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RAF 32 AIRFOIL (raf32-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: RAF 32 AIRFOIL (raf32-il)
Reynolds number: 1,000,000
Max Cl/Cd: 152.3 at α=4.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-raf32-il-1000000.txt
Download as CSV file: xf-raf32-il-1000000.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 =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -15.750  -0.6923   0.09299   0.09079  -0.0699   1.0000   0.0146
 -15.500  -0.7401   0.08237   0.08005  -0.0749   1.0000   0.0144
 -15.250  -0.7875   0.07306   0.07063  -0.0790   1.0000   0.0144
 -15.000  -0.8357   0.06475   0.06221  -0.0820   1.0000   0.0142
 -14.750  -0.8654   0.05470   0.05199  -0.0915   0.9983   0.0141
 -14.500  -0.8878   0.04391   0.04100  -0.1041   0.9950   0.0141
 -14.250  -0.8969   0.03427   0.03113  -0.1176   0.9900   0.0141
 -14.000  -0.8862   0.02762   0.02422  -0.1310   0.9846   0.0144
 -13.750  -0.8662   0.02544   0.02191  -0.1342   0.9810   0.0147
 -13.500  -0.8452   0.02392   0.02029  -0.1359   0.9770   0.0150
 -13.250  -0.8186   0.02261   0.01887  -0.1381   0.9748   0.0155
 -13.000  -0.7901   0.02138   0.01753  -0.1404   0.9733   0.0159
 -12.750  -0.7593   0.02031   0.01634  -0.1426   0.9722   0.0164
 -12.500  -0.7263   0.01934   0.01525  -0.1451   0.9711   0.0167
 -12.250  -0.7090   0.01797   0.01378  -0.1449   0.9643   0.0175
 -12.000  -0.6791   0.01714   0.01289  -0.1464   0.9612   0.0182
 -11.750  -0.6480   0.01640   0.01206  -0.1480   0.9587   0.0189
 -11.500  -0.6217   0.01585   0.01144  -0.1483   0.9542   0.0196
 -11.250  -0.5966   0.01537   0.01087  -0.1482   0.9487   0.0201
 -11.000  -0.5701   0.01442   0.00983  -0.1490   0.9442   0.0212
 -10.750  -0.5463   0.01391   0.00927  -0.1487   0.9382   0.0221
 -10.500  -0.5208   0.01348   0.00877  -0.1486   0.9324   0.0230
 -10.000  -0.4706   0.01255   0.00770  -0.1482   0.9204   0.0253
  -9.750  -0.4437   0.01221   0.00732  -0.1483   0.9147   0.0267
  -9.500  -0.4178   0.01195   0.00700  -0.1481   0.9089   0.0281
  -9.250  -0.3930   0.01157   0.00656  -0.1477   0.9025   0.0296
  -8.750  -0.3404   0.01111   0.00604  -0.1473   0.8909   0.0332
  -8.500  -0.3142   0.01085   0.00570  -0.1471   0.8849   0.0349
  -8.250  -0.2875   0.01067   0.00552  -0.1470   0.8795   0.0371
  -8.000  -0.2608   0.01056   0.00539  -0.1467   0.8737   0.0390
  -7.750  -0.2331   0.01050   0.00525  -0.1467   0.8685   0.0402
  -7.500  -0.2081   0.01013   0.00486  -0.1463   0.8632   0.0426
  -7.250  -0.1812   0.01004   0.00476  -0.1461   0.8576   0.0446
  -7.000  -0.1538   0.00995   0.00462  -0.1460   0.8523   0.0463
  -6.750  -0.1265   0.00989   0.00451  -0.1459   0.8472   0.0474
  -6.500  -0.1017   0.00951   0.00409  -0.1454   0.8417   0.0498
  -6.250  -0.0748   0.00935   0.00390  -0.1452   0.8367   0.0518
  -6.000  -0.0479   0.00922   0.00375  -0.1451   0.8319   0.0535
  -5.750  -0.0212   0.00910   0.00359  -0.1448   0.8266   0.0551
  -5.500   0.0061   0.00903   0.00346  -0.1447   0.8214   0.0561
  -5.250   0.0320   0.00874   0.00312  -0.1443   0.8163   0.0585
  -5.000   0.0583   0.00853   0.00291  -0.1440   0.8110   0.0608
  -4.750   0.0852   0.00841   0.00274  -0.1438   0.8059   0.0628
  -4.500   0.1123   0.00830   0.00260  -0.1436   0.8008   0.0646
  -4.250   0.1391   0.00820   0.00247  -0.1434   0.7952   0.0661
  -4.000   0.1659   0.00805   0.00227  -0.1431   0.7896   0.0686
  -3.750   0.1925   0.00790   0.00211  -0.1429   0.7843   0.0723
  -3.500   0.2193   0.00778   0.00199  -0.1426   0.7782   0.0760
  -3.250   0.2461   0.00770   0.00186  -0.1423   0.7722   0.0804
  -3.000   0.2726   0.00754   0.00174  -0.1420   0.7656   0.0913
  -2.750   0.2978   0.00728   0.00160  -0.1416   0.7581   0.1324
  -2.500   0.3232   0.00702   0.00152  -0.1412   0.7508   0.1882
  -2.250   0.3493   0.00689   0.00147  -0.1408   0.7434   0.2228
  -2.000   0.3759   0.00683   0.00144  -0.1405   0.7369   0.2463
  -1.750   0.4025   0.00677   0.00142  -0.1402   0.7296   0.2660
  -1.500   0.4289   0.00674   0.00140  -0.1399   0.7228   0.2833
  -1.250   0.4557   0.00670   0.00139  -0.1396   0.7155   0.2998
  -0.750   0.5087   0.00665   0.00138  -0.1390   0.7016   0.3352
  -0.500   0.5347   0.00663   0.00138  -0.1386   0.6944   0.3583
  -0.250   0.5610   0.00656   0.00140  -0.1383   0.6879   0.3929
   0.000   0.5869   0.00651   0.00143  -0.1379   0.6812   0.4301
   0.250   0.6126   0.00646   0.00147  -0.1374   0.6751   0.4748
   0.500   0.6386   0.00641   0.00153  -0.1371   0.6687   0.5178
   0.750   0.6639   0.00640   0.00159  -0.1365   0.6625   0.5631
   1.000   0.6902   0.00637   0.00165  -0.1362   0.6571   0.5965
   1.250   0.7162   0.00637   0.00171  -0.1357   0.6513   0.6233
   1.500   0.7412   0.00640   0.00178  -0.1351   0.6446   0.6523
   1.750   0.7666   0.00638   0.00184  -0.1346   0.6376   0.6845
   2.000   0.7906   0.00640   0.00192  -0.1337   0.6307   0.7236
   2.250   0.8150   0.00633   0.00200  -0.1329   0.6246   0.7722
   2.500   0.8359   0.00619   0.00209  -0.1313   0.6179   0.8541
   2.750   0.8931   0.00616   0.00222  -0.1379   0.6095   1.0000
   3.000   0.9163   0.00629   0.00229  -0.1369   0.5990   1.0000
   3.250   0.9409   0.00637   0.00237  -0.1362   0.5895   1.0000
   3.500   0.9645   0.00650   0.00245  -0.1353   0.5815   1.0000
   3.750   0.9897   0.00658   0.00253  -0.1347   0.5740   1.0000
   4.000   1.0129   0.00671   0.00263  -0.1337   0.5641   1.0000
   4.250   1.0365   0.00683   0.00273  -0.1328   0.5535   1.0000
   4.500   1.0600   0.00696   0.00284  -0.1319   0.5427   1.0000
   4.750   1.0822   0.00712   0.00296  -0.1308   0.5299   1.0000
   5.000   1.1031   0.00731   0.00309  -0.1294   0.5129   1.0000
   5.250   1.1228   0.00753   0.00325  -0.1277   0.4933   1.0000
   5.500   1.1396   0.00784   0.00345  -0.1255   0.4683   1.0000
   5.750   1.1522   0.00823   0.00369  -0.1225   0.4379   1.0000
   6.000   1.1657   0.00863   0.00396  -0.1196   0.4111   1.0000
   6.250   1.1796   0.00904   0.00424  -0.1170   0.3826   1.0000
   6.500   1.1923   0.00952   0.00457  -0.1141   0.3506   1.0000
   6.750   1.2019   0.01014   0.00499  -0.1108   0.3088   1.0000
   7.000   1.2074   0.01095   0.00554  -0.1068   0.2598   1.0000
   7.250   1.2160   0.01167   0.00606  -0.1035   0.2258   1.0000
   7.500   1.2263   0.01234   0.00658  -0.1005   0.1969   1.0000
   7.750   1.2367   0.01302   0.00712  -0.0976   0.1682   1.0000
   8.000   1.2439   0.01387   0.00778  -0.0943   0.1325   1.0000
   8.250   1.2473   0.01494   0.00862  -0.0906   0.0936   1.0000
   8.500   1.2563   0.01578   0.00935  -0.0878   0.0750   1.0000
   8.750   1.2694   0.01644   0.00997  -0.0857   0.0665   1.0000
   9.000   1.2841   0.01704   0.01056  -0.0839   0.0607   1.0000
   9.250   1.2981   0.01768   0.01120  -0.0820   0.0562   1.0000
   9.500   1.3127   0.01832   0.01184  -0.0803   0.0517   1.0000
   9.750   1.3273   0.01897   0.01250  -0.0786   0.0479   1.0000
  10.000   1.3403   0.01973   0.01324  -0.0768   0.0434   1.0000
  10.250   1.3543   0.02045   0.01396  -0.0752   0.0393   1.0000
  10.500   1.3669   0.02128   0.01479  -0.0735   0.0354   1.0000
  10.750   1.3796   0.02212   0.01563  -0.0718   0.0325   1.0000
  11.000   1.3909   0.02307   0.01659  -0.0700   0.0297   1.0000
  11.250   1.4034   0.02397   0.01751  -0.0685   0.0277   1.0000
  11.500   1.4129   0.02509   0.01865  -0.0667   0.0256   1.0000
  11.750   1.4242   0.02611   0.01971  -0.0651   0.0243   1.0000
  12.000   1.4356   0.02715   0.02079  -0.0637   0.0231   1.0000
  12.250   1.4453   0.02834   0.02200  -0.0621   0.0220   1.0000
  12.500   1.4509   0.02988   0.02358  -0.0603   0.0208   1.0000
  12.750   1.4618   0.03104   0.02480  -0.0590   0.0201   1.0000
  13.000   1.4717   0.03230   0.02611  -0.0577   0.0195   1.0000
  13.250   1.4810   0.03365   0.02751  -0.0564   0.0188   1.0000
  13.500   1.4889   0.03513   0.02902  -0.0551   0.0180   1.0000
  13.750   1.4925   0.03703   0.03097  -0.0536   0.0173   1.0000
  14.000   1.4961   0.03898   0.03300  -0.0522   0.0167   1.0000
  14.250   1.5050   0.04050   0.03458  -0.0512   0.0164   1.0000
  14.500   1.5124   0.04219   0.03633  -0.0503   0.0159   1.0000
  14.750   1.5187   0.04401   0.03821  -0.0493   0.0154   1.0000
  15.000   1.5245   0.04592   0.04018  -0.0484   0.0150   1.0000
  15.250   1.5286   0.04804   0.04235  -0.0476   0.0146   1.0000
  15.500   1.5306   0.05042   0.04480  -0.0467   0.0143   1.0000
  15.750   1.5270   0.05347   0.04793  -0.0459   0.0139   1.0000
  16.000   1.5254   0.05636   0.05090  -0.0452   0.0136   1.0000
  16.250   1.5302   0.05860   0.05323  -0.0447   0.0134   1.0000
  16.500   1.5351   0.06086   0.05556  -0.0444   0.0130   1.0000
  16.750   1.5365   0.06356   0.05835  -0.0441   0.0128   1.0000
  17.000   1.5392   0.06617   0.06102  -0.0439   0.0125   1.0000
  17.250   1.5402   0.06901   0.06394  -0.0438   0.0122   1.0000
  17.500   1.5406   0.07198   0.06698  -0.0438   0.0120   1.0000
  17.750   1.5401   0.07512   0.07019  -0.0439   0.0118   1.0000
  18.000   1.5374   0.07862   0.07377  -0.0442   0.0116   1.0000
  18.250   1.5319   0.08258   0.07780  -0.0446   0.0114   1.0000
  18.500   1.5238   0.08696   0.08228  -0.0453   0.0112   1.0000
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