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SOMERS S102 AIRFOIL (BLUNT) (s102b-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: SOMERS S102 AIRFOIL (BLUNT) (s102b-il)
Reynolds number: 50,000
Max Cl/Cd: 28.11 at α=6.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s102b-il-50000-n5.txt
Download as CSV file: xf-s102b-il-50000-n5.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 =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.4430   0.10428   0.09711  -0.0483   1.0000   0.0424
 -10.750  -0.4518   0.09728   0.09017  -0.0525   1.0000   0.0411
 -10.250  -0.5146   0.08141   0.07413  -0.0632   1.0000   0.0381
 -10.000  -0.5276   0.07761   0.07032  -0.0639   1.0000   0.0378
  -9.750  -0.5436   0.07430   0.06701  -0.0636   1.0000   0.0376
  -9.500  -0.5630   0.07170   0.06441  -0.0619   1.0000   0.0375
  -9.250  -0.5827   0.06940   0.06210  -0.0594   1.0000   0.0373
  -9.000  -0.6004   0.06720   0.05985  -0.0566   1.0000   0.0371
  -8.750  -0.6173   0.06516   0.05774  -0.0533   1.0000   0.0370
  -8.500  -0.6326   0.06318   0.05566  -0.0498   1.0000   0.0369
  -8.250  -0.6453   0.06115   0.05349  -0.0465   1.0000   0.0367
  -8.000  -0.6479   0.05841   0.05050  -0.0451   0.9977   0.0366
  -7.750  -0.6289   0.05433   0.04595  -0.0475   0.9895   0.0365
  -7.500  -0.6059   0.05056   0.04167  -0.0497   0.9824   0.0366
  -7.250  -0.5821   0.04731   0.03794  -0.0510   0.9747   0.0368
  -7.000  -0.5523   0.04428   0.03440  -0.0526   0.9691   0.0374
  -6.750  -0.5256   0.04186   0.03159  -0.0531   0.9619   0.0386
  -6.500  -0.4943   0.03995   0.02961  -0.0546   0.9569   0.0413
  -6.250  -0.4641   0.03828   0.02767  -0.0549   0.9514   0.0441
  -6.000  -0.4316   0.03689   0.02598  -0.0544   0.9465   0.0464
  -5.750  -0.3983   0.03576   0.02494  -0.0543   0.9428   0.0507
  -5.500  -0.3650   0.03487   0.02388  -0.0542   0.9390   0.0569
  -5.250  -0.3454   0.03397   0.02301  -0.0529   0.9315   0.0627
  -5.000  -0.3196   0.03286   0.02188  -0.0533   0.9261   0.0730
  -4.750  -0.3012   0.03174   0.02078  -0.0529   0.9192   0.0870
  -4.500  -0.2825   0.03019   0.01946  -0.0533   0.9127   0.1166
  -4.250  -0.2775   0.02915   0.02134  -0.0479   0.9080   0.5169
  -4.000  -0.2625   0.03060   0.02233  -0.0454   0.8992   0.6271
  -3.750  -0.2473   0.03370   0.02537  -0.0358   0.8949   0.6878
  -3.500  -0.2236   0.03565   0.02715  -0.0286   0.8924   0.7339
  -3.250  -0.2124   0.03549   0.02676  -0.0266   0.8851   0.7442
  -3.000  -0.1862   0.03518   0.02617  -0.0269   0.8806   0.7481
  -2.750  -0.1557   0.03485   0.02556  -0.0281   0.8771   0.7518
  -2.500  -0.1404   0.03461   0.02515  -0.0272   0.8706   0.7561
  -2.250  -0.1177   0.03431   0.02461  -0.0280   0.8656   0.7602
  -2.000  -0.0890   0.03407   0.02418  -0.0291   0.8622   0.7626
  -1.750  -0.0665   0.03394   0.02389  -0.0291   0.8579   0.7652
  -1.500  -0.0482   0.03385   0.02367  -0.0286   0.8522   0.7679
  -1.250  -0.0208   0.03372   0.02338  -0.0297   0.8483   0.7704
  -1.000   0.0100   0.03359   0.02310  -0.0315   0.8454   0.7729
  -0.750   0.0279   0.03364   0.02304  -0.0314   0.8401   0.7754
  -0.500   0.0504   0.03366   0.02298  -0.0318   0.8352   0.7774
  -0.250   0.0786   0.03367   0.02290  -0.0327   0.8318   0.7793
   0.000   0.1106   0.03367   0.02281  -0.0343   0.8291   0.7810
   0.250   0.1242   0.03392   0.02302  -0.0333   0.8230   0.7830
   0.500   0.1485   0.03408   0.02313  -0.0339   0.8183   0.7851
   0.750   0.1797   0.03419   0.02319  -0.0356   0.8149   0.7873
   1.000   0.2122   0.03432   0.02328  -0.0374   0.8116   0.7894
   1.250   0.2276   0.03474   0.02370  -0.0371   0.8047   0.7916
   1.500   0.2570   0.03494   0.02389  -0.0383   0.8003   0.7931
   1.750   0.2911   0.03506   0.02402  -0.0400   0.7970   0.7948
   2.000   0.3048   0.03555   0.02455  -0.0390   0.7893   0.7971
   2.250   0.3342   0.03578   0.02482  -0.0401   0.7841   0.7995
   2.500   0.3722   0.03585   0.02493  -0.0422   0.7804   0.8017
   2.750   0.3867   0.03642   0.02556  -0.0415   0.7707   0.8043
   3.000   0.4260   0.03641   0.02561  -0.0438   0.7655   0.8063
   3.250   0.4500   0.03654   0.02581  -0.0437   0.7536   0.8084
   3.500   0.4864   0.03582   0.02517  -0.0440   0.7391   0.8104
   3.750   0.5255   0.03464   0.02405  -0.0439   0.7222   0.8128
   4.000   0.5615   0.03355   0.02306  -0.0436   0.7055   0.8155
   4.250   0.5925   0.03292   0.02252  -0.0433   0.6908   0.8186
   4.500   0.6234   0.03238   0.02208  -0.0432   0.6765   0.8218
   4.750   0.6518   0.03184   0.02170  -0.0426   0.6615   0.8248
   5.000   0.6770   0.03137   0.02137  -0.0416   0.6449   0.8277
   5.250   0.7011   0.03090   0.02105  -0.0404   0.6257   0.8310
   5.500   0.7267   0.03032   0.02063  -0.0394   0.6043   0.8347
   5.750   0.7392   0.03046   0.02096  -0.0375   0.5743   0.8391
   6.000   0.7421   0.03101   0.02171  -0.0345   0.5353   0.8437
   6.250   0.7678   0.03017   0.02088  -0.0329   0.4773   0.8487
   6.500   0.8081   0.02875   0.01869  -0.0316   0.3909   0.8533
   6.750   0.8182   0.02963   0.01911  -0.0291   0.3408   0.8585
   7.000   0.8289   0.03078   0.02001  -0.0274   0.3087   0.8645
   7.250   0.8431   0.03188   0.02097  -0.0262   0.2861   0.8708
   7.500   0.8586   0.03283   0.02185  -0.0250   0.2697   0.8777
   7.750   0.8770   0.03373   0.02272  -0.0243   0.2559   0.8858
   8.000   0.8961   0.03451   0.02351  -0.0234   0.2444   0.8956
   8.250   0.9173   0.03522   0.02424  -0.0227   0.2342   0.9079
   8.500   0.9426   0.03587   0.02503  -0.0225   0.2252   0.9250
   9.000   1.0036   0.03733   0.02671  -0.0242   0.2086   1.0000
   9.250   1.0421   0.03835   0.02769  -0.0264   0.2008   1.0000
   9.500   1.0756   0.03961   0.02921  -0.0280   0.1939   1.0000
   9.750   1.1140   0.04089   0.03047  -0.0303   0.1873   1.0000
  10.000   1.1392   0.04241   0.03228  -0.0310   0.1811   1.0000
  10.250   1.1666   0.04391   0.03395  -0.0320   0.1753   1.0000
  10.500   1.1966   0.04550   0.03558  -0.0331   0.1701   1.0000
  10.750   1.2105   0.04737   0.03783  -0.0325   0.1648   1.0000
  11.000   1.2308   0.04904   0.03964  -0.0325   0.1597   1.0000
  11.250   1.2531   0.05086   0.04155  -0.0328   0.1551   1.0000
  11.500   1.2542   0.05311   0.04424  -0.0308   0.1509   1.0000
  11.750   1.2619   0.05514   0.04649  -0.0296   0.1464   1.0000
  12.000   1.2862   0.05673   0.04806  -0.0299   0.1418   1.0000
  12.250   1.2746   0.05966   0.05140  -0.0272   0.1388   1.0000
  12.500   1.2627   0.06276   0.05486  -0.0251   0.1356   1.0000
  12.750   1.2558   0.06569   0.05803  -0.0236   0.1323   1.0000
  13.000   1.2686   0.06746   0.05984  -0.0231   0.1283   1.0000
  13.250   1.2570   0.07102   0.06363  -0.0219   0.1258   1.0000
  13.500   1.2242   0.07644   0.06940  -0.0210   0.1246   1.0000
  13.750   1.1862   0.08309   0.07636  -0.0215   0.1237   1.0000
  14.000   1.1379   0.09197   0.08549  -0.0238   0.1235   1.0000
  14.250   1.0682   0.10590   0.09960  -0.0303   0.1243   1.0000
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