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SOMERS S102 AIRFOIL (BLUNT) (s102b-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: SOMERS S102 AIRFOIL (BLUNT) (s102b-il)
Reynolds number: 200,000
Max Cl/Cd: 60.51 at α=5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s102b-il-200000.txt
Download as CSV file: xf-s102b-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: SOMERS S102 AIRFOIL (BLUNT)                     
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -11.500  -0.3099   0.10789   0.10457  -0.0471   1.0000   0.0514
 -11.250  -0.3144   0.10357   0.10028  -0.0488   1.0000   0.0531
 -11.000  -0.4435   0.10290   0.09940  -0.0463   1.0000   0.0481
 -10.750  -0.4374   0.10010   0.09661  -0.0465   1.0000   0.0493
 -10.500  -0.4377   0.09568   0.09223  -0.0486   1.0000   0.0505
 -10.250  -0.4444   0.08958   0.08616  -0.0527   1.0000   0.0517
 -10.000  -0.4613   0.08203   0.07863  -0.0586   1.0000   0.0522
  -9.750  -0.4832   0.07601   0.07259  -0.0625   1.0000   0.0525
  -9.500  -0.5079   0.07162   0.06818  -0.0638   1.0000   0.0525
  -9.250  -0.5388   0.06926   0.06586  -0.0613   1.0000   0.0521
  -9.000  -0.5738   0.06807   0.06471  -0.0575   0.9970   0.0514
  -8.750  -0.5777   0.06379   0.05956  -0.0685   0.9808   0.0560
  -7.000  -0.4090   0.02892   0.02204  -0.0810   0.9309   0.0299
  -6.750  -0.3787   0.02600   0.01879  -0.0811   0.9251   0.0278
  -6.500  -0.3524   0.02401   0.01642  -0.0801   0.9161   0.0265
  -6.250  -0.3243   0.02250   0.01481  -0.0797   0.9096   0.0266
  -6.000  -0.3000   0.02135   0.01362  -0.0788   0.9010   0.0272
  -5.750  -0.2751   0.02031   0.01256  -0.0781   0.8940   0.0283
  -5.500  -0.2521   0.01945   0.01167  -0.0772   0.8859   0.0299
  -5.250  -0.2293   0.01851   0.01073  -0.0766   0.8791   0.0331
  -5.000  -0.2048   0.01791   0.01009  -0.0763   0.8726   0.0381
  -4.750  -0.1821   0.01684   0.00905  -0.0763   0.8657   0.0451
  -4.500  -0.1570   0.01565   0.00791  -0.0767   0.8609   0.0697
  -4.250  -0.1374   0.01334   0.00786  -0.0783   0.8540   0.5843
  -4.000  -0.1120   0.01469   0.00920  -0.0760   0.8488   0.6195
  -3.750  -0.0891   0.01606   0.01062  -0.0726   0.8448   0.6409
  -3.500  -0.0676   0.01727   0.01186  -0.0694   0.8393   0.6577
  -3.250  -0.0481   0.01862   0.01325  -0.0650   0.8347   0.6761
  -3.000  -0.0273   0.01978   0.01437  -0.0612   0.8310   0.6967
  -2.750  -0.0058   0.02019   0.01474  -0.0583   0.8278   0.7027
  -2.500   0.0212   0.02002   0.01450  -0.0588   0.8231   0.7054
  -2.250   0.0502   0.01974   0.01411  -0.0599   0.8190   0.7081
  -2.000   0.0815   0.01938   0.01361  -0.0617   0.8155   0.7111
  -1.750   0.1149   0.01900   0.01307  -0.0642   0.8129   0.7136
  -1.500   0.1413   0.01889   0.01294  -0.0643   0.8092   0.7148
  -1.250   0.1691   0.01877   0.01278  -0.0649   0.8056   0.7158
  -1.000   0.1972   0.01867   0.01263  -0.0654   0.8023   0.7172
  -0.750   0.2264   0.01853   0.01244  -0.0661   0.7993   0.7185
  -0.500   0.2568   0.01839   0.01223  -0.0672   0.7969   0.7195
  -0.250   0.2854   0.01838   0.01221  -0.0681   0.7939   0.7209
   0.000   0.3141   0.01837   0.01219  -0.0691   0.7901   0.7224
   0.250   0.3440   0.01830   0.01210  -0.0703   0.7868   0.7235
   0.500   0.3748   0.01819   0.01194  -0.0715   0.7836   0.7245
   0.750   0.4054   0.01800   0.01169  -0.0722   0.7782   0.7260
   1.000   0.4347   0.01772   0.01137  -0.0728   0.7690   0.7275
   1.250   0.4652   0.01740   0.01097  -0.0733   0.7605   0.7284
   1.500   0.4954   0.01710   0.01061  -0.0739   0.7516   0.7294
   1.750   0.5231   0.01683   0.01033  -0.0737   0.7421   0.7302
   2.000   0.5524   0.01648   0.00991  -0.0737   0.7329   0.7312
   2.250   0.5791   0.01634   0.00981  -0.0735   0.7234   0.7325
   2.500   0.6085   0.01618   0.00963  -0.0738   0.7174   0.7338
   2.750   0.6363   0.01609   0.00960  -0.0740   0.7095   0.7349
   3.000   0.6659   0.01588   0.00937  -0.0743   0.7015   0.7361
   3.250   0.6936   0.01575   0.00928  -0.0744   0.6917   0.7374
   3.500   0.7235   0.01554   0.00904  -0.0747   0.6828   0.7387
   3.750   0.7513   0.01537   0.00894  -0.0748   0.6714   0.7402
   4.000   0.7793   0.01519   0.00879  -0.0749   0.6586   0.7417
   4.250   0.8073   0.01498   0.00860  -0.0749   0.6428   0.7434
   4.500   0.8346   0.01475   0.00837  -0.0747   0.6221   0.7453
   4.750   0.8588   0.01455   0.00821  -0.0739   0.5912   0.7467
   5.000   0.8786   0.01452   0.00794  -0.0721   0.5023   0.7482
   5.250   0.8780   0.01613   0.00847  -0.0675   0.3385   0.7497
   5.500   0.8881   0.01736   0.00925  -0.0652   0.2717   0.7514
   5.750   0.9043   0.01820   0.00989  -0.0637   0.2427   0.7532
   6.000   0.9231   0.01889   0.01046  -0.0627   0.2255   0.7552
   6.250   0.9427   0.01955   0.01104  -0.0618   0.2135   0.7573
   6.500   0.9632   0.02017   0.01159  -0.0611   0.2043   0.7595
   6.750   0.9845   0.02074   0.01217  -0.0604   0.1970   0.7615
   7.000   1.0049   0.02128   0.01273  -0.0596   0.1906   0.7636
   7.250   1.0255   0.02197   0.01339  -0.0588   0.1848   0.7662
   7.500   1.0476   0.02246   0.01396  -0.0581   0.1793   0.7691
   7.750   1.0699   0.02308   0.01458  -0.0577   0.1745   0.7721
   8.000   1.0946   0.02389   0.01535  -0.0577   0.1700   0.7750
   8.250   1.1168   0.02438   0.01598  -0.0571   0.1656   0.7778
   8.500   1.1387   0.02495   0.01660  -0.0565   0.1613   0.7807
   8.750   1.1652   0.02586   0.01746  -0.0568   0.1570   0.7840
   9.000   1.1873   0.02647   0.01824  -0.0563   0.1533   0.7879
   9.250   1.2094   0.02709   0.01897  -0.0558   0.1493   0.7921
   9.500   1.2308   0.02771   0.01967  -0.0552   0.1455   0.7958
   9.750   1.2595   0.02885   0.02078  -0.0559   0.1410   0.8003
  10.000   1.2767   0.02941   0.02157  -0.0547   0.1377   0.8060
  10.250   1.2930   0.02999   0.02231  -0.0532   0.1338   0.8116
  10.500   1.3117   0.03064   0.02300  -0.0523   0.1300   0.8184
  10.750   1.3362   0.03179   0.02424  -0.0525   0.1257   0.8255
  11.000   1.3461   0.03238   0.02509  -0.0501   0.1223   0.8341
  11.250   1.3586   0.03302   0.02588  -0.0484   0.1185   0.8441
  11.500   1.3750   0.03373   0.02659  -0.0473   0.1147   0.8569
  11.750   1.3866   0.03471   0.02781  -0.0455   0.1109   0.8750
  12.000   1.3862   0.03518   0.02862  -0.0415   0.1078   0.9293
  12.250   1.3958   0.03595   0.02947  -0.0403   0.1040   1.0000
  12.500   1.4152   0.03713   0.03052  -0.0403   0.0996   1.0000
  12.750   1.4167   0.03835   0.03202  -0.0384   0.0964   1.0000
  13.000   1.4218   0.03953   0.03332  -0.0370   0.0925   1.0000
  13.250   1.4291   0.04062   0.03439  -0.0360   0.0891   1.0000
  13.500   1.4341   0.04227   0.03617  -0.0348   0.0853   1.0000
  13.750   1.4363   0.04389   0.03799  -0.0337   0.0814   1.0000
  14.000   1.4402   0.04540   0.03952  -0.0330   0.0779   1.0000
  14.250   1.4432   0.04740   0.04162  -0.0321   0.0742   1.0000
  14.500   1.4444   0.04951   0.04390  -0.0315   0.0703   1.0000
  14.750   1.4460   0.05158   0.04599  -0.0311   0.0670   1.0000
  15.000   1.4453   0.05418   0.04873  -0.0305   0.0634   1.0000
  15.250   1.4445   0.05681   0.05151  -0.0303   0.0598   1.0000
  15.500   1.4427   0.05959   0.05428  -0.0302   0.0567   1.0000
  15.750   1.4384   0.06295   0.05784  -0.0301   0.0536   1.0000
  16.000   1.4345   0.06634   0.06139  -0.0304   0.0506   1.0000
  16.250   1.4290   0.06995   0.06499  -0.0308   0.0482   1.0000
  16.500   1.4206   0.07419   0.06941  -0.0313   0.0459   1.0000
  16.750   1.4120   0.07864   0.07405  -0.0322   0.0437   1.0000
  17.000   1.4037   0.08316   0.07867  -0.0335   0.0418   1.0000
  17.250   1.3950   0.08761   0.08309  -0.0345   0.0400   1.0000
  17.500   1.3812   0.09340   0.08911  -0.0365   0.0387   1.0000
  17.750   1.3668   0.09953   0.09547  -0.0390   0.0374   1.0000
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