.01035  -0.0784   0.8007   0.0186
  -5.750  -0.2483   0.01763   0.00955  -0.0779   0.7944   0.0191
  -5.500  -0.2242   0.01700   0.00881  -0.0774   0.7887   0.0197
  -5.250  -0.1995   0.01642   0.00814  -0.0771   0.7819   0.0205
  -5.000  -0.1745   0.01591   0.00750  -0.0766   0.7763   0.0215
  -4.750  -0.1492   0.01540   0.00691  -0.0764   0.7699   0.0230
  -4.500  -0.1234   0.01500   0.00644  -0.0761   0.7638   0.0257
  -4.250  -0.0975   0.01458   0.00594  -0.0758   0.7585   0.0296
  -4.000  -0.0715   0.01413   0.00549  -0.0756   0.7518   0.0394
  -3.750  -0.0465   0.01350   0.00504  -0.0754   0.7463   0.0861
  -3.500  -0.0217   0.01289   0.00472  -0.0753   0.7404   0.1592
  -3.250   0.0026   0.01223   0.00448  -0.0752   0.7342   0.2610
  -3.000   0.0277   0.01176   0.00428  -0.0749   0.7292   0.3493
  -2.750   0.0525   0.01136   0.00422  -0.0746   0.7227   0.4411
  -2.500   0.0781   0.01114   0.00417  -0.0742   0.7169   0.5066
  -2.250   0.1049   0.01104   0.00409  -0.0739   0.7117   0.5448
  -2.000   0.1318   0.01098   0.00406  -0.0736   0.7052   0.5757
  -1.750   0.1589   0.01093   0.00399  -0.0733   0.6999   0.6033
  -1.500   0.1862   0.01091   0.00395  -0.0731   0.6940   0.6277
  -1.250   0.2132   0.01088   0.00392  -0.0729   0.6879   0.6490
  -0.750   0.2676   0.01086   0.00387  -0.0724   0.6763   0.6864
  -0.500   0.2948   0.01086   0.00384  -0.0722   0.6706   0.7032
  -0.250   0.3219   0.01086   0.00382  -0.0720   0.6650   0.7196
   0.000   0.3488   0.01086   0.00384  -0.0717   0.6587   0.7360
   0.250   0.3758   0.01087   0.00382  -0.0714   0.6533   0.7525
   0.500   0.4024   0.01088   0.00386  -0.0711   0.6469   0.7688
   0.750   0.4289   0.01089   0.00387  -0.0708   0.6409   0.7850
   1.000   0.4554   0.01091   0.00389  -0.0704   0.6353   0.8017
   1.500   0.5075   0.01094   0.00396  -0.0694   0.6229   0.8369
   1.750   0.5333   0.01097   0.00404  -0.0689   0.6163   0.8564
   2.000   0.5599   0.01099   0.00408  -0.0685   0.6098   0.8778
   2.250   0.5877   0.01102   0.00413  -0.0684   0.6036   0.9011
   2.500   0.6184   0.01106   0.00419  -0.0690   0.5964   0.9266
   2.750   0.6540   0.01111   0.00424  -0.0706   0.5899   0.9523
   3.000   0.6919   0.01118   0.00432  -0.0729   0.5819   0.9809
   3.250   0.7242   0.01128   0.00438  -0.0741   0.5751   1.0000
   3.500   0.7495   0.01141   0.00452  -0.0738   0.5671   1.0000
   3.750   0.7753   0.01155   0.00461  -0.0736   0.5602   1.0000
   4.000   0.8010   0.01169   0.00477  -0.0734   0.5518   1.0000
   4.250   0.8268   0.01185   0.00491  -0.0731   0.5443   1.0000
   4.500   0.8524   0.01200   0.00509  -0.0729   0.5356   1.0000
   4.750   0.8781   0.01217   0.00526  -0.0727   0.5275   1.0000
   5.000   0.9035   0.01235   0.00544  -0.0724   0.5186   1.0000
   5.250   0.9288   0.01253   0.00566  -0.0721   0.5094   1.0000
   5.500   0.9538   0.01274   0.00585  -0.0717   0.5003   1.0000
   5.750   0.9786   0.01294   0.00609  -0.0713   0.4897   1.0000
   6.000   1.0030   0.01316   0.00635  -0.0709   0.4792   1.0000
   6.250   1.0270   0.01340   0.00660  -0.0703   0.4682   1.0000
   6.500   1.0504   0.01366   0.00686  -0.0697   0.4562   1.0000
   6.750   1.0733   0.01394   0.00716  -0.0691   0.4427   1.0000
   7.000   1.0953   0.01425   0.00749  -0.0682   0.4278   1.0000
   7.250   1.1162   0.01460   0.00783  -0.0673   0.4115   1.0000
   7.500   1.1365   0.01498   0.00820  -0.0662   0.3951   1.0000
   7.750   1.1561   0.01538   0.00862  -0.0651   0.3780   1.0000
   8.000   1.1736   0.01585   0.00907  -0.0636   0.3578   1.0000
   8.250   1.1883   0.01643   0.00958  -0.0618   0.3354   1.0000
   8.500   1.2001   0.01709   0.01016  -0.0595   0.3086   1.0000
   8.750   1.2087   0.01781   0.01079  -0.0568   0.2825   1.0000
   9.000   1.2131   0.01871   0.01158  -0.0536   0.2544   1.0000
   9.250   1.2155   0.01982   0.01253  -0.0505   0.2240   1.0000
   9.500   1.2169   0.02111   0.01366  -0.0476   0.1933   1.0000
  10.000   1.2193   0.02410   0.01637  -0.0425   0.1376   1.0000
  10.250   1.2206   0.02577   0.01791  -0.0404   0.1132   1.0000
  10.500   1.2233   0.02744   0.01950  -0.0385   0.0948   1.0000
  10.750   1.2264   0.02915   0.02116  -0.0369   0.0785   1.0000
  11.000   1.2292   0.03097   0.02295  -0.0354   0.0643   1.0000
  11.250   1.2305   0.03299   0.02491  -0.0340   0.0509   1.0000
  11.500   1.2330   0.03498   0.02689  -0.0328   0.0408   1.0000
  11.750   1.2349   0.03710   0.02902  -0.0317   0.0329   1.0000
  12.000   1.2359   0.03937   0.03130  -0.0307   0.0268   1.0000
  12.250   1.2382   0.04160   0.03360  -0.0299   0.0228   1.0000
  12.500   1.2393   0.04402   0.03608  -0.0292   0.0200   1.0000
  12.750   1.2410   0.04646   0.03862  -0.0286   0.0184   1.0000
  13.000   1.2411   0.04916   0.04140  -0.0282   0.0173   1.0000
  13.250   1.2420   0.05186   0.04422  -0.0279   0.0162   1.0000
  13.500   1.2435   0.05460   0.04708  -0.0278   0.0156   1.0000
  13.750   1.2441   0.05752   0.05011  -0.0279   0.0150   1.0000
  14.000   1.2437   0.06062   0.05333  -0.0280   0.0144   1.0000
  14.250   1.2415   0.06406   0.05685  -0.0284   0.0138   1.0000
  14.500   1.2385   0.06770   0.06059  -0.0289   0.0134   1.0000
  14.750   1.2384   0.07106   0.06409  -0.0295   0.0130   1.0000
  15.000   1.2371   0.07463   0.06779  -0.0301   0.0126   1.0000
  15.250   1.2357   0.07833   0.07162  -0.0310   0.0123   1.0000
  15.500   1.2334   0.08222   0.07564  -0.0319   0.0120   1.0000
  15.750   1.2310   0.08620   0.07973  -0.0330   0.0117   1.0000
  16.000   1.2289   0.09019   0.08383  -0.0342   0.0115   1.0000
  16.250   1.2268   0.09424   0.08800  -0.0354   0.0114   1.0000
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