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NACA 6412 (naca6412-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: NACA 6412 (naca6412-il)
Reynolds number: 500,000
Max Cl/Cd: 114.15 at α=6.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-naca6412-il-500000.txt
Download as CSV file: xf-naca6412-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 6412                                       
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.1344   0.08939   0.08696  -0.0883   0.9771   0.0354
  -9.250  -0.2938   0.02885   0.02541  -0.1484   0.9457   0.0283
  -9.000  -0.2807   0.02451   0.02046  -0.1502   0.9392   0.0288
  -8.750  -0.2627   0.02239   0.01793  -0.1500   0.9319   0.0293
  -8.500  -0.2407   0.02012   0.01534  -0.1503   0.9273   0.0300
  -8.250  -0.2191   0.01921   0.01438  -0.1496   0.9208   0.0306
  -8.000  -0.1937   0.01861   0.01370  -0.1494   0.9157   0.0314
  -7.750  -0.1673   0.01780   0.01274  -0.1494   0.9115   0.0324
  -7.500  -0.1435   0.01696   0.01172  -0.1489   0.9055   0.0332
  -7.250  -0.1184   0.01622   0.01078  -0.1484   0.8996   0.0341
  -7.000  -0.0929   0.01507   0.00944  -0.1482   0.8949   0.0349
  -6.750  -0.0682   0.01447   0.00881  -0.1477   0.8886   0.0360
  -6.500  -0.0419   0.01404   0.00832  -0.1474   0.8824   0.0373
  -6.000   0.0114   0.01319   0.00723  -0.1467   0.8699   0.0400
  -5.750   0.0372   0.01249   0.00649  -0.1464   0.8637   0.0418
  -5.500   0.0643   0.01217   0.00613  -0.1461   0.8575   0.0437
  -5.250   0.0908   0.01188   0.00574  -0.1457   0.8501   0.0458
  -5.000   0.1179   0.01140   0.00521  -0.1455   0.8438   0.0486
  -4.750   0.1441   0.01119   0.00498  -0.1450   0.8354   0.0516
  -4.500   0.1714   0.01085   0.00454  -0.1448   0.8285   0.0549
  -4.250   0.1976   0.01060   0.00430  -0.1444   0.8202   0.0586
  -4.000   0.2254   0.01048   0.00408  -0.1441   0.8124   0.0622
  -3.750   0.2513   0.01018   0.00380  -0.1437   0.8036   0.0676
  -3.500   0.2790   0.01009   0.00361  -0.1435   0.7954   0.0720
  -3.250   0.3050   0.00983   0.00338  -0.1430   0.7863   0.0784
  -3.000   0.3323   0.00973   0.00320  -0.1427   0.7779   0.0845
  -2.750   0.3586   0.00957   0.00306  -0.1423   0.7681   0.0925
  -2.500   0.3853   0.00945   0.00290  -0.1420   0.7590   0.1011
  -2.250   0.4119   0.00939   0.00281  -0.1416   0.7484   0.1099
  -2.000   0.4382   0.00927   0.00270  -0.1411   0.7383   0.1218
  -1.750   0.4645   0.00920   0.00260  -0.1407   0.7281   0.1339
  -1.500   0.4907   0.00914   0.00254  -0.1403   0.7171   0.1468
  -1.250   0.5169   0.00911   0.00248  -0.1398   0.7064   0.1609
  -1.000   0.5429   0.00910   0.00245  -0.1393   0.6949   0.1772
  -0.750   0.5688   0.00907   0.00244  -0.1389   0.6835   0.1956
  -0.500   0.5946   0.00906   0.00243  -0.1384   0.6725   0.2155
  -0.250   0.6201   0.00907   0.00244  -0.1378   0.6610   0.2375
   0.000   0.6458   0.00907   0.00247  -0.1373   0.6494   0.2623
   0.250   0.6712   0.00908   0.00250  -0.1368   0.6385   0.2907
   0.500   0.6963   0.00908   0.00254  -0.1362   0.6275   0.3269
   0.750   0.7212   0.00902   0.00259  -0.1356   0.6168   0.3775
   1.000   0.7419   0.00864   0.00273  -0.1343   0.6072   0.5862
   1.250   0.8011   0.00799   0.00289  -0.1414   0.5961   0.9999
   1.500   0.8268   0.00814   0.00295  -0.1409   0.5870   0.9999
   1.750   0.8523   0.00830   0.00302  -0.1404   0.5780   0.9999
   2.000   0.8782   0.00845   0.00311  -0.1399   0.5698   0.9999
   2.250   0.9038   0.00861   0.00320  -0.1395   0.5618   0.9999
   2.500   0.9297   0.00878   0.00331  -0.1391   0.5548   0.9999
   2.750   0.9556   0.00893   0.00341  -0.1387   0.5476   0.9999
   3.000   0.9810   0.00914   0.00354  -0.1382   0.5410   0.9999
   3.250   1.0072   0.00926   0.00366  -0.1379   0.5347   0.9999
   3.500   1.0328   0.00943   0.00379  -0.1375   0.5283   0.9999
   3.750   1.0584   0.00963   0.00395  -0.1371   0.5223   0.9999
   4.000   1.0843   0.00977   0.00409  -0.1367   0.5163   0.9999
   4.250   1.1098   0.00996   0.00424  -0.1363   0.5107   0.9999
   4.500   1.1353   0.01016   0.00442  -0.1359   0.5051   0.9999
   4.750   1.1609   0.01031   0.00459  -0.1355   0.4993   0.9999
   5.000   1.1861   0.01051   0.00476  -0.1351   0.4938   0.9999
   5.250   1.2116   0.01073   0.00497  -0.1347   0.4889   0.9999
   5.500   1.2367   0.01088   0.00516  -0.1342   0.4832   0.9999
   5.750   1.2611   0.01109   0.00535  -0.1337   0.4769   0.9999
   6.000   1.2856   0.01131   0.00557  -0.1331   0.4708   0.9999
   6.250   1.3093   0.01147   0.00576  -0.1324   0.4633   0.9999
   6.500   1.3320   0.01172   0.00598  -0.1315   0.4550   0.9999
   6.750   1.3544   0.01188   0.00617  -0.1305   0.4454   0.9999
   7.000   1.3764   0.01212   0.00640  -0.1295   0.4364   0.9999
   7.250   1.3985   0.01233   0.00663  -0.1286   0.4275   0.9999
   7.500   1.4203   0.01257   0.00688  -0.1276   0.4189   0.9999
   7.750   1.4404   0.01282   0.00715  -0.1262   0.4091   0.9999
   8.000   1.4601   0.01307   0.00742  -0.1248   0.3982   0.9999
   8.250   1.4785   0.01339   0.00773  -0.1232   0.3873   0.9999
   8.500   1.4960   0.01377   0.00808  -0.1215   0.3748   0.9999
   8.750   1.5139   0.01415   0.00847  -0.1199   0.3603   0.9999
   9.000   1.5288   0.01467   0.00894  -0.1178   0.3423   0.9999
   9.250   1.5427   0.01529   0.00949  -0.1157   0.3195   0.9999
   9.500   1.5530   0.01612   0.01020  -0.1131   0.2945   0.9999
   9.750   1.5615   0.01710   0.01105  -0.1104   0.2660   0.9999
  10.000   1.5684   0.01824   0.01203  -0.1076   0.2367   0.9999
  10.250   1.5732   0.01955   0.01318  -0.1046   0.2070   0.9999
  10.500   1.5761   0.02103   0.01451  -0.1016   0.1774   0.9999
  10.750   1.5778   0.02266   0.01600  -0.0986   0.1498   0.9999
  11.000   1.5792   0.02439   0.01759  -0.0957   0.1260   0.9999
  11.250   1.5797   0.02626   0.01935  -0.0930   0.1058   0.9999
  11.500   1.5818   0.02808   0.02111  -0.0906   0.0897   0.9999
  11.750   1.5841   0.02998   0.02296  -0.0884   0.0771   0.9999
  12.000   1.5861   0.03196   0.02493  -0.0864   0.0673   0.9999
  12.250   1.5874   0.03408   0.02705  -0.0845   0.0598   0.9999
  12.500   1.5904   0.03615   0.02913  -0.0829   0.0537   0.9999
  12.750   1.5928   0.03834   0.03136  -0.0814   0.0489   0.9999
  13.000   1.5928   0.04082   0.03387  -0.0800   0.0449   0.9999
  13.250   1.5952   0.04319   0.03631  -0.0788   0.0418   0.9999
  13.500   1.5959   0.04581   0.03897  -0.0778   0.0390   0.9999
  13.750   1.5928   0.04890   0.04212  -0.0767   0.0366   0.9999
  14.000   1.5954   0.05145   0.04477  -0.0760   0.0345   0.9999
  14.250   1.5936   0.05457   0.04794  -0.0753   0.0327   0.9999
  14.500   1.5871   0.05833   0.05176  -0.0746   0.0311   0.9999
  14.750   1.5890   0.06114   0.05468  -0.0742   0.0297   0.9999
  15.000   1.5882   0.06432   0.05794  -0.0739   0.0283   0.9999
  15.250   1.5833   0.06808   0.06176  -0.0737   0.0272   0.9999
  15.500   1.5733   0.07257   0.06632  -0.0735   0.0263   0.9999
  15.750   1.5732   0.07582   0.06969  -0.0735   0.0255   0.9999
  16.000   1.5708   0.07938   0.07334  -0.0735   0.0247   0.9999
  16.250   1.5677   0.08308   0.07712  -0.0736   0.0240   0.9999
  16.500   1.5633   0.08699   0.08112  -0.0739   0.0233   0.9999
  16.750   1.5568   0.09124   0.08543  -0.0743   0.0228   0.9999
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