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RAF 32 AIRFOIL (raf32-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: RAF 32 AIRFOIL (raf32-il)
Reynolds number: 100,000
Max Cl/Cd: 56.26 at α=6.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-raf32-il-100000-n5.txt
Download as CSV file: xf-raf32-il-100000-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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.3172   0.09240   0.08743  -0.0703   0.9767   0.0411
  -9.500  -0.3163   0.08713   0.08218  -0.0744   0.9704   0.0424
  -9.250  -0.3204   0.08004   0.07511  -0.0808   0.9646   0.0438
  -9.000  -0.3442   0.06950   0.06463  -0.0897   0.9551   0.0447
  -8.750  -0.4095   0.04912   0.04385  -0.1103   0.9340   0.0427
  -8.500  -0.4141   0.04231   0.03638  -0.1153   0.9246   0.0447
  -8.250  -0.4028   0.03687   0.03003  -0.1187   0.9184   0.0475
  -8.000  -0.3774   0.03586   0.02903  -0.1196   0.9143   0.0499
  -7.750  -0.3601   0.03458   0.02752  -0.1192   0.9074   0.0530
  -7.500  -0.3335   0.03205   0.02430  -0.1210   0.9037   0.0576
  -7.250  -0.3016   0.03077   0.02298  -0.1229   0.9015   0.0615
  -7.000  -0.2879   0.02997   0.02199  -0.1210   0.8930   0.0649
  -6.750  -0.2585   0.02863   0.02015  -0.1221   0.8894   0.0700
  -6.500  -0.2261   0.02754   0.01909  -0.1237   0.8871   0.0744
  -6.250  -0.2059   0.02686   0.01822  -0.1227   0.8805   0.0786
  -6.000  -0.1789   0.02604   0.01705  -0.1228   0.8756   0.0828
  -5.750  -0.1476   0.02504   0.01609  -0.1240   0.8728   0.0873
  -5.500  -0.1128   0.02423   0.01513  -0.1255   0.8706   0.0918
  -5.250  -0.0942   0.02381   0.01453  -0.1240   0.8633   0.0956
  -5.000  -0.0658   0.02308   0.01375  -0.1243   0.8589   0.0996
  -4.750  -0.0325   0.02240   0.01302  -0.1255   0.8560   0.1037
  -4.500   0.0024   0.02177   0.01228  -0.1269   0.8538   0.1085
  -4.250   0.0188   0.02157   0.01201  -0.1249   0.8457   0.1130
  -4.000   0.0486   0.02105   0.01150  -0.1254   0.8417   0.1207
  -3.750   0.0824   0.02051   0.01092  -0.1266   0.8388   0.1306
  -3.500   0.1101   0.02012   0.01053  -0.1267   0.8343   0.1434
  -3.250   0.1312   0.01988   0.01036  -0.1256   0.8275   0.1623
  -3.000   0.1629   0.01945   0.01006  -0.1265   0.8240   0.1993
  -2.750   0.1978   0.01908   0.00976  -0.1278   0.8214   0.2446
  -2.500   0.2162   0.01913   0.00984  -0.1262   0.8137   0.2757
  -2.250   0.2452   0.01897   0.00971  -0.1264   0.8092   0.3064
  -2.000   0.2790   0.01871   0.00947  -0.1275   0.8061   0.3355
  -1.750   0.3042   0.01866   0.00946  -0.1271   0.8006   0.3646
  -1.500   0.3278   0.01859   0.00952  -0.1263   0.7943   0.4038
  -1.250   0.3592   0.01834   0.00942  -0.1269   0.7908   0.4510
  -1.000   0.3937   0.01807   0.00922  -0.1279   0.7880   0.4914
  -0.750   0.4081   0.01827   0.00951  -0.1255   0.7791   0.5216
  -0.500   0.4402   0.01808   0.00937  -0.1260   0.7752   0.5630
  -0.250   0.4753   0.01780   0.00915  -0.1271   0.7723   0.6073
   0.000   0.4893   0.01800   0.00946  -0.1245   0.7633   0.6447
   0.500   0.5469   0.01756   0.00927  -0.1241   0.7543   0.7531
   0.750   0.5732   0.01742   0.00939  -0.1235   0.7475   0.8491
   1.000   0.6200   0.01724   0.00918  -0.1273   0.7436   1.0000
   1.250   0.6483   0.01734   0.00919  -0.1274   0.7384   1.0000
   1.500   0.6696   0.01759   0.00938  -0.1263   0.7312   1.0000
   1.750   0.7023   0.01758   0.00928  -0.1272   0.7270   1.0000
   2.000   0.7243   0.01784   0.00951  -0.1262   0.7205   1.0000
   2.250   0.7498   0.01799   0.00963  -0.1258   0.7144   1.0000
   2.500   0.7838   0.01796   0.00955  -0.1268   0.7104   1.0000
   2.750   0.8010   0.01834   0.00993  -0.1250   0.7026   1.0000
   3.000   0.8296   0.01844   0.01000  -0.1251   0.6973   1.0000
   3.250   0.8618   0.01846   0.01001  -0.1258   0.6928   1.0000
   3.500   0.8783   0.01886   0.01045  -0.1239   0.6847   1.0000
   3.750   0.9104   0.01888   0.01047  -0.1246   0.6798   1.0000
   4.000   0.9312   0.01919   0.01082  -0.1234   0.6728   1.0000
   4.250   0.9568   0.01937   0.01102  -0.1229   0.6663   1.0000
   4.500   0.9908   0.01936   0.01103  -0.1239   0.6615   1.0000
   4.750   1.0054   0.01979   0.01154  -0.1216   0.6523   1.0000
   5.000   1.0393   0.01967   0.01142  -0.1224   0.6450   1.0000
   5.250   1.0573   0.01989   0.01170  -0.1205   0.6337   1.0000
   5.500   1.0781   0.02002   0.01187  -0.1190   0.6222   1.0000
   5.750   1.1097   0.01997   0.01183  -0.1194   0.6135   1.0000
   6.000   1.1239   0.02039   0.01236  -0.1170   0.6033   1.0000
   6.250   1.1488   0.02056   0.01260  -0.1164   0.5947   1.0000
   6.500   1.1691   0.02078   0.01289  -0.1149   0.5838   1.0000
   6.750   1.1835   0.02109   0.01329  -0.1124   0.5711   1.0000
   7.000   1.1979   0.02131   0.01356  -0.1098   0.5565   1.0000
   7.250   1.2111   0.02157   0.01387  -0.1071   0.5406   1.0000
   7.500   1.2239   0.02187   0.01421  -0.1043   0.5238   1.0000
   7.750   1.2365   0.02223   0.01462  -0.1016   0.5065   1.0000
   8.000   1.2494   0.02259   0.01498  -0.0990   0.4871   1.0000
   8.250   1.2579   0.02315   0.01555  -0.0958   0.4649   1.0000
   8.500   1.2683   0.02373   0.01609  -0.0930   0.4423   1.0000
   8.750   1.2772   0.02444   0.01678  -0.0901   0.4188   1.0000
   9.000   1.2847   0.02528   0.01759  -0.0872   0.3942   1.0000
   9.250   1.2893   0.02631   0.01857  -0.0840   0.3657   1.0000
   9.500   1.2899   0.02760   0.01973  -0.0806   0.3312   1.0000
   9.750   1.2866   0.02923   0.02115  -0.0769   0.2923   1.0000
  10.000   1.2812   0.03116   0.02284  -0.0734   0.2560   1.0000
  10.250   1.2764   0.03323   0.02472  -0.0703   0.2242   1.0000
  10.500   1.2738   0.03532   0.02667  -0.0677   0.1952   1.0000
  10.750   1.2720   0.03746   0.02872  -0.0653   0.1661   1.0000
  11.000   1.2689   0.03981   0.03093  -0.0631   0.1379   1.0000
  11.250   1.2665   0.04222   0.03321  -0.0611   0.1161   1.0000
  11.500   1.2647   0.04468   0.03559  -0.0594   0.1006   1.0000
  11.750   1.2644   0.04710   0.03798  -0.0578   0.0895   1.0000
  12.000   1.2643   0.04957   0.04046  -0.0564   0.0807   1.0000
  12.250   1.2626   0.05229   0.04316  -0.0551   0.0734   1.0000
  12.500   1.2644   0.05473   0.04572  -0.0541   0.0667   1.0000
  12.750   1.2634   0.05754   0.04856  -0.0531   0.0614   1.0000
  13.000   1.2650   0.06015   0.05130  -0.0522   0.0562   1.0000
  13.250   1.2628   0.06322   0.05437  -0.0515   0.0525   1.0000
  13.500   1.2665   0.06572   0.05705  -0.0508   0.0484   1.0000
  13.750   1.2680   0.06854   0.05996  -0.0503   0.0449   1.0000
  14.000   1.2670   0.07167   0.06311  -0.0500   0.0426   1.0000
  14.250   1.2710   0.07425   0.06585  -0.0495   0.0401   1.0000
  14.500   1.2744   0.07696   0.06870  -0.0491   0.0377   1.0000
  14.750   1.2765   0.07988   0.07172  -0.0490   0.0357   1.0000
  15.000   1.2781   0.08289   0.07481  -0.0490   0.0342   1.0000
  15.250   1.2796   0.08587   0.07784  -0.0488   0.0327   1.0000
  15.500   1.2844   0.08856   0.08071  -0.0486   0.0314   1.0000
  15.750   1.2876   0.09153   0.08386  -0.0487   0.0300   1.0000
  16.000   1.2896   0.09468   0.08717  -0.0489   0.0288   1.0000
  16.250   1.2914   0.09789   0.09050  -0.0493   0.0278   1.0000
  16.500   1.2927   0.10118   0.09391  -0.0498   0.0270   1.0000
  16.750   1.2937   0.10450   0.09731  -0.0504   0.0263   1.0000
  17.000   1.2952   0.10775   0.10063  -0.0509   0.0256   1.0000
  17.250   1.2929   0.11186   0.10496  -0.0520   0.0250   1.0000
  17.500   1.2872   0.11665   0.11001  -0.0537   0.0244   1.0000
  17.750   1.2805   0.12172   0.11532  -0.0557   0.0239   1.0000
  18.000   1.2721   0.12719   0.12102  -0.0581   0.0234   1.0000
  18.250   1.2624   0.13306   0.12713  -0.0611   0.0231   1.0000
  18.500   1.2507   0.13952   0.13381  -0.0645   0.0228   1.0000
  18.750   1.2365   0.14677   0.14128  -0.0688   0.0227   1.0000
  19.000   1.2186   0.15526   0.15000  -0.0741   0.0227   1.0000
  19.250   1.1940   0.16615   0.16112  -0.0812   0.0228   1.0000
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