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RAF 32 AIRFOIL (raf32-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: RAF 32 AIRFOIL (raf32-il)
Reynolds number: 200,000
Max Cl/Cd: 84.76 at α=5.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-raf32-il-200000-n5.txt
Download as CSV file: xf-raf32-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: RAF 32 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
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.5613   0.04395   0.03984  -0.1155   0.9638   0.0212
 -11.000  -0.5650   0.03657   0.03203  -0.1267   0.9521   0.0215
 -10.750  -0.5529   0.03310   0.02823  -0.1305   0.9451   0.0222
 -10.500  -0.5384   0.03045   0.02522  -0.1323   0.9385   0.0232
 -10.250  -0.5178   0.02831   0.02281  -0.1341   0.9334   0.0244
 -10.000  -0.4882   0.02708   0.02147  -0.1364   0.9308   0.0258
  -9.750  -0.4702   0.02603   0.02027  -0.1360   0.9240   0.0271
  -9.500  -0.4452   0.02462   0.01861  -0.1369   0.9198   0.0289
  -9.250  -0.4164   0.02340   0.01720  -0.1384   0.9171   0.0309
  -9.000  -0.3941   0.02298   0.01672  -0.1380   0.9113   0.0329
  -8.750  -0.3684   0.02221   0.01578  -0.1383   0.9067   0.0356
  -8.500  -0.3390   0.02129   0.01466  -0.1394   0.9036   0.0385
  -8.250  -0.3072   0.02088   0.01417  -0.1407   0.9009   0.0415
  -8.000  -0.2872   0.02043   0.01357  -0.1395   0.8939   0.0448
  -7.750  -0.2588   0.01976   0.01270  -0.1400   0.8900   0.0482
  -7.500  -0.2278   0.01928   0.01216  -0.1411   0.8871   0.0514
  -7.250  -0.2024   0.01888   0.01163  -0.1409   0.8820   0.0550
  -7.000  -0.1764   0.01853   0.01105  -0.1407   0.8766   0.0580
  -6.750  -0.1480   0.01783   0.01036  -0.1413   0.8727   0.0614
  -6.500  -0.1162   0.01738   0.00980  -0.1423   0.8698   0.0650
  -6.250  -0.0937   0.01707   0.00938  -0.1414   0.8635   0.0680
  -6.000  -0.0665   0.01661   0.00881  -0.1414   0.8586   0.0706
  -5.750  -0.0368   0.01603   0.00820  -0.1421   0.8548   0.0739
  -5.500  -0.0105   0.01567   0.00778  -0.1419   0.8498   0.0766
  -5.250   0.0148   0.01535   0.00739  -0.1415   0.8441   0.0794
  -5.000   0.0439   0.01502   0.00695  -0.1418   0.8399   0.0821
  -4.750   0.0734   0.01458   0.00646  -0.1423   0.8360   0.0848
  -4.500   0.0963   0.01429   0.00617  -0.1414   0.8294   0.0879
  -4.250   0.1243   0.01401   0.00582  -0.1415   0.8243   0.0917
  -4.000   0.1552   0.01374   0.00545  -0.1421   0.8206   0.0966
  -3.750   0.1783   0.01350   0.00525  -0.1413   0.8142   0.1044
  -3.500   0.2054   0.01325   0.00500  -0.1412   0.8088   0.1156
  -3.250   0.2352   0.01293   0.00472  -0.1417   0.8047   0.1385
  -3.000   0.2589   0.01271   0.00462  -0.1410   0.7981   0.1742
  -2.750   0.2858   0.01252   0.00451  -0.1409   0.7926   0.2112
  -2.500   0.3157   0.01237   0.00437  -0.1413   0.7884   0.2417
  -2.250   0.3396   0.01230   0.00436  -0.1406   0.7816   0.2638
  -2.000   0.3669   0.01221   0.00427  -0.1404   0.7760   0.2863
  -1.750   0.3958   0.01213   0.00418  -0.1406   0.7713   0.3088
  -1.500   0.4199   0.01206   0.00419  -0.1399   0.7644   0.3305
  -1.250   0.4474   0.01195   0.00413  -0.1399   0.7588   0.3617
  -1.000   0.4730   0.01184   0.00415  -0.1394   0.7527   0.3989
  -0.750   0.4982   0.01174   0.00416  -0.1389   0.7458   0.4366
  -0.500   0.5260   0.01163   0.00412  -0.1388   0.7403   0.4754
  -0.250   0.5494   0.01160   0.00419  -0.1379   0.7328   0.5110
   0.000   0.5764   0.01154   0.00419  -0.1376   0.7271   0.5471
   0.250   0.6013   0.01151   0.00424  -0.1370   0.7209   0.5818
   0.500   0.6263   0.01148   0.00429  -0.1363   0.7146   0.6161
   1.000   0.6765   0.01140   0.00441  -0.1350   0.7028   0.6903
   1.250   0.7018   0.01133   0.00445  -0.1343   0.6971   0.7362
   1.500   0.7280   0.01124   0.00449  -0.1338   0.6917   0.7963
   1.750   0.7771   0.01107   0.00457  -0.1382   0.6855   1.0000
   2.000   0.8041   0.01118   0.00461  -0.1380   0.6800   1.0000
   2.250   0.8295   0.01131   0.00471  -0.1376   0.6740   1.0000
   2.500   0.8547   0.01145   0.00482  -0.1371   0.6677   1.0000
   2.750   0.8822   0.01157   0.00489  -0.1370   0.6625   1.0000
   3.000   0.9060   0.01173   0.00506  -0.1363   0.6559   1.0000
   3.250   0.9316   0.01188   0.00519  -0.1358   0.6498   1.0000
   3.500   0.9574   0.01203   0.00532  -0.1354   0.6435   1.0000
   3.750   0.9809   0.01219   0.00549  -0.1346   0.6354   1.0000
   4.000   1.0056   0.01234   0.00561  -0.1339   0.6271   1.0000
   4.250   1.0285   0.01250   0.00578  -0.1330   0.6175   1.0000
   4.500   1.0514   0.01267   0.00596  -0.1320   0.6082   1.0000
   5.000   1.0951   0.01303   0.00632  -0.1296   0.5865   1.0000
   5.250   1.1160   0.01322   0.00652  -0.1282   0.5751   1.0000
   5.500   1.1363   0.01342   0.00672  -0.1267   0.5626   1.0000
   5.750   1.1561   0.01364   0.00694  -0.1251   0.5503   1.0000
   6.000   1.1749   0.01387   0.00720  -0.1234   0.5374   1.0000
   6.250   1.1928   0.01411   0.00746  -0.1215   0.5234   1.0000
   6.500   1.2091   0.01438   0.00773  -0.1193   0.5081   1.0000
   6.750   1.2234   0.01467   0.00802  -0.1167   0.4917   1.0000
   7.250   1.2449   0.01552   0.00872  -0.1103   0.4482   1.0000
   7.500   1.2536   0.01607   0.00920  -0.1070   0.4247   1.0000
   7.750   1.2635   0.01665   0.00972  -0.1039   0.4025   1.0000
   8.000   1.2701   0.01738   0.01035  -0.1005   0.3762   1.0000
   8.250   1.2734   0.01828   0.01111  -0.0966   0.3418   1.0000
   8.500   1.2724   0.01944   0.01207  -0.0924   0.3008   1.0000
   8.750   1.2693   0.02084   0.01323  -0.0881   0.2616   1.0000
   9.000   1.2680   0.02230   0.01451  -0.0844   0.2283   1.0000
   9.250   1.2705   0.02367   0.01576  -0.0813   0.2030   1.0000
   9.500   1.2738   0.02507   0.01706  -0.0786   0.1764   1.0000
   9.750   1.2759   0.02662   0.01847  -0.0759   0.1462   1.0000
  10.000   1.2767   0.02834   0.02003  -0.0732   0.1172   1.0000
  10.250   1.2781   0.03010   0.02166  -0.0707   0.0963   1.0000
  10.500   1.2824   0.03172   0.02325  -0.0687   0.0841   1.0000
  10.750   1.2874   0.03333   0.02485  -0.0668   0.0748   1.0000
  11.000   1.2939   0.03487   0.02643  -0.0651   0.0675   1.0000
  11.250   1.2995   0.03653   0.02812  -0.0635   0.0610   1.0000
  11.500   1.3053   0.03823   0.02985  -0.0620   0.0547   1.0000
  11.750   1.3120   0.03989   0.03159  -0.0606   0.0488   1.0000
  12.000   1.3170   0.04175   0.03347  -0.0593   0.0433   1.0000
  12.250   1.3227   0.04359   0.03541  -0.0580   0.0386   1.0000
  12.500   1.3272   0.04560   0.03744  -0.0568   0.0347   1.0000
  12.750   1.3300   0.04783   0.03972  -0.0557   0.0318   1.0000
  13.000   1.3346   0.04995   0.04194  -0.0547   0.0295   1.0000
  13.250   1.3373   0.05231   0.04437  -0.0538   0.0276   1.0000
  13.500   1.3383   0.05491   0.04703  -0.0530   0.0261   1.0000
  13.750   1.3394   0.05760   0.04980  -0.0522   0.0247   1.0000
  14.000   1.3420   0.06016   0.05248  -0.0516   0.0235   1.0000
  14.250   1.3440   0.06283   0.05526  -0.0512   0.0224   1.0000
  14.500   1.3452   0.06566   0.05820  -0.0508   0.0216   1.0000
  14.750   1.3440   0.06886   0.06146  -0.0505   0.0207   1.0000
  15.000   1.3422   0.07219   0.06487  -0.0504   0.0201   1.0000
  15.250   1.3445   0.07507   0.06790  -0.0503   0.0192   1.0000
  15.500   1.3452   0.07818   0.07113  -0.0503   0.0186   1.0000
  15.750   1.3455   0.08141   0.07447  -0.0505   0.0180   1.0000
  16.000   1.3454   0.08475   0.07792  -0.0507   0.0174   1.0000
  16.250   1.3449   0.08819   0.08145  -0.0512   0.0170   1.0000
  16.500   1.3433   0.09183   0.08518  -0.0517   0.0166   1.0000
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