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REPUBLIC S-3 AIRFOIL (s3-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: REPUBLIC S-3 AIRFOIL (s3-il)
Reynolds number: 100,000
Max Cl/Cd: 42.68 at α=8.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s3-il-100000-n5.txt
Download as CSV file: xf-s3-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: REPUBLIC S-3 AIRFOIL                            
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.5313   0.09160   0.08686  -0.0108   1.0000   0.0236
  -9.500  -0.5351   0.08593   0.08123  -0.0144   1.0000   0.0233
  -9.250  -0.5424   0.07911   0.07446  -0.0196   1.0000   0.0229
  -9.000  -0.5553   0.07284   0.06818  -0.0247   1.0000   0.0226
  -8.750  -0.5716   0.06792   0.06324  -0.0273   1.0000   0.0224
  -8.500  -0.5847   0.06379   0.05902  -0.0278   1.0000   0.0221
  -8.250  -0.5927   0.05951   0.05458  -0.0280   1.0000   0.0220
  -8.000  -0.5960   0.05541   0.05022  -0.0277   1.0000   0.0220
  -7.750  -0.5956   0.05137   0.04591  -0.0270   1.0000   0.0224
  -7.500  -0.5916   0.04751   0.04172  -0.0259   1.0000   0.0229
  -7.250  -0.5843   0.04382   0.03767  -0.0246   1.0000   0.0234
  -7.000  -0.5745   0.04031   0.03374  -0.0231   1.0000   0.0239
  -6.750  -0.5622   0.03704   0.03006  -0.0214   1.0000   0.0241
  -6.500  -0.5478   0.03405   0.02664  -0.0197   1.0000   0.0244
  -6.250  -0.5313   0.03140   0.02356  -0.0179   1.0000   0.0249
  -6.000  -0.5139   0.02906   0.02087  -0.0162   1.0000   0.0257
  -5.750  -0.4968   0.02752   0.01928  -0.0149   1.0000   0.0272
  -5.500  -0.4789   0.02637   0.01802  -0.0134   1.0000   0.0294
  -5.250  -0.4608   0.02488   0.01634  -0.0117   1.0000   0.0311
  -5.000  -0.4432   0.02345   0.01471  -0.0097   1.0000   0.0327
  -4.750  -0.4109   0.02191   0.01304  -0.0108   0.9914   0.0359
  -4.500  -0.3734   0.02076   0.01189  -0.0131   0.9801   0.0411
  -4.250  -0.3361   0.01951   0.01054  -0.0149   0.9691   0.0467
  -4.000  -0.3003   0.01850   0.00954  -0.0168   0.9571   0.0561
  -3.750  -0.2671   0.01761   0.00861  -0.0180   0.9436   0.0675
  -3.500  -0.2343   0.01685   0.00780  -0.0191   0.9298   0.0829
  -3.250  -0.2029   0.01612   0.00706  -0.0199   0.9156   0.1055
  -3.000  -0.1803   0.01435   0.00629  -0.0197   0.9001   0.3024
  -2.750  -0.1607   0.01330   0.00625  -0.0179   0.8843   0.5463
  -2.500  -0.1361   0.01307   0.00622  -0.0163   0.8688   0.6305
  -2.250  -0.1119   0.01298   0.00621  -0.0146   0.8530   0.6911
  -2.000  -0.0885   0.01297   0.00621  -0.0125   0.8361   0.7411
  -1.750  -0.0657   0.01299   0.00621  -0.0102   0.8190   0.7850
  -1.500  -0.0406   0.01300   0.00613  -0.0086   0.8026   0.8137
  -1.250  -0.0136   0.01297   0.00598  -0.0077   0.7874   0.8324
  -1.000   0.0145   0.01295   0.00585  -0.0071   0.7727   0.8493
  -0.750   0.0433   0.01294   0.00571  -0.0067   0.7576   0.8650
  -0.500   0.0728   0.01294   0.00558  -0.0065   0.7418   0.8797
  -0.250   0.1031   0.01294   0.00547  -0.0065   0.7233   0.8940
   0.000   0.1342   0.01295   0.00534  -0.0067   0.7013   0.9079
   0.250   0.1663   0.01296   0.00521  -0.0072   0.6758   0.9212
   0.500   0.1999   0.01298   0.00508  -0.0081   0.6462   0.9341
   0.750   0.2346   0.01300   0.00496  -0.0093   0.6126   0.9462
   1.000   0.2704   0.01305   0.00483  -0.0107   0.5762   0.9578
   1.250   0.3069   0.01315   0.00469  -0.0124   0.5330   0.9686
   1.500   0.3437   0.01332   0.00460  -0.0143   0.4904   0.9791
   2.000   0.4145   0.01380   0.00460  -0.0181   0.4269   1.0000
   2.250   0.4337   0.01406   0.00470  -0.0167   0.4070   1.0000
   2.500   0.4537   0.01431   0.00484  -0.0155   0.3882   1.0000
   2.750   0.4745   0.01458   0.00501  -0.0144   0.3705   1.0000
   3.000   0.4957   0.01485   0.00519  -0.0134   0.3536   1.0000
   3.250   0.5175   0.01513   0.00540  -0.0125   0.3381   1.0000
   3.500   0.5396   0.01542   0.00562  -0.0116   0.3243   1.0000
   3.750   0.5621   0.01574   0.00586  -0.0107   0.3123   1.0000
   4.000   0.5847   0.01608   0.00614  -0.0099   0.3019   1.0000
   4.250   0.6079   0.01643   0.00645  -0.0092   0.2920   1.0000
   4.500   0.6313   0.01680   0.00679  -0.0085   0.2834   1.0000
   4.750   0.6547   0.01721   0.00717  -0.0078   0.2758   1.0000
   5.000   0.6786   0.01763   0.00759  -0.0072   0.2686   1.0000
   5.250   0.7024   0.01806   0.00801  -0.0067   0.2617   1.0000
   5.500   0.7265   0.01852   0.00847  -0.0061   0.2557   1.0000
   5.750   0.7508   0.01897   0.00901  -0.0057   0.2498   1.0000
   6.000   0.7748   0.01945   0.00948  -0.0052   0.2445   1.0000
   6.250   0.7990   0.01989   0.01003  -0.0047   0.2377   1.0000
   6.500   0.8227   0.02031   0.01051  -0.0042   0.2307   1.0000
   6.750   0.8464   0.02073   0.01103  -0.0037   0.2234   1.0000
   7.000   0.8697   0.02111   0.01148  -0.0032   0.2157   1.0000
   7.250   0.8931   0.02155   0.01204  -0.0026   0.2091   1.0000
   7.500   0.9163   0.02196   0.01257  -0.0021   0.2025   1.0000
   7.750   0.9387   0.02234   0.01309  -0.0015   0.1935   1.0000
   8.000   0.9601   0.02268   0.01348  -0.0009   0.1827   1.0000
   8.250   0.9815   0.02308   0.01398  -0.0002   0.1718   1.0000
   8.500   1.0024   0.02350   0.01450   0.0004   0.1580   1.0000
   8.750   1.0235   0.02398   0.01509   0.0010   0.1439   1.0000
   9.000   1.0449   0.02451   0.01575   0.0017   0.1305   1.0000
   9.250   1.0653   0.02512   0.01647   0.0023   0.1085   1.0000
   9.500   1.0814   0.02610   0.01730   0.0033   0.0860   1.0000
   9.750   1.0966   0.02724   0.01842   0.0044   0.0739   1.0000
  10.000   1.1086   0.02868   0.01986   0.0057   0.0584   1.0000
  10.250   1.1189   0.03020   0.02140   0.0071   0.0309   1.0000
  10.500   1.1183   0.03258   0.02363   0.0091   0.0228   1.0000
  10.750   1.1193   0.03444   0.02561   0.0112   0.0209   1.0000
  11.000   1.1178   0.03639   0.02774   0.0132   0.0201   1.0000
  11.250   1.1145   0.03864   0.03018   0.0146   0.0195   1.0000
  11.500   1.1097   0.04126   0.03299   0.0153   0.0192   1.0000
  11.750   1.1005   0.04466   0.03660   0.0151   0.0188   1.0000
  12.000   1.0877   0.04892   0.04107   0.0138   0.0185   1.0000
  12.250   1.0740   0.05384   0.04619   0.0116   0.0185   1.0000
  12.500   1.0569   0.05989   0.05244   0.0083   0.0185   1.0000
  12.750   1.0377   0.06696   0.05971   0.0042   0.0187   1.0000
  13.000   1.0164   0.07467   0.06760  -0.0001   0.0187   1.0000
  13.250   1.0001   0.08152   0.07460  -0.0037   0.0189   1.0000
  13.500   0.9838   0.08835   0.08157  -0.0071   0.0190   1.0000
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