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Supermarine 371-I (root) (supermarine371i-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: Supermarine 371-I (root) (supermarine371i-il)
Reynolds number: 100,000
Max Cl/Cd: 40.99 at α=5.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-supermarine371i-il-100000-n5.txt
Download as CSV file: xf-supermarine371i-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: Supermarine 371-I (root)                        
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -12.250  -0.6038   0.08904   0.08387  -0.0444   1.0000   0.0331
 -12.000  -0.6411   0.07707   0.07181  -0.0528   1.0000   0.0321
 -11.750  -0.6759   0.06884   0.06346  -0.0577   1.0000   0.0313
 -11.500  -0.7023   0.06338   0.05782  -0.0596   1.0000   0.0314
 -11.250  -0.7265   0.05881   0.05306  -0.0599   1.0000   0.0312
 -11.000  -0.7455   0.05534   0.04939  -0.0588   1.0000   0.0316
 -10.750  -0.7631   0.05221   0.04604  -0.0565   1.0000   0.0316
 -10.500  -0.7777   0.04966   0.04328  -0.0533   1.0000   0.0319
 -10.250  -0.7878   0.04720   0.04059  -0.0500   1.0000   0.0321
 -10.000  -0.7961   0.04492   0.03807  -0.0464   1.0000   0.0324
  -9.750  -0.8074   0.04326   0.03621  -0.0416   0.9998   0.0326
  -9.500  -0.7911   0.04006   0.03250  -0.0422   0.9854   0.0332
  -9.250  -0.7699   0.03730   0.02925  -0.0430   0.9760   0.0340
  -9.000  -0.7456   0.03505   0.02652  -0.0438   0.9679   0.0349
  -8.750  -0.7184   0.03279   0.02414  -0.0452   0.9618   0.0367
  -8.500  -0.6915   0.03119   0.02240  -0.0462   0.9549   0.0385
  -8.250  -0.6623   0.02956   0.02055  -0.0472   0.9491   0.0403
  -8.000  -0.6329   0.02806   0.01883  -0.0481   0.9437   0.0420
  -7.750  -0.6052   0.02681   0.01738  -0.0485   0.9375   0.0438
  -7.500  -0.5784   0.02538   0.01591  -0.0491   0.9327   0.0464
  -7.250  -0.5567   0.02437   0.01486  -0.0488   0.9261   0.0499
  -7.000  -0.5338   0.02347   0.01382  -0.0484   0.9202   0.0539
  -6.750  -0.5129   0.02251   0.01283  -0.0477   0.9148   0.0578
  -6.500  -0.4945   0.02180   0.01212  -0.0465   0.9080   0.0640
  -6.250  -0.4723   0.02122   0.01167  -0.0460   0.9029   0.0734
  -6.000  -0.4502   0.02084   0.01127  -0.0453   0.8977   0.0912
  -5.750  -0.4291   0.02043   0.01077  -0.0443   0.8925   0.1127
  -5.500  -0.4084   0.01982   0.01019  -0.0435   0.8883   0.1321
  -5.250  -0.3876   0.01931   0.00976  -0.0427   0.8843   0.1532
  -5.000  -0.3689   0.01888   0.00943  -0.0415   0.8793   0.1791
  -4.500  -0.3293   0.01783   0.00875  -0.0394   0.8716   0.2694
  -4.250  -0.3178   0.01715   0.00853  -0.0370   0.8664   0.3611
  -4.000  -0.3063   0.01649   0.00846  -0.0342   0.8621   0.4812
  -3.750  -0.2845   0.01653   0.00912  -0.0319   0.8593   0.5976
  -3.500  -0.2631   0.01664   0.00912  -0.0305   0.8566   0.6587
  -3.250  -0.2426   0.01684   0.00927  -0.0289   0.8526   0.6875
  -3.000  -0.2208   0.01706   0.00941  -0.0276   0.8486   0.7090
  -2.750  -0.1988   0.01724   0.00950  -0.0263   0.8454   0.7296
  -2.500  -0.1738   0.01747   0.00966  -0.0253   0.8430   0.7468
  -2.250  -0.1484   0.01766   0.00976  -0.0245   0.8410   0.7618
  -2.000  -0.1276   0.01792   0.00999  -0.0231   0.8372   0.7753
  -1.750  -0.1038   0.01817   0.01021  -0.0221   0.8335   0.7860
  -1.500  -0.0804   0.01829   0.01026  -0.0213   0.8305   0.7949
  -1.250  -0.0545   0.01843   0.01035  -0.0208   0.8282   0.8033
  -1.000  -0.0277   0.01853   0.01040  -0.0205   0.8261   0.8115
  -0.750  -0.0066   0.01872   0.01056  -0.0193   0.8224   0.8204
  -0.500   0.0147   0.01892   0.01075  -0.0183   0.8185   0.8272
  -0.250   0.0389   0.01904   0.01085  -0.0177   0.8152   0.8339
   0.000   0.0638   0.01907   0.01084  -0.0173   0.8123   0.8398
   0.250   0.0942   0.01912   0.01088  -0.0177   0.8101   0.8444
   0.500   0.1093   0.01935   0.01112  -0.0157   0.8041   0.8530
   0.750   0.1361   0.01951   0.01131  -0.0154   0.8000   0.8606
   1.000   0.1619   0.01957   0.01139  -0.0148   0.7967   0.8705
   1.250   0.1962   0.01963   0.01149  -0.0156   0.7944   0.8777
   1.500   0.2103   0.01991   0.01182  -0.0136   0.7875   0.8865
   1.750   0.2404   0.01999   0.01195  -0.0140   0.7834   0.8914
   2.000   0.2708   0.01992   0.01191  -0.0145   0.7802   0.8955
   2.250   0.2891   0.02003   0.01207  -0.0132   0.7727   0.9009
   2.500   0.3220   0.01989   0.01200  -0.0140   0.7669   0.9039
   2.750   0.3533   0.01975   0.01192  -0.0144   0.7610   0.9076
   3.000   0.3756   0.01975   0.01200  -0.0136   0.7530   0.9134
   3.250   0.4117   0.01940   0.01172  -0.0146   0.7482   0.9163
   3.500   0.4375   0.01936   0.01179  -0.0143   0.7370   0.9207
   3.750   0.4669   0.01911   0.01163  -0.0143   0.7273   0.9253
   4.000   0.5002   0.01855   0.01116  -0.0145   0.7177   0.9296
   4.250   0.5321   0.01808   0.01078  -0.0146   0.7024   0.9334
   4.500   0.5605   0.01780   0.01063  -0.0145   0.6849   0.9386
   4.750   0.5851   0.01762   0.01061  -0.0138   0.6663   0.9460
   5.000   0.6171   0.01733   0.01045  -0.0143   0.6405   0.9509
   5.250   0.6414   0.01722   0.01048  -0.0138   0.6003   0.9597
   5.500   0.6779   0.01661   0.00958  -0.0141   0.5156   0.9631
   5.750   0.7017   0.01712   0.00945  -0.0133   0.4106   0.9703
   6.000   0.7213   0.01822   0.01002  -0.0129   0.3169   0.9795
   6.250   0.7422   0.01935   0.01073  -0.0131   0.2382   0.9905
   6.500   0.7574   0.02029   0.01136  -0.0121   0.1872   1.0000
   6.750   0.7554   0.02083   0.01174  -0.0074   0.1614   1.0000
   7.000   0.7590   0.02146   0.01222  -0.0037   0.1380   1.0000
   7.250   0.7661   0.02220   0.01282  -0.0008   0.1192   1.0000
   7.500   0.7744   0.02297   0.01348   0.0020   0.1038   1.0000
   7.750   0.7840   0.02375   0.01422   0.0046   0.0915   1.0000
   8.000   0.7948   0.02457   0.01502   0.0068   0.0809   1.0000
   8.250   0.8051   0.02551   0.01593   0.0090   0.0731   1.0000
   8.500   0.8175   0.02640   0.01684   0.0108   0.0657   1.0000
   8.750   0.8293   0.02745   0.01789   0.0127   0.0604   1.0000
   9.000   0.8427   0.02849   0.01899   0.0143   0.0559   1.0000
   9.250   0.8547   0.02970   0.02017   0.0158   0.0524   1.0000
   9.500   0.8709   0.03084   0.02144   0.0171   0.0488   1.0000
   9.750   0.8862   0.03196   0.02265   0.0183   0.0453   1.0000
  10.000   0.9006   0.03323   0.02393   0.0194   0.0429   1.0000
  10.250   0.9188   0.03482   0.02554   0.0202   0.0411   1.0000
  10.500   0.9381   0.03636   0.02732   0.0211   0.0393   1.0000
  10.750   0.9539   0.03791   0.02907   0.0221   0.0373   1.0000
  11.000   0.9662   0.03937   0.03068   0.0232   0.0354   1.0000
  11.250   0.9776   0.04092   0.03230   0.0244   0.0340   1.0000
  11.500   0.9910   0.04303   0.03446   0.0252   0.0329   1.0000
  11.750   0.9995   0.04541   0.03714   0.0265   0.0321   1.0000
  12.000   1.0028   0.04793   0.03999   0.0281   0.0314   1.0000
  12.250   1.0012   0.05063   0.04301   0.0298   0.0306   1.0000
  12.500   0.9966   0.05340   0.04607   0.0312   0.0297   1.0000
  12.750   0.9907   0.05630   0.04922   0.0324   0.0291   1.0000
  13.000   0.9827   0.05938   0.05252   0.0333   0.0284   1.0000
  13.250   0.9726   0.06278   0.05613   0.0337   0.0278   1.0000
  13.500   0.9593   0.06675   0.06032   0.0337   0.0275   1.0000
  13.750   0.9438   0.07115   0.06493   0.0331   0.0273   1.0000
  14.000   0.9221   0.07675   0.07078   0.0316   0.0273   1.0000
  14.250   0.8947   0.08375   0.07802   0.0286   0.0274   1.0000
  14.500   0.8426   0.09672   0.09132   0.0209   0.0284   1.0000
  14.750   0.7726   0.11880   0.11359   0.0068   0.0306   1.0000
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