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RAF 19 AIRFOIL (raf19-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: RAF 19 AIRFOIL (raf19-il)
Reynolds number: 100,000
Max Cl/Cd: 44.63 at α=6.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-raf19-il-100000.txt
Download as CSV file: xf-raf19-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: RAF 19 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.0344   0.11215   0.10832  -0.0514   0.9511   0.0615
  -7.500  -0.0212   0.11207   0.10824  -0.0580   0.9384   0.0624
  -7.250  -0.0026   0.10887   0.10506  -0.0635   0.9289   0.0630
  -7.000   0.0289   0.10113   0.09730  -0.0642   0.9241   0.0649
  -6.750   0.0529   0.09737   0.09353  -0.0679   0.9153   0.0673
  -6.500   0.0703   0.09446   0.09061  -0.0709   0.9031   0.0697
  -6.250   0.0945   0.09210   0.08823  -0.0772   0.8903   0.0725
  -6.000   0.1342   0.09018   0.08624  -0.0906   0.8807   0.0736
  -5.750   0.1530   0.08319   0.07925  -0.0878   0.8722   0.0750
  -5.500   0.1962   0.07817   0.07416  -0.0940   0.8673   0.0806
  -5.250   0.2496   0.07895   0.07476  -0.1124   0.8518   0.0851
  -5.000   0.2570   0.07217   0.06802  -0.1070   0.8412   0.0863
  -4.750   0.2888   0.06772   0.06349  -0.1095   0.8325   0.0904
  -4.500   0.3476   0.06652   0.06204  -0.1252   0.8192   0.0982
  -4.250   0.3554   0.06173   0.05725  -0.1211   0.8060   0.1003
  -4.000   0.4205   0.06271   0.05785  -0.1364   0.7900   0.1119
  -3.750   0.4195   0.05697   0.05217  -0.1306   0.7778   0.1135
  -3.500   0.4373   0.05402   0.04914  -0.1297   0.7653   0.1180
  -3.250   0.4929   0.05384   0.04856  -0.1405   0.7508   0.1275
  -3.000   0.5034   0.05015   0.04484  -0.1378   0.7391   0.1295
  -2.750   0.5203   0.04833   0.04294  -0.1370   0.7256   0.1327
  -2.500   0.5458   0.04694   0.04140  -0.1385   0.7125   0.1373
  -2.250   0.5926   0.04675   0.04085  -0.1450   0.6992   0.1431
  -2.000   0.6090   0.04397   0.03800  -0.1437   0.6886   0.1451
  -1.750   0.6262   0.04258   0.03655  -0.1427   0.6754   0.1479
  -1.500   0.6505   0.04148   0.03532  -0.1432   0.6628   0.1526
  -1.250   0.6932   0.04153   0.03502  -0.1474   0.6498   0.1583
  -1.000   0.7122   0.03915   0.03254  -0.1465   0.6393   0.1602
  -0.750   0.7299   0.03789   0.03123  -0.1453   0.6261   0.1634
  -0.250   0.7829   0.03620   0.02919  -0.1461   0.6008   0.1752
   0.000   0.8065   0.03506   0.02788  -0.1457   0.5891   0.1808
   0.250   0.8389   0.03471   0.02722  -0.1469   0.5762   0.1885
   0.500   0.8565   0.03353   0.02599  -0.1454   0.5632   0.1921
   0.750   0.8864   0.03355   0.02574  -0.1459   0.5504   0.2022
   1.000   0.9072   0.03228   0.02436  -0.1450   0.5395   0.2068
   1.250   0.9352   0.03194   0.02374  -0.1452   0.5279   0.2176
   1.500   0.9575   0.03176   0.02344  -0.1443   0.5158   0.2307
   1.750   0.9798   0.03108   0.02262  -0.1435   0.5057   0.2461
   2.000   1.0025   0.03049   0.02190  -0.1428   0.4959   0.2624
   2.250   1.0224   0.03015   0.02151  -0.1415   0.4863   0.2814
   3.000   1.0874   0.02871   0.01971  -0.1385   0.4624   0.3975
   3.250   1.1056   0.02832   0.01934  -0.1368   0.4546   0.4299
   3.500   1.1331   0.02806   0.01890  -0.1367   0.4474   0.4377
   3.750   1.1794   0.02927   0.01944  -0.1385   0.4402   0.2551
   4.000   1.2033   0.02927   0.01932  -0.1377   0.4337   0.2546
   4.250   1.2361   0.02932   0.01903  -0.1384   0.4286   0.2571
   4.500   1.2527   0.02964   0.01945  -0.1365   0.4222   0.2602
   4.750   1.2779   0.02983   0.01950  -0.1359   0.4167   0.2594
   5.000   1.3101   0.03000   0.01950  -0.1369   0.4118   0.2680
   5.250   1.3290   0.03056   0.02017  -0.1356   0.4056   0.2697
   5.500   1.3594   0.03089   0.02037  -0.1362   0.4005   0.2710
   5.750   1.3960   0.03130   0.02057  -0.1380   0.3962   0.2739
   6.000   1.4152   0.03207   0.02156  -0.1371   0.3910   0.2796
   6.250   1.4404   0.03268   0.02218  -0.1369   0.3867   0.2877
   6.500   1.4747   0.03304   0.02247  -0.1384   0.3829   0.2952
   6.750   1.4976   0.03386   0.02333  -0.1379   0.3791   0.3017
   7.000   1.5115   0.03479   0.02449  -0.1360   0.3746   0.3084
   7.250   1.5328   0.03548   0.02523  -0.1352   0.3707   0.3185
   7.500   1.5619   0.03594   0.02568  -0.1357   0.3672   0.3387
   7.750   1.5844   0.03688   0.02671  -0.1353   0.3642   0.3649
   8.000   1.5881   0.03833   0.02855  -0.1320   0.3609   0.3944
   8.250   1.6299   0.03958   0.03046  -0.1364   0.3566   1.0000
   8.500   1.6563   0.03994   0.03067  -0.1361   0.3523   1.0000
   8.750   1.6722   0.04057   0.03126  -0.1344   0.3468   1.0000
   9.000   1.6786   0.04107   0.03183  -0.1310   0.3399   1.0000
   9.250   1.7112   0.04029   0.03075  -0.1314   0.3316   1.0000
   9.500   1.7082   0.04139   0.03205  -0.1269   0.3264   1.0000
   9.750   1.7442   0.04057   0.03094  -0.1278   0.3190   1.0000
  10.000   1.7433   0.04170   0.03226  -0.1237   0.3145   1.0000
  10.250   1.7394   0.04293   0.03369  -0.1193   0.3105   1.0000
  10.500   1.7743   0.04159   0.03198  -0.1198   0.3010   1.0000
  10.750   1.7564   0.04305   0.03373  -0.1134   0.2977   1.0000
  11.000   1.7495   0.04388   0.03469  -0.1088   0.2924   1.0000
  11.250   1.7784   0.04313   0.03368  -0.1086   0.2854   1.0000
  11.500   1.7600   0.04503   0.03590  -0.1032   0.2823   1.0000
  11.750   1.7491   0.04672   0.03780  -0.0991   0.2784   1.0000
  12.000   1.7643   0.04662   0.03761  -0.0975   0.2726   1.0000
  12.250   1.7547   0.04826   0.03938  -0.0941   0.2677   1.0000
  12.500   1.7352   0.05095   0.04230  -0.0906   0.2634   1.0000
  12.750   1.7450   0.05096   0.04218  -0.0889   0.2560   1.0000
  13.000   1.7264   0.05426   0.04573  -0.0864   0.2523   1.0000
  13.250   1.7082   0.05796   0.04967  -0.0845   0.2489   1.0000
  13.500   1.7005   0.06065   0.05248  -0.0832   0.2443   1.0000
  13.750   1.7059   0.06192   0.05373  -0.0822   0.2395   1.0000
  14.000   1.6786   0.06753   0.05964  -0.0815   0.2371   1.0000
  14.250   1.6463   0.07425   0.06664  -0.0814   0.2347   1.0000
  14.500   1.5807   0.08660   0.07933  -0.0832   0.2344   1.0000
  14.750   1.6448   0.07938   0.07187  -0.0809   0.2253   1.0000
  15.000   1.5914   0.09026   0.08306  -0.0829   0.2241   1.0000
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