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NACA 6412 (naca6412-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: NACA 6412 (naca6412-il)
Reynolds number: 200,000
Max Cl/Cd: 81.22 at α=6.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca6412-il-200000-n5.txt
Download as CSV file: xf-naca6412-il-200000-n5.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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.2812   0.03450   0.02977  -0.1366   0.9274   0.0297
  -8.500  -0.2655   0.03216   0.02722  -0.1374   0.9197   0.0301
  -8.250  -0.2431   0.02984   0.02464  -0.1390   0.9143   0.0307
  -8.000  -0.2168   0.02742   0.02186  -0.1410   0.9107   0.0316
  -7.750  -0.1997   0.02552   0.01960  -0.1405   0.9021   0.0328
  -7.500  -0.1743   0.02333   0.01688  -0.1414   0.8967   0.0342
  -7.250  -0.1485   0.02220   0.01562  -0.1415   0.8907   0.0351
  -7.000  -0.1241   0.02135   0.01466  -0.1412   0.8832   0.0359
  -6.750  -0.0949   0.02038   0.01351  -0.1418   0.8786   0.0372
  -6.500  -0.0709   0.01951   0.01242  -0.1413   0.8716   0.0387
  -6.250  -0.0445   0.01866   0.01136  -0.1412   0.8655   0.0404
  -6.000  -0.0144   0.01809   0.01075  -0.1417   0.8611   0.0421
  -5.750   0.0094   0.01755   0.01011  -0.1410   0.8531   0.0439
  -5.500   0.0378   0.01688   0.00922  -0.1410   0.8471   0.0461
  -5.250   0.0648   0.01637   0.00869  -0.1409   0.8406   0.0482
  -5.000   0.0914   0.01598   0.00823  -0.1406   0.8331   0.0512
  -4.750   0.1210   0.01548   0.00759  -0.1409   0.8274   0.0545
  -4.500   0.1461   0.01516   0.00725  -0.1403   0.8185   0.0576
  -4.250   0.1752   0.01480   0.00676  -0.1404   0.8118   0.0619
  -4.000   0.2010   0.01449   0.00645  -0.1400   0.8033   0.0659
  -3.750   0.2294   0.01421   0.00607  -0.1399   0.7959   0.0711
  -3.500   0.2558   0.01394   0.00580  -0.1396   0.7870   0.0763
  -3.250   0.2840   0.01373   0.00547  -0.1395   0.7788   0.0828
  -3.000   0.3102   0.01350   0.00526  -0.1391   0.7693   0.0895
  -2.750   0.3383   0.01331   0.00498  -0.1389   0.7610   0.0972
  -2.500   0.3644   0.01315   0.00482  -0.1385   0.7510   0.1055
  -2.250   0.3918   0.01299   0.00461  -0.1383   0.7418   0.1142
  -2.000   0.4183   0.01289   0.00445  -0.1379   0.7315   0.1250
  -1.750   0.4450   0.01277   0.00434  -0.1376   0.7218   0.1375
  -1.500   0.4718   0.01268   0.00423  -0.1372   0.7121   0.1505
  -1.250   0.4981   0.01261   0.00415  -0.1368   0.7019   0.1645
  -1.000   0.5247   0.01256   0.00406  -0.1365   0.6920   0.1802
  -0.750   0.5507   0.01252   0.00402  -0.1360   0.6811   0.1977
  -0.500   0.5768   0.01249   0.00399  -0.1356   0.6709   0.2171
  -0.250   0.6029   0.01247   0.00397  -0.1352   0.6610   0.2386
   0.000   0.6286   0.01246   0.00398  -0.1347   0.6507   0.2625
   0.250   0.6544   0.01246   0.00398  -0.1343   0.6411   0.2892
   0.500   0.6797   0.01244   0.00401  -0.1337   0.6309   0.3217
   0.750   0.7050   0.01240   0.00405  -0.1332   0.6220   0.3646
   1.000   0.7286   0.01217   0.00414  -0.1324   0.6129   0.4740
   1.250   0.7775   0.01131   0.00427  -0.1368   0.6034   0.9999
   1.500   0.8032   0.01148   0.00432  -0.1363   0.5947   0.9999
   1.750   0.8289   0.01165   0.00440  -0.1359   0.5867   0.9999
   2.000   0.8544   0.01184   0.00449  -0.1354   0.5785   0.9999
   2.250   0.8800   0.01202   0.00460  -0.1349   0.5710   0.9999
   2.500   0.9055   0.01221   0.00472  -0.1344   0.5634   0.9999
   2.750   0.9311   0.01242   0.00484  -0.1340   0.5567   0.9999
   3.000   0.9564   0.01261   0.00501  -0.1335   0.5494   0.9999
   3.250   0.9817   0.01283   0.00515  -0.1330   0.5428   0.9999
   3.500   1.0071   0.01304   0.00533  -0.1326   0.5364   0.9999
   3.750   1.0322   0.01325   0.00552  -0.1321   0.5299   0.9999
   4.250   1.0825   0.01370   0.00593  -0.1311   0.5181   0.9999
   4.500   1.1073   0.01394   0.00615  -0.1306   0.5121   0.9999
   4.750   1.1323   0.01420   0.00637  -0.1301   0.5066   0.9999
   5.000   1.1567   0.01442   0.00664  -0.1296   0.5003   0.9999
   5.250   1.1812   0.01467   0.00689  -0.1290   0.4946   0.9999
   5.500   1.2058   0.01495   0.00715  -0.1285   0.4894   0.9999
   5.750   1.2296   0.01519   0.00746  -0.1278   0.4830   0.9999
   6.000   1.2533   0.01546   0.00773  -0.1271   0.4769   0.9999
   6.250   1.2773   0.01575   0.00804  -0.1265   0.4716   0.9999
   6.500   1.3003   0.01601   0.00838  -0.1258   0.4653   0.9999
   6.750   1.3230   0.01631   0.00868  -0.1249   0.4587   0.9999
   7.000   1.3449   0.01660   0.00904  -0.1239   0.4514   0.9999
   7.250   1.3659   0.01690   0.00937  -0.1228   0.4433   0.9999
   7.500   1.3851   0.01721   0.00972  -0.1213   0.4331   0.9999
   7.750   1.4024   0.01755   0.01005  -0.1195   0.4213   0.9999
   8.000   1.4175   0.01790   0.01043  -0.1173   0.4079   0.9999
   8.250   1.4321   0.01827   0.01084  -0.1150   0.3945   0.9999
   8.500   1.4467   0.01870   0.01129  -0.1129   0.3813   0.9999
   8.750   1.4606   0.01919   0.01179  -0.1106   0.3677   0.9999
   9.000   1.4733   0.01975   0.01236  -0.1083   0.3524   0.9999
   9.250   1.4845   0.02041   0.01301  -0.1058   0.3350   0.9999
   9.500   1.4932   0.02122   0.01378  -0.1031   0.3153   0.9999
   9.750   1.4997   0.02221   0.01470  -0.1002   0.2937   0.9999
  10.000   1.5048   0.02336   0.01578  -0.0973   0.2701   0.9999
  10.250   1.5074   0.02474   0.01707  -0.0943   0.2458   0.9999
  10.500   1.5080   0.02635   0.01856  -0.0912   0.2202   0.9999
  10.750   1.5079   0.02812   0.02024  -0.0883   0.1952   0.9999
  11.000   1.5060   0.03013   0.02214  -0.0855   0.1719   0.9999
  11.250   1.5038   0.03228   0.02421  -0.0830   0.1499   0.9999
  11.500   1.5006   0.03462   0.02647  -0.0805   0.1308   0.9999
  11.750   1.4983   0.03700   0.02881  -0.0784   0.1139   0.9999
  12.000   1.4958   0.03949   0.03128  -0.0765   0.0999   0.9999
  12.250   1.4937   0.04207   0.03385  -0.0749   0.0885   0.9999
  12.500   1.4914   0.04478   0.03656  -0.0734   0.0791   0.9999
  12.750   1.4895   0.04755   0.03934  -0.0722   0.0712   0.9999
  13.000   1.4887   0.05030   0.04214  -0.0711   0.0648   0.9999
  13.250   1.4862   0.05332   0.04521  -0.0702   0.0597   0.9999
  13.500   1.4861   0.05617   0.04815  -0.0695   0.0550   0.9999
  13.750   1.4830   0.05943   0.05145  -0.0688   0.0513   0.9999
  14.000   1.4826   0.06244   0.05456  -0.0684   0.0480   0.9999
  14.250   1.4797   0.06582   0.05799  -0.0680   0.0452   0.9999
  14.500   1.4769   0.06927   0.06153  -0.0677   0.0429   0.9999
  14.750   1.4757   0.07256   0.06493  -0.0676   0.0407   0.9999
  15.000   1.4725   0.07614   0.06860  -0.0675   0.0388   0.9999
  15.250   1.4674   0.08004   0.07257  -0.0676   0.0372   0.9999
  15.500   1.4655   0.08357   0.07621  -0.0677   0.0357   0.9999
  15.750   1.4633   0.08717   0.07992  -0.0679   0.0342   0.9999
  16.000   1.4600   0.09095   0.08378  -0.0682   0.0328   0.9999
  16.250   1.4549   0.09500   0.08791  -0.0687   0.0317   0.9999
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