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RAF 32 MOD AIRFOIL (raf32md-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: RAF 32 MOD AIRFOIL (raf32md-il)
Reynolds number: 500,000
Max Cl/Cd: 120.81 at α=4.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-raf32md-il-500000.txt
Download as CSV file: xf-raf32md-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.3758   0.08363   0.08145  -0.0542   0.9945   0.0283
  -8.750  -0.4219   0.05022   0.04792  -0.0896   0.9818   0.0217
  -8.500  -0.4215   0.03712   0.03422  -0.1060   0.9723   0.0211
  -8.250  -0.4098   0.03056   0.02699  -0.1105   0.9650   0.0214
  -8.000  -0.3880   0.02581   0.02158  -0.1137   0.9609   0.0225
  -7.750  -0.3560   0.02441   0.02018  -0.1161   0.9594   0.0237
  -7.500  -0.3219   0.02331   0.01897  -0.1184   0.9582   0.0251
  -7.250  -0.2936   0.02145   0.01681  -0.1196   0.9549   0.0262
  -7.000  -0.2687   0.01996   0.01504  -0.1196   0.9494   0.0271
  -6.750  -0.2355   0.01983   0.01470  -0.1207   0.9466   0.0283
  -6.500  -0.2081   0.01654   0.01113  -0.1221   0.9439   0.0303
  -6.250  -0.1820   0.01564   0.01014  -0.1220   0.9389   0.0315
  -6.000  -0.1546   0.01482   0.00923  -0.1221   0.9339   0.0326
  -5.750  -0.1240   0.01408   0.00838  -0.1228   0.9303   0.0341
  -5.500  -0.0956   0.01353   0.00772  -0.1229   0.9257   0.0355
  -5.250  -0.0694   0.01303   0.00713  -0.1225   0.9196   0.0363
  -5.000  -0.0410   0.01217   0.00616  -0.1227   0.9152   0.0372
  -4.750  -0.0167   0.01128   0.00521  -0.1222   0.9090   0.0391
  -4.500   0.0100   0.01079   0.00467  -0.1219   0.9031   0.0406
  -4.250   0.0388   0.01038   0.00420  -0.1221   0.8985   0.0420
  -4.000   0.0638   0.01006   0.00383  -0.1215   0.8914   0.0434
  -3.750   0.0920   0.00976   0.00346  -0.1215   0.8860   0.0450
  -3.500   0.1187   0.00955   0.00319  -0.1212   0.8796   0.0467
  -3.250   0.1457   0.00924   0.00283  -0.1209   0.8733   0.0505
  -3.000   0.1735   0.00902   0.00258  -0.1208   0.8676   0.0564
  -2.750   0.1991   0.00865   0.00240  -0.1204   0.8606   0.1036
  -2.500   0.2268   0.00830   0.00222  -0.1205   0.8551   0.1638
  -2.250   0.2514   0.00795   0.00217  -0.1200   0.8476   0.2494
  -2.000   0.2790   0.00779   0.00210  -0.1200   0.8416   0.3012
  -1.750   0.3053   0.00769   0.00206  -0.1196   0.8344   0.3338
  -1.500   0.3326   0.00759   0.00200  -0.1195   0.8278   0.3658
  -1.250   0.3590   0.00745   0.00196  -0.1192   0.8208   0.4034
  -1.000   0.3853   0.00728   0.00192  -0.1188   0.8137   0.4519
  -0.750   0.4107   0.00709   0.00199  -0.1184   0.8066   0.5426
  -0.500   0.4369   0.00701   0.00200  -0.1179   0.7991   0.5986
  -0.250   0.4627   0.00693   0.00202  -0.1174   0.7917   0.6424
   0.000   0.4879   0.00681   0.00203  -0.1167   0.7840   0.6901
   0.250   0.5126   0.00669   0.00207  -0.1158   0.7761   0.7427
   0.500   0.5365   0.00653   0.00208  -0.1148   0.7683   0.8072
   0.750   0.5926   0.00622   0.00207  -0.1207   0.7609   0.9985
   1.000   0.6195   0.00629   0.00207  -0.1205   0.7527   1.0000
   1.250   0.6448   0.00635   0.00210  -0.1199   0.7434   1.0000
   1.500   0.6709   0.00643   0.00212  -0.1194   0.7348   1.0000
   1.750   0.6964   0.00651   0.00217  -0.1189   0.7252   1.0000
   2.000   0.7221   0.00659   0.00222  -0.1184   0.7156   1.0000
   2.250   0.7477   0.00669   0.00226  -0.1178   0.7053   1.0000
   2.500   0.7728   0.00679   0.00231  -0.1172   0.6933   1.0000
   2.750   0.7976   0.00689   0.00239  -0.1164   0.6802   1.0000
   3.000   0.8217   0.00701   0.00245  -0.1156   0.6643   1.0000
   3.250   0.8456   0.00715   0.00253  -0.1147   0.6476   1.0000
   3.500   0.8695   0.00729   0.00263  -0.1138   0.6307   1.0000
   3.750   0.8939   0.00745   0.00275  -0.1130   0.6163   1.0000
   4.000   0.9178   0.00761   0.00288  -0.1122   0.6003   1.0000
   4.250   0.9411   0.00779   0.00302  -0.1112   0.5811   1.0000
   4.500   0.9638   0.00801   0.00318  -0.1101   0.5613   1.0000
   4.750   0.9868   0.00821   0.00335  -0.1091   0.5410   1.0000
   5.000   1.0085   0.00847   0.00354  -0.1079   0.5169   1.0000
   5.250   1.0281   0.00882   0.00377  -0.1062   0.4807   1.0000
   5.500   1.0447   0.00933   0.00406  -0.1041   0.4305   1.0000
   5.750   1.0584   0.01004   0.00446  -0.1015   0.3657   1.0000
   6.000   1.0689   0.01101   0.00499  -0.0985   0.2850   1.0000
   6.250   1.0777   0.01214   0.00566  -0.0953   0.2009   1.0000
   6.500   1.0891   0.01310   0.00629  -0.0926   0.1424   1.0000
   6.750   1.1004   0.01405   0.00694  -0.0898   0.0907   1.0000
   7.000   1.1144   0.01474   0.00750  -0.0875   0.0698   1.0000
   7.250   1.1289   0.01533   0.00805  -0.0851   0.0592   1.0000
   7.500   1.1447   0.01584   0.00856  -0.0831   0.0519   1.0000
   7.750   1.1599   0.01640   0.00914  -0.0809   0.0443   1.0000
   8.000   1.1727   0.01711   0.00983  -0.0784   0.0368   1.0000
   8.250   1.1869   0.01775   0.01044  -0.0762   0.0312   1.0000
   8.500   1.1999   0.01846   0.01120  -0.0738   0.0276   1.0000
   8.750   1.2138   0.01913   0.01190  -0.0716   0.0251   1.0000
   9.000   1.2198   0.02030   0.01310  -0.0684   0.0229   1.0000
   9.250   1.2336   0.02100   0.01388  -0.0664   0.0219   1.0000
   9.500   1.2460   0.02181   0.01477  -0.0642   0.0207   1.0000
   9.750   1.2589   0.02260   0.01558  -0.0623   0.0192   1.0000
  10.000   1.2657   0.02384   0.01687  -0.0597   0.0183   1.0000
  10.250   1.2687   0.02544   0.01856  -0.0567   0.0174   1.0000
  10.500   1.2800   0.02647   0.01967  -0.0548   0.0169   1.0000
  10.750   1.2893   0.02771   0.02100  -0.0527   0.0165   1.0000
  11.000   1.2992   0.02891   0.02231  -0.0509   0.0158   1.0000
  11.250   1.3082   0.03025   0.02372  -0.0491   0.0153   1.0000
  11.500   1.3171   0.03162   0.02516  -0.0474   0.0148   1.0000
  11.750   1.3250   0.03315   0.02675  -0.0456   0.0144   1.0000
  12.000   1.3310   0.03498   0.02865  -0.0439   0.0139   1.0000
  12.250   1.3359   0.03761   0.03141  -0.0419   0.0133   1.0000
  12.500   1.3444   0.03906   0.03300  -0.0406   0.0131   1.0000
  12.750   1.3520   0.04068   0.03476  -0.0392   0.0127   1.0000
  13.000   1.3585   0.04264   0.03687  -0.0379   0.0124   1.0000
  13.250   1.3636   0.04476   0.03914  -0.0366   0.0121   1.0000
  13.500   1.3677   0.04696   0.04148  -0.0354   0.0118   1.0000
  13.750   1.3702   0.04940   0.04407  -0.0343   0.0116   1.0000
  14.000   1.3714   0.05197   0.04678  -0.0333   0.0114   1.0000
  14.250   1.3703   0.05495   0.04994  -0.0325   0.0113   1.0000
  14.500   1.3684   0.05793   0.05306  -0.0319   0.0110   1.0000
  14.750   1.3650   0.06121   0.05649  -0.0316   0.0109   1.0000
  15.000   1.3599   0.06484   0.06027  -0.0315   0.0108   1.0000
  15.250   1.3530   0.06886   0.06445  -0.0317   0.0107   1.0000
  15.500   1.3439   0.07338   0.06914  -0.0323   0.0106   1.0000
  15.750   1.3333   0.07826   0.07420  -0.0334   0.0105   1.0000
  16.000   1.3206   0.08372   0.07984  -0.0349   0.0105   1.0000
  16.250   1.3052   0.08992   0.08624  -0.0371   0.0105   1.0000
  16.500   1.2889   0.09653   0.09304  -0.0399   0.0104   1.0000
  16.750   1.2696   0.10413   0.10086  -0.0435   0.0105   1.0000
  17.000   1.2497   0.11227   0.10919  -0.0479   0.0105   1.0000
  17.250   1.2223   0.12275   0.11993  -0.0541   0.0106   1.0000
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