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S3025 9.38% (s3025-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: S3025 9.38% (s3025-il)
Reynolds number: 200,000
Max Cl/Cd: 77.1 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s3025-il-200000-n5.txt
Download as CSV file: xf-s3025-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S3025 9.38%                                     
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.3482   0.10148   0.09789  -0.0339   1.0000   0.0247
  -9.000  -0.3473   0.09822   0.09468  -0.0354   1.0000   0.0248
  -8.750  -0.3483   0.09491   0.09143  -0.0371   1.0000   0.0250
  -8.500  -0.3497   0.09100   0.08758  -0.0369   1.0000   0.0255
  -8.250  -0.3502   0.08803   0.08467  -0.0372   1.0000   0.0256
  -8.000  -0.3460   0.08584   0.08252  -0.0356   1.0000   0.0262
  -7.750  -0.3489   0.08336   0.08010  -0.0351   1.0000   0.0265
  -7.500  -0.3562   0.08110   0.07792  -0.0341   1.0000   0.0267
  -6.500  -0.3000   0.05634   0.05303  -0.0642   0.9733   0.0201
  -6.250  -0.2762   0.04450   0.04077  -0.0734   0.9613   0.0140
  -6.000  -0.2546   0.03958   0.03561  -0.0770   0.9501   0.0136
  -5.750  -0.2311   0.03436   0.02999  -0.0800   0.9391   0.0132
  -5.500  -0.2050   0.02973   0.02487  -0.0821   0.9294   0.0129
  -5.250  -0.1791   0.02569   0.02025  -0.0831   0.9183   0.0126
  -5.000  -0.1520   0.02261   0.01660  -0.0835   0.9074   0.0126
  -4.750  -0.1229   0.02026   0.01373  -0.0839   0.8971   0.0127
  -4.500  -0.0927   0.01842   0.01148  -0.0842   0.8869   0.0130
  -4.250  -0.0637   0.01712   0.00986  -0.0843   0.8753   0.0136
  -4.000  -0.0356   0.01600   0.00854  -0.0842   0.8631   0.0149
  -3.750  -0.0079   0.01518   0.00761  -0.0841   0.8511   0.0160
  -3.500   0.0194   0.01437   0.00664  -0.0838   0.8390   0.0167
  -3.250   0.0464   0.01371   0.00584  -0.0835   0.8272   0.0175
  -3.000   0.0732   0.01318   0.00516  -0.0830   0.8153   0.0187
  -2.750   0.0997   0.01271   0.00455  -0.0826   0.8034   0.0204
  -2.500   0.1265   0.01239   0.00412  -0.0823   0.7920   0.0250
  -2.250   0.1530   0.01193   0.00367  -0.0819   0.7813   0.0405
  -2.000   0.1791   0.01144   0.00337  -0.0815   0.7709   0.1036
  -1.750   0.2039   0.01085   0.00323  -0.0813   0.7602   0.2304
  -1.250   0.2524   0.00989   0.00306  -0.0801   0.7407   0.4994
  -1.000   0.2739   0.00938   0.00304  -0.0786   0.7307   0.6572
  -0.750   0.2964   0.00894   0.00304  -0.0765   0.7216   0.8358
  -0.500   0.3507   0.00882   0.00288  -0.0815   0.7123   0.9748
  -0.250   0.3892   0.00885   0.00275  -0.0838   0.7018   1.0000
   0.000   0.4141   0.00894   0.00270  -0.0831   0.6919   1.0000
   0.250   0.4393   0.00904   0.00266  -0.0825   0.6823   1.0000
   0.500   0.4644   0.00913   0.00265  -0.0819   0.6718   1.0000
   0.750   0.4898   0.00923   0.00264  -0.0813   0.6616   1.0000
   1.000   0.5152   0.00934   0.00264  -0.0808   0.6518   1.0000
   1.250   0.5407   0.00945   0.00267  -0.0802   0.6411   1.0000
   1.500   0.5663   0.00956   0.00271  -0.0797   0.6305   1.0000
   1.750   0.5919   0.00968   0.00276  -0.0792   0.6202   1.0000
   2.000   0.6175   0.00981   0.00281  -0.0787   0.6096   1.0000
   2.250   0.6431   0.00993   0.00289  -0.0782   0.5984   1.0000
   2.500   0.6688   0.01006   0.00298  -0.0777   0.5872   1.0000
   2.750   0.6943   0.01020   0.00308  -0.0772   0.5760   1.0000
   3.000   0.7198   0.01036   0.00318  -0.0767   0.5643   1.0000
   3.250   0.7452   0.01051   0.00329  -0.0762   0.5519   1.0000
   3.500   0.7705   0.01067   0.00345  -0.0757   0.5387   1.0000
   3.750   0.7957   0.01084   0.00359  -0.0752   0.5247   1.0000
   4.000   0.8206   0.01102   0.00374  -0.0746   0.5099   1.0000
   4.250   0.8453   0.01123   0.00393  -0.0740   0.4942   1.0000
   4.500   0.8698   0.01144   0.00412  -0.0734   0.4774   1.0000
   4.750   0.8942   0.01167   0.00433  -0.0727   0.4599   1.0000
   5.000   0.9182   0.01193   0.00455  -0.0721   0.4413   1.0000
   5.250   0.9418   0.01222   0.00482  -0.0713   0.4222   1.0000
   5.500   0.9653   0.01252   0.00510  -0.0706   0.4022   1.0000
   5.750   0.9881   0.01287   0.00540  -0.0697   0.3806   1.0000
   6.000   1.0106   0.01324   0.00573  -0.0689   0.3586   1.0000
   6.250   1.0326   0.01365   0.00612  -0.0680   0.3366   1.0000
   6.500   1.0545   0.01408   0.00651  -0.0671   0.3151   1.0000
   6.750   1.0758   0.01455   0.00694  -0.0661   0.2941   1.0000
   7.000   1.0965   0.01506   0.00741  -0.0650   0.2701   1.0000
   7.250   1.1157   0.01567   0.00794  -0.0638   0.2419   1.0000
   7.500   1.1334   0.01639   0.00851  -0.0624   0.2092   1.0000
   7.750   1.1511   0.01712   0.00912  -0.0611   0.1802   1.0000
   8.000   1.1697   0.01777   0.00973  -0.0598   0.1580   1.0000
   8.250   1.1866   0.01854   0.01041  -0.0584   0.1345   1.0000
   8.500   1.2033   0.01930   0.01115  -0.0570   0.1153   1.0000
   8.750   1.2182   0.02018   0.01194  -0.0553   0.0925   1.0000
   9.000   1.2317   0.02114   0.01281  -0.0535   0.0715   1.0000
   9.250   1.2426   0.02223   0.01379  -0.0513   0.0505   1.0000
   9.500   1.2502   0.02339   0.01487  -0.0486   0.0343   1.0000
   9.750   1.2576   0.02457   0.01604  -0.0459   0.0246   1.0000
  10.000   1.2653   0.02574   0.01727  -0.0435   0.0204   1.0000
  10.250   1.2736   0.02690   0.01855  -0.0412   0.0184   1.0000
  10.500   1.2814   0.02812   0.01989  -0.0391   0.0172   1.0000
  10.750   1.2872   0.02953   0.02142  -0.0369   0.0162   1.0000
  11.000   1.2915   0.03111   0.02311  -0.0350   0.0155   1.0000
  11.250   1.2936   0.03294   0.02507  -0.0331   0.0149   1.0000
  11.500   1.2970   0.03476   0.02704  -0.0315   0.0145   1.0000
  11.750   1.3000   0.03672   0.02915  -0.0302   0.0139   1.0000
  12.000   1.3014   0.03891   0.03150  -0.0291   0.0135   1.0000
  12.250   1.3029   0.04122   0.03395  -0.0283   0.0129   1.0000
  12.500   1.3022   0.04387   0.03675  -0.0276   0.0126   1.0000
  12.750   1.3011   0.04667   0.03969  -0.0272   0.0124   1.0000
  13.000   1.2995   0.04964   0.04280  -0.0270   0.0121   1.0000
  13.250   1.2969   0.05283   0.04612  -0.0269   0.0119   1.0000
  13.500   1.2938   0.05620   0.04962  -0.0271   0.0117   1.0000
  13.750   1.2899   0.05977   0.05331  -0.0274   0.0115   1.0000
  14.000   1.2862   0.06341   0.05709  -0.0279   0.0114   1.0000
  14.250   1.2818   0.06727   0.06107  -0.0286   0.0113   1.0000
  14.500   1.2767   0.07132   0.06524  -0.0293   0.0111   1.0000
  14.750   1.2726   0.07535   0.06939  -0.0300   0.0109   1.0000
  15.000   1.2692   0.07941   0.07358  -0.0309   0.0108   1.0000
  15.250   1.2657   0.08366   0.07801  -0.0322   0.0108   1.0000
  15.500   1.2610   0.08823   0.08276  -0.0338   0.0107   1.0000
  15.750   1.2552   0.09319   0.08791  -0.0358   0.0105   1.0000
  16.000   1.2488   0.09836   0.09326  -0.0380   0.0104   1.0000
  16.250   1.2411   0.10394   0.09903  -0.0405   0.0103   1.0000
  16.500   1.2329   0.10978   0.10505  -0.0434   0.0102   1.0000
  16.750   1.2233   0.11612   0.11161  -0.0468   0.0101   1.0000
  17.000   1.2132   0.12276   0.11843  -0.0505   0.0099   1.0000
  17.250   1.2025   0.12968   0.12553  -0.0544   0.0099   1.0000
  17.500   1.1908   0.13708   0.13310  -0.0588   0.0099   1.0000
  17.750   1.1788   0.14484   0.14103  -0.0636   0.0098   1.0000
  18.000   1.1656   0.15324   0.14957  -0.0689   0.0098   1.0000
  18.250   1.1514   0.16222   0.15870  -0.0746   0.0099   1.0000
  18.500   1.1347   0.17237   0.16900  -0.0810   0.0100   1.0000
  18.750   1.1152   0.18417   0.18094  -0.0883   0.0102   1.0000
  19.000   1.0871   0.20050   0.19735  -0.0979   0.0105   1.0000
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