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RAF 32 MOD AIRFOIL (raf32md-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: RAF 32 MOD AIRFOIL (raf32md-il)
Reynolds number: 200,000
Max Cl/Cd: 83.79 at α=4.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-raf32md-il-200000-n5.txt
Download as CSV file: xf-raf32md-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: RAF 32 MOD AIRFOIL                              
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.3926   0.09621   0.09271  -0.0432   1.0000   0.0187
  -9.500  -0.3999   0.09353   0.09009  -0.0423   1.0000   0.0192
  -9.250  -0.3990   0.08905   0.08564  -0.0452   0.9981   0.0197
  -9.000  -0.3943   0.08260   0.07921  -0.0515   0.9937   0.0204
  -8.750  -0.3928   0.07529   0.07192  -0.0589   0.9876   0.0206
  -8.500  -0.3971   0.06632   0.06298  -0.0688   0.9783   0.0206
  -8.250  -0.4214   0.03847   0.03432  -0.1015   0.9592   0.0204
  -8.000  -0.4085   0.03229   0.02737  -0.1057   0.9517   0.0216
  -7.750  -0.3822   0.02935   0.02373  -0.1082   0.9477   0.0231
  -7.500  -0.3585   0.02667   0.02086  -0.1097   0.9436   0.0246
  -7.250  -0.3331   0.02534   0.01934  -0.1104   0.9385   0.0259
  -7.000  -0.3030   0.02369   0.01738  -0.1119   0.9355   0.0275
  -6.750  -0.2742   0.02250   0.01588  -0.1128   0.9318   0.0297
  -6.500  -0.2484   0.02155   0.01464  -0.1127   0.9262   0.0312
  -6.000  -0.1886   0.01865   0.01136  -0.1148   0.9199   0.0349
  -5.750  -0.1648   0.01791   0.01052  -0.1142   0.9134   0.0366
  -5.500  -0.1344   0.01707   0.00955  -0.1149   0.9096   0.0380
  -5.250  -0.1020   0.01635   0.00870  -0.1160   0.9069   0.0400
  -5.000  -0.0785   0.01584   0.00809  -0.1152   0.8999   0.0415
  -4.750  -0.0486   0.01525   0.00738  -0.1157   0.8955   0.0425
  -4.500  -0.0170   0.01460   0.00665  -0.1166   0.8923   0.0436
  -4.250   0.0069   0.01413   0.00613  -0.1159   0.8851   0.0452
  -4.000   0.0365   0.01370   0.00563  -0.1163   0.8803   0.0474
  -3.750   0.0676   0.01332   0.00518  -0.1170   0.8763   0.0510
  -3.500   0.0930   0.01307   0.00486  -0.1165   0.8693   0.0542
  -3.250   0.1229   0.01271   0.00451  -0.1169   0.8644   0.0621
  -3.000   0.1507   0.01237   0.00425  -0.1170   0.8587   0.0902
  -2.750   0.1780   0.01209   0.00403  -0.1169   0.8523   0.1228
  -2.500   0.2081   0.01173   0.00379  -0.1175   0.8477   0.1648
  -2.250   0.2330   0.01147   0.00370  -0.1170   0.8403   0.2170
  -2.000   0.2616   0.01123   0.00360  -0.1172   0.8346   0.2746
  -1.750   0.2888   0.01109   0.00352  -0.1171   0.8281   0.3118
  -1.500   0.3158   0.01092   0.00345  -0.1169   0.8213   0.3550
  -1.250   0.3435   0.01069   0.00338  -0.1169   0.8154   0.4080
  -1.000   0.3681   0.01046   0.00341  -0.1163   0.8078   0.4744
  -0.500   0.4204   0.01023   0.00344  -0.1154   0.7939   0.5995
  -0.250   0.4472   0.01007   0.00340  -0.1149   0.7876   0.6519
   0.000   0.4707   0.00993   0.00345  -0.1138   0.7794   0.7050
   0.250   0.4972   0.00977   0.00342  -0.1132   0.7728   0.7633
   0.500   0.5234   0.00961   0.00345  -0.1126   0.7647   0.8341
   0.750   0.5757   0.00944   0.00336  -0.1176   0.7583   1.0000
   1.000   0.6013   0.00953   0.00340  -0.1171   0.7495   1.0000
   1.250   0.6287   0.00960   0.00340  -0.1169   0.7419   1.0000
   1.500   0.6542   0.00969   0.00346  -0.1165   0.7327   1.0000
   1.750   0.6807   0.00979   0.00352  -0.1161   0.7243   1.0000
   2.000   0.7070   0.00988   0.00358  -0.1158   0.7154   1.0000
   2.250   0.7329   0.00999   0.00367  -0.1153   0.7062   1.0000
   2.500   0.7596   0.01010   0.00374  -0.1150   0.6975   1.0000
   2.750   0.7849   0.01022   0.00387  -0.1145   0.6875   1.0000
   3.000   0.8108   0.01035   0.00399  -0.1140   0.6779   1.0000
   3.500   0.8617   0.01062   0.00424  -0.1129   0.6552   1.0000
   3.750   0.8859   0.01078   0.00435  -0.1120   0.6392   1.0000
   4.000   0.9087   0.01095   0.00448  -0.1109   0.6179   1.0000
   4.250   0.9312   0.01116   0.00463  -0.1097   0.5956   1.0000
   4.500   0.9535   0.01138   0.00480  -0.1085   0.5734   1.0000
   4.750   0.9753   0.01164   0.00500  -0.1072   0.5499   1.0000
   5.000   0.9967   0.01191   0.00524  -0.1059   0.5257   1.0000
   5.250   1.0163   0.01226   0.00550  -0.1043   0.4944   1.0000
   5.500   1.0346   0.01266   0.00579  -0.1024   0.4600   1.0000
   5.750   1.0512   0.01316   0.00614  -0.1003   0.4192   1.0000
   6.000   1.0657   0.01377   0.00656  -0.0979   0.3733   1.0000
   6.250   1.0775   0.01453   0.00710  -0.0951   0.3201   1.0000
   6.500   1.0864   0.01550   0.00775  -0.0919   0.2585   1.0000
   6.750   1.0927   0.01665   0.00854  -0.0885   0.1946   1.0000
   7.000   1.0992   0.01773   0.00933  -0.0851   0.1454   1.0000
   7.250   1.1071   0.01876   0.01011  -0.0820   0.1039   1.0000
   7.500   1.1169   0.01970   0.01089  -0.0792   0.0802   1.0000
   7.750   1.1295   0.02050   0.01166  -0.0769   0.0683   1.0000
   8.000   1.1428   0.02125   0.01247  -0.0748   0.0600   1.0000
   8.250   1.1550   0.02210   0.01332  -0.0726   0.0524   1.0000
   8.500   1.1686   0.02287   0.01417  -0.0706   0.0458   1.0000
   8.750   1.1797   0.02383   0.01511  -0.0684   0.0391   1.0000
   9.000   1.1923   0.02470   0.01604  -0.0664   0.0327   1.0000
   9.250   1.2030   0.02574   0.01712  -0.0643   0.0283   1.0000
   9.500   1.2131   0.02683   0.01828  -0.0622   0.0250   1.0000
   9.750   1.2210   0.02812   0.01962  -0.0599   0.0227   1.0000
  10.000   1.2310   0.02929   0.02089  -0.0580   0.0206   1.0000
  10.250   1.2401   0.03056   0.02224  -0.0561   0.0190   1.0000
  10.500   1.2469   0.03205   0.02380  -0.0541   0.0177   1.0000
  10.750   1.2505   0.03389   0.02572  -0.0519   0.0168   1.0000
  11.000   1.2577   0.03548   0.02745  -0.0501   0.0161   1.0000
  11.250   1.2642   0.03722   0.02932  -0.0484   0.0155   1.0000
  11.500   1.2710   0.03897   0.03120  -0.0468   0.0148   1.0000
  11.750   1.2777   0.04076   0.03311  -0.0453   0.0141   1.0000
  12.000   1.2842   0.04259   0.03508  -0.0440   0.0134   1.0000
  12.250   1.2894   0.04456   0.03715  -0.0428   0.0129   1.0000
  12.500   1.2919   0.04694   0.03962  -0.0416   0.0123   1.0000
  12.750   1.2936   0.04963   0.04243  -0.0403   0.0119   1.0000
  13.000   1.2982   0.05197   0.04497  -0.0392   0.0117   1.0000
  13.250   1.3015   0.05455   0.04775  -0.0383   0.0114   1.0000
  13.500   1.3034   0.05734   0.05074  -0.0374   0.0112   1.0000
  13.750   1.3037   0.06038   0.05399  -0.0368   0.0110   1.0000
  14.000   1.3020   0.06371   0.05754  -0.0363   0.0108   1.0000
  14.250   1.2984   0.06738   0.06143  -0.0361   0.0106   1.0000
  14.500   1.2930   0.07136   0.06564  -0.0362   0.0104   1.0000
  14.750   1.2859   0.07565   0.07014  -0.0367   0.0102   1.0000
  15.000   1.2770   0.08041   0.07513  -0.0377   0.0101   1.0000
  15.250   1.2675   0.08539   0.08032  -0.0391   0.0099   1.0000
  15.500   1.2566   0.09083   0.08595  -0.0409   0.0097   1.0000
  15.750   1.2422   0.09718   0.09253  -0.0434   0.0097   1.0000
  16.000   1.2298   0.10342   0.09896  -0.0464   0.0096   1.0000
  16.250   1.2117   0.11122   0.10699  -0.0503   0.0096   1.0000
  16.500   1.1949   0.11917   0.11514  -0.0548   0.0096   1.0000
  16.750   1.1712   0.12934   0.12556  -0.0609   0.0097   1.0000
  17.000   1.1429   0.14175   0.13820  -0.0688   0.0099   1.0000
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