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NACA 6412 (naca6412-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: NACA 6412 (naca6412-il)
Reynolds number: 100,000
Max Cl/Cd: 53.09 at α=10.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-naca6412-il-100000.txt
Download as CSV file: xf-naca6412-il-100000.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 =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.3657   0.12392   0.11950  -0.0276   1.0001   0.0956
  -8.500  -0.3935   0.12437   0.12006  -0.0262   1.0001   0.0959
  -8.250  -0.4195   0.12441   0.12020  -0.0243   1.0001   0.0960
  -8.000  -0.3673   0.11524   0.11096  -0.0217   1.0001   0.0988
  -7.750  -0.3473   0.11172   0.10742  -0.0242   0.9963   0.1026
  -7.500  -0.3363   0.10865   0.10434  -0.0297   0.9895   0.1073
  -7.250  -0.3428   0.10667   0.10238  -0.0508   0.9733   0.1103
  -7.000  -0.3193   0.10099   0.09670  -0.0429   0.9727   0.1119
  -6.750  -0.2956   0.09735   0.09303  -0.0429   0.9671   0.1149
  -6.500  -0.2745   0.09372   0.08938  -0.0477   0.9594   0.1196
  -6.250  -0.2591   0.08857   0.08416  -0.0661   0.9449   0.1262
  -6.000  -0.2341   0.08517   0.08077  -0.0613   0.9427   0.1294
  -5.750  -0.2208   0.08254   0.07814  -0.0622   0.9326   0.1341
  -5.500  -0.1927   0.07702   0.07247  -0.0771   0.9225   0.1430
  -5.250  -0.1747   0.07417   0.06965  -0.0752   0.9153   0.1457
  -5.000  -0.1367   0.06949   0.06468  -0.0893   0.9061   0.1591
  -4.750  -0.1209   0.06662   0.06191  -0.0860   0.8991   0.1619
  -4.500  -0.0749   0.06220   0.05725  -0.0959   0.8945   0.1775
  -4.250  -0.0320   0.04616   0.04005  -0.1114   0.8854   0.1116
  -4.000   0.0124   0.04081   0.03396  -0.1169   0.8809   0.1094
  -3.750   0.0596   0.03638   0.02884  -0.1219   0.8781   0.1111
  -3.500   0.0792   0.03587   0.02850  -0.1209   0.8669   0.1160
  -3.250   0.1250   0.03333   0.02534  -0.1243   0.8631   0.1230
  -3.000   0.1528   0.03210   0.02391  -0.1247   0.8542   0.1299
  -2.750   0.1925   0.03088   0.02234  -0.1265   0.8483   0.1399
  -2.500   0.2394   0.02948   0.02085  -0.1297   0.8454   0.1523
  -2.250   0.2610   0.02893   0.02013  -0.1286   0.8340   0.1619
  -2.000   0.3063   0.02778   0.01881  -0.1312   0.8304   0.1776
  -1.750   0.3528   0.02665   0.01766  -0.1340   0.8279   0.1973
  -1.500   0.3729   0.02648   0.01742  -0.1325   0.8158   0.2126
  -1.250   0.4158   0.02542   0.01645  -0.1346   0.8125   0.2365
  -0.750   0.4773   0.02438   0.01548  -0.1349   0.7972   0.2886
  -0.500   0.5058   0.02399   0.01516  -0.1348   0.7887   0.3210
  -0.250   0.5387   0.02324   0.01457  -0.1352   0.7819   0.3636
   0.000   0.5812   0.02202   0.01367  -0.1371   0.7785   0.4425
   0.250   0.6154   0.02073   0.01371  -0.1380   0.7684   0.9999
   0.500   0.6546   0.02038   0.01303  -0.1393   0.7631   0.9999
   0.750   0.6783   0.02066   0.01315  -0.1384   0.7530   0.9999
   1.000   0.7136   0.02045   0.01275  -0.1393   0.7469   0.9999
   1.250   0.7388   0.02072   0.01290  -0.1387   0.7379   0.9999
   1.500   0.7706   0.02067   0.01271  -0.1390   0.7307   0.9999
   1.750   0.7990   0.02082   0.01276  -0.1389   0.7231   0.9999
   2.000   0.8256   0.02103   0.01289  -0.1386   0.7148   0.9999
   2.250   0.8638   0.02079   0.01251  -0.1399   0.7100   0.9999
   2.500   0.8791   0.02152   0.01324  -0.1379   0.6992   0.9999
   2.750   0.9159   0.02135   0.01295  -0.1391   0.6941   0.9999
   3.000   0.9315   0.02212   0.01374  -0.1373   0.6841   0.9999
   3.250   0.9656   0.02206   0.01360  -0.1380   0.6785   0.9999
   3.500   0.9844   0.02274   0.01429  -0.1366   0.6698   0.9999
   3.750   1.0139   0.02290   0.01441  -0.1368   0.6632   0.9999
   4.000   1.0411   0.02323   0.01473  -0.1366   0.6567   0.9999
   4.250   1.0612   0.02383   0.01537  -0.1354   0.6485   0.9999
   4.500   1.0972   0.02376   0.01522  -0.1365   0.6435   0.9999
   4.750   1.1094   0.02477   0.01633  -0.1343   0.6343   0.9999
   5.000   1.1412   0.02486   0.01640  -0.1347   0.6284   0.9999
   5.250   1.1609   0.02556   0.01716  -0.1335   0.6207   0.9999
   5.500   1.1851   0.02599   0.01763  -0.1329   0.6135   0.9999
   5.750   1.2210   0.02597   0.01758  -0.1339   0.6084   0.9999
   6.000   1.2294   0.02715   0.01891  -0.1312   0.5990   0.9999
   6.250   1.2657   0.02702   0.01875  -0.1322   0.5933   0.9999
   6.500   1.2761   0.02814   0.02003  -0.1298   0.5843   0.9999
   6.750   1.3072   0.02824   0.02015  -0.1300   0.5778   0.9999
   7.000   1.3248   0.02905   0.02106  -0.1286   0.5699   0.9999
   7.250   1.3505   0.02931   0.02139  -0.1281   0.5619   0.9999
   7.500   1.3734   0.02977   0.02193  -0.1272   0.5538   0.9999
   7.750   1.3974   0.03004   0.02227  -0.1264   0.5450   0.9999
   8.000   1.4185   0.03047   0.02281  -0.1252   0.5360   0.9999
   8.250   1.4526   0.03004   0.02236  -0.1255   0.5261   0.9999
   8.500   1.4655   0.03050   0.02295  -0.1229   0.5140   0.9999
   8.750   1.4912   0.03022   0.02269  -0.1219   0.5017   0.9999
   9.000   1.5229   0.02963   0.02206  -0.1218   0.4889   0.9999
   9.250   1.5396   0.02970   0.02221  -0.1196   0.4759   0.9999
   9.500   1.5510   0.03002   0.02266  -0.1167   0.4630   0.9999
   9.750   1.5674   0.03010   0.02281  -0.1145   0.4500   0.9999
  10.000   1.5843   0.03007   0.02282  -0.1124   0.4364   0.9999
  10.250   1.5975   0.03009   0.02288  -0.1096   0.4221   0.9999
  10.500   1.6004   0.03041   0.02329  -0.1054   0.4076   0.9999
  10.750   1.5968   0.03101   0.02403  -0.1004   0.3930   0.9999
  11.000   1.5938   0.03171   0.02481  -0.0958   0.3771   0.9999
  11.250   1.5904   0.03256   0.02571  -0.0915   0.3596   0.9999
  11.500   1.5830   0.03388   0.02710  -0.0871   0.3399   0.9999
  11.750   1.5733   0.03561   0.02886  -0.0830   0.3174   0.9999
  12.000   1.5616   0.03775   0.03093  -0.0791   0.2920   0.9999
  12.250   1.5460   0.04053   0.03358  -0.0755   0.2642   0.9999
  12.500   1.5269   0.04401   0.03690  -0.0722   0.2352   0.9999
  12.750   1.5063   0.04801   0.04073  -0.0695   0.2077   0.9999
  13.000   1.4863   0.05230   0.04483  -0.0672   0.1842   0.9999
  13.250   1.4684   0.05667   0.04902  -0.0654   0.1644   0.9999
  13.500   1.4540   0.06082   0.05300  -0.0639   0.1482   0.9999
  13.750   1.4437   0.06465   0.05671  -0.0626   0.1343   0.9999
  14.000   1.4378   0.06807   0.06005  -0.0615   0.1222   0.9999
  14.250   1.4357   0.07102   0.06294  -0.0602   0.1120   0.9999
  14.500   1.4371   0.07351   0.06529  -0.0589   0.1031   0.9999
  14.750   1.4389   0.07617   0.06797  -0.0580   0.0957   0.9999
  15.000   1.4454   0.07823   0.07001  -0.0566   0.0890   0.9999
  15.250   1.4517   0.08032   0.07205  -0.0556   0.0832   0.9999
  15.500   1.4618   0.08210   0.07389  -0.0542   0.0782   0.9999
  15.750   1.4668   0.08457   0.07647  -0.0535   0.0741   0.9999
  16.000   1.4892   0.08512   0.07685  -0.0516   0.0696   0.9999
  16.250   1.4906   0.08829   0.08031  -0.0511   0.0674   0.9999
  16.500   1.4942   0.09122   0.08346  -0.0506   0.0651   0.9999
  16.750   1.5004   0.09378   0.08613  -0.0501   0.0629   0.9999
  17.000   1.5222   0.09526   0.08752  -0.0487   0.0601   0.9999
  17.250   1.5087   0.10002   0.09261  -0.0492   0.0594   0.9999
  17.500   1.4948   0.10510   0.09801  -0.0501   0.0587   0.9999
  17.750   1.4799   0.11053   0.10375  -0.0514   0.0581   0.9999
  18.000   1.4634   0.11645   0.10996  -0.0533   0.0577   0.9999
  18.250   1.4440   0.12303   0.11683  -0.0558   0.0575   0.9999
  18.500   1.4210   0.13053   0.12462  -0.0593   0.0575   0.9999
  18.750   1.3943   0.13916   0.13353  -0.0639   0.0578   0.9999
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