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S4310 (s4310-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: S4310 (s4310-il)
Reynolds number: 200,000
Max Cl/Cd: 78.5 at α=5.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s4310-il-200000-n5.txt
Download as CSV file: xf-s4310-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S4310                                           
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.2990   0.10291   0.09947  -0.0411   1.0000   0.0215
  -9.250  -0.2959   0.09377   0.09039  -0.0422   1.0000   0.0159
  -9.000  -0.2933   0.09107   0.08775  -0.0424   1.0000   0.0157
  -8.750  -0.2816   0.08729   0.08399  -0.0457   0.9841   0.0154
  -8.500  -0.2673   0.08276   0.07945  -0.0508   0.9674   0.0151
  -8.250  -0.2544   0.07755   0.07424  -0.0567   0.9513   0.0150
  -8.000  -0.2438   0.07268   0.06935  -0.0622   0.9342   0.0148
  -7.500  -0.2444   0.06118   0.05779  -0.0739   0.8961   0.0155
  -7.250  -0.2473   0.05191   0.04835  -0.0819   0.8800   0.0159
  -7.000  -0.2433   0.04622   0.04244  -0.0849   0.8686   0.0157
  -6.750  -0.2412   0.03894   0.03471  -0.0875   0.8573   0.0158
  -6.500  -0.2328   0.03347   0.02870  -0.0884   0.8477   0.0158
  -6.250  -0.2191   0.02912   0.02369  -0.0883   0.8400   0.0159
  -6.000  -0.2011   0.02586   0.01989  -0.0880   0.8315   0.0163
  -5.750  -0.1799   0.02386   0.01757  -0.0876   0.8249   0.0168
  -5.500  -0.1564   0.02234   0.01577  -0.0873   0.8169   0.0174
  -5.250  -0.1323   0.02097   0.01410  -0.0868   0.8106   0.0182
  -5.000  -0.1068   0.01995   0.01280  -0.0865   0.8029   0.0199
  -4.750  -0.0808   0.01903   0.01152  -0.0859   0.7965   0.0214
  -4.500  -0.0557   0.01755   0.00989  -0.0856   0.7893   0.0224
  -4.250  -0.0299   0.01670   0.00891  -0.0852   0.7828   0.0236
  -4.000  -0.0036   0.01602   0.00813  -0.0848   0.7758   0.0253
  -3.750   0.0230   0.01550   0.00747  -0.0845   0.7692   0.0277
  -3.500   0.0491   0.01477   0.00665  -0.0841   0.7627   0.0293
  -3.250   0.0755   0.01421   0.00603  -0.0838   0.7559   0.0312
  -3.000   0.1023   0.01384   0.00558  -0.0835   0.7497   0.0343
  -2.750   0.1293   0.01348   0.00514  -0.0833   0.7426   0.0374
  -2.250   0.1835   0.01280   0.00435  -0.0828   0.7295   0.0494
  -2.000   0.2104   0.01242   0.00405  -0.0826   0.7234   0.0789
  -1.750   0.2371   0.01205   0.00387  -0.0825   0.7164   0.1377
  -1.500   0.2638   0.01174   0.00371  -0.0823   0.7098   0.2020
  -1.250   0.2898   0.01131   0.00364  -0.0822   0.7031   0.3105
  -1.000   0.3142   0.01073   0.00361  -0.0818   0.6963   0.4720
  -0.750   0.3362   0.01016   0.00362  -0.0804   0.6898   0.6485
  -0.500   0.3563   0.00973   0.00367  -0.0779   0.6828   0.8213
  -0.250   0.3972   0.00959   0.00355  -0.0798   0.6762   0.9488
   0.000   0.4438   0.00956   0.00340  -0.0837   0.6682   1.0000
   0.250   0.4694   0.00964   0.00334  -0.0832   0.6611   1.0000
   0.500   0.4951   0.00971   0.00332  -0.0827   0.6531   1.0000
   0.750   0.5211   0.00980   0.00330  -0.0823   0.6454   1.0000
   1.000   0.5471   0.00989   0.00329  -0.0819   0.6370   1.0000
   1.250   0.5733   0.00999   0.00330  -0.0815   0.6285   1.0000
   1.500   0.5995   0.01009   0.00330  -0.0812   0.6204   1.0000
   1.750   0.6258   0.01019   0.00335  -0.0808   0.6111   1.0000
   2.000   0.6521   0.01030   0.00339  -0.0805   0.6026   1.0000
   2.250   0.6784   0.01042   0.00344  -0.0802   0.5933   1.0000
   2.500   0.7047   0.01054   0.00352  -0.0799   0.5838   1.0000
   2.750   0.7309   0.01067   0.00359  -0.0795   0.5747   1.0000
   3.000   0.7571   0.01080   0.00368  -0.0792   0.5642   1.0000
   3.250   0.7832   0.01094   0.00380  -0.0789   0.5535   1.0000
   3.500   0.8091   0.01110   0.00391  -0.0785   0.5424   1.0000
   3.750   0.8348   0.01126   0.00403  -0.0781   0.5307   1.0000
   4.000   0.8604   0.01144   0.00416  -0.0777   0.5182   1.0000
   4.250   0.8858   0.01163   0.00433  -0.0773   0.5050   1.0000
   4.500   0.9110   0.01183   0.00450  -0.0769   0.4911   1.0000
   4.750   0.9360   0.01205   0.00468  -0.0764   0.4768   1.0000
   5.000   0.9606   0.01229   0.00488  -0.0759   0.4617   1.0000
   5.250   0.9848   0.01256   0.00513  -0.0753   0.4461   1.0000
   5.500   1.0087   0.01285   0.00537  -0.0748   0.4297   1.0000
   5.750   1.0323   0.01315   0.00565  -0.0741   0.4126   1.0000
   6.000   1.0554   0.01349   0.00594  -0.0734   0.3949   1.0000
   6.250   1.0779   0.01386   0.00629  -0.0727   0.3771   1.0000
   6.500   1.0997   0.01428   0.00665  -0.0718   0.3592   1.0000
   6.750   1.1213   0.01470   0.00703  -0.0710   0.3416   1.0000
   7.000   1.1424   0.01515   0.00744  -0.0701   0.3239   1.0000
   7.250   1.1629   0.01562   0.00790  -0.0691   0.3071   1.0000
   7.500   1.1827   0.01613   0.00838  -0.0680   0.2904   1.0000
   7.750   1.2019   0.01666   0.00888  -0.0669   0.2749   1.0000
   8.000   1.2205   0.01721   0.00941  -0.0657   0.2600   1.0000
   8.250   1.2384   0.01778   0.00999  -0.0644   0.2458   1.0000
   8.500   1.2557   0.01837   0.01057  -0.0630   0.2321   1.0000
   8.750   1.2722   0.01897   0.01119  -0.0615   0.2194   1.0000
   9.000   1.2872   0.01959   0.01182  -0.0599   0.2077   1.0000
   9.250   1.2998   0.02025   0.01250  -0.0578   0.1964   1.0000
   9.500   1.3114   0.02100   0.01326  -0.0557   0.1856   1.0000
   9.750   1.3233   0.02177   0.01406  -0.0538   0.1753   1.0000
  10.000   1.3352   0.02257   0.01491  -0.0520   0.1656   1.0000
  10.250   1.3456   0.02350   0.01586  -0.0502   0.1562   1.0000
  10.500   1.3550   0.02452   0.01690  -0.0484   0.1471   1.0000
  10.750   1.3659   0.02551   0.01795  -0.0468   0.1384   1.0000
  11.000   1.3744   0.02668   0.01915  -0.0452   0.1301   1.0000
  11.250   1.3819   0.02798   0.02048  -0.0437   0.1206   1.0000
  11.500   1.3902   0.02927   0.02183  -0.0423   0.1109   1.0000
  11.750   1.3970   0.03074   0.02331  -0.0410   0.1015   1.0000
  12.000   1.4021   0.03239   0.02497  -0.0397   0.0930   1.0000
  12.250   1.4075   0.03408   0.02668  -0.0386   0.0837   1.0000
  12.500   1.4136   0.03577   0.02844  -0.0376   0.0767   1.0000
  12.750   1.4166   0.03780   0.03049  -0.0366   0.0701   1.0000
  13.000   1.4222   0.03965   0.03243  -0.0359   0.0637   1.0000
  13.250   1.4243   0.04190   0.03472  -0.0352   0.0580   1.0000
  13.500   1.4269   0.04416   0.03706  -0.0346   0.0513   1.0000
  13.750   1.4282   0.04663   0.03960  -0.0342   0.0461   1.0000
  14.000   1.4288   0.04925   0.04230  -0.0338   0.0408   1.0000
  14.250   1.4282   0.05211   0.04523  -0.0337   0.0356   1.0000
  14.500   1.4246   0.05543   0.04859  -0.0337   0.0297   1.0000
  14.750   1.4208   0.05891   0.05214  -0.0340   0.0247   1.0000
  15.000   1.4151   0.06276   0.05606  -0.0345   0.0203   1.0000
  15.250   1.4070   0.06710   0.06048  -0.0353   0.0164   1.0000
  15.500   1.3998   0.07149   0.06497  -0.0363   0.0142   1.0000
  15.750   1.3905   0.07637   0.06996  -0.0377   0.0120   1.0000
  16.000   1.3820   0.08128   0.07500  -0.0392   0.0109   1.0000
  16.250   1.3712   0.08676   0.08061  -0.0411   0.0100   1.0000
  16.500   1.3624   0.09208   0.08608  -0.0431   0.0097   1.0000
  16.750   1.3524   0.09777   0.09194  -0.0454   0.0092   1.0000
  17.000   1.3409   0.10389   0.09822  -0.0481   0.0087   1.0000
  17.250   1.3297   0.11010   0.10459  -0.0509   0.0085   1.0000
  17.500   1.3174   0.11667   0.11132  -0.0541   0.0083   1.0000
  17.750   1.3052   0.12337   0.11819  -0.0575   0.0082   1.0000
  18.000   1.2929   0.13026   0.12523  -0.0611   0.0081   1.0000
  18.250   1.2802   0.13737   0.13248  -0.0649   0.0079   1.0000
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