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AH 94-145 (ah94145-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: AH 94-145 (ah94145-il)
Reynolds number: 500,000
Max Cl/Cd: 135.6 at α=7.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-ah94145-il-500000.txt
Download as CSV file: xf-ah94145-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: AH 94-145                                       
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.1933   0.10422   0.10069  -0.0601   0.7192   0.0267
 -10.000  -0.2061   0.09630   0.09281  -0.0681   0.7178   0.0280
  -9.750  -0.2006   0.09290   0.08940  -0.0684   0.7159   0.0283
  -9.500  -0.1907   0.09063   0.08712  -0.0689   0.7141   0.0285
  -9.250  -0.1810   0.08828   0.08475  -0.0697   0.7123   0.0289
  -9.000  -0.1728   0.08560   0.08205  -0.0711   0.7103   0.0293
  -8.750  -0.1658   0.08247   0.07894  -0.0731   0.7089   0.0299
  -8.500  -0.1608   0.07880   0.07530  -0.0759   0.7072   0.0308
  -8.250  -0.1784   0.06536   0.06192  -0.0948   0.7055   0.0329
  -8.000  -0.2561   0.02698   0.02195  -0.1199   0.7048   0.0221
  -7.750  -0.2356   0.02353   0.01793  -0.1209   0.7028   0.0228
  -7.500  -0.2107   0.02161   0.01558  -0.1215   0.7007   0.0234
  -7.250  -0.1851   0.01983   0.01344  -0.1220   0.6988   0.0238
  -7.000  -0.1588   0.01846   0.01193  -0.1224   0.6971   0.0244
  -6.750  -0.1311   0.01778   0.01115  -0.1228   0.6954   0.0251
  -6.500  -0.1032   0.01717   0.01042  -0.1232   0.6935   0.0259
  -6.250  -0.0748   0.01646   0.00961  -0.1236   0.6918   0.0268
  -6.000  -0.0461   0.01590   0.00892  -0.1239   0.6899   0.0277
  -5.750  -0.0181   0.01508   0.00806  -0.1243   0.6880   0.0291
  -5.500   0.0107   0.01473   0.00771  -0.1248   0.6861   0.0306
  -5.250   0.0397   0.01434   0.00723  -0.1251   0.6844   0.0322
  -5.000   0.0685   0.01376   0.00659  -0.1255   0.6827   0.0339
  -4.750   0.0976   0.01345   0.00627  -0.1260   0.6810   0.0361
  -4.500   0.1270   0.01326   0.00600  -0.1264   0.6792   0.0386
  -4.250   0.1561   0.01299   0.00573  -0.1269   0.6773   0.0424
  -4.000   0.1856   0.01271   0.00545  -0.1274   0.6758   0.0466
  -3.750   0.2151   0.01251   0.00528  -0.1279   0.6742   0.0517
  -3.500   0.2447   0.01228   0.00509  -0.1284   0.6724   0.0582
  -3.250   0.2743   0.01211   0.00492  -0.1289   0.6706   0.0654
  -3.000   0.3039   0.01201   0.00482  -0.1294   0.6687   0.0729
  -2.750   0.3337   0.01181   0.00464  -0.1300   0.6669   0.0817
  -2.500   0.3635   0.01167   0.00448  -0.1305   0.6652   0.0905
  -2.250   0.3933   0.01158   0.00438  -0.1310   0.6636   0.1004
  -2.000   0.4232   0.01149   0.00431  -0.1317   0.6620   0.1144
  -1.750   0.4531   0.01136   0.00427  -0.1323   0.6602   0.1373
  -1.500   0.4833   0.01102   0.00422  -0.1332   0.6584   0.2111
  -1.250   0.5144   0.01038   0.00422  -0.1347   0.6565   0.4096
  -1.000   0.5454   0.00986   0.00431  -0.1359   0.6547   0.6098
  -0.750   0.5745   0.00966   0.00440  -0.1362   0.6529   0.7093
  -0.500   0.6016   0.00957   0.00450  -0.1359   0.6512   0.7770
  -0.250   0.6277   0.00958   0.00458  -0.1353   0.6495   0.8254
   0.000   0.6543   0.00964   0.00464  -0.1349   0.6478   0.8557
   0.250   0.6797   0.00975   0.00474  -0.1342   0.6461   0.8788
   0.500   0.7049   0.00988   0.00487  -0.1336   0.6443   0.8975
   0.750   0.7289   0.00992   0.00496  -0.1327   0.6425   0.9146
   1.000   0.7473   0.00993   0.00501  -0.1304   0.6405   0.9370
   1.250   0.7597   0.00982   0.00494  -0.1267   0.6384   0.9659
   1.500   0.7908   0.00969   0.00481  -0.1272   0.6363   0.9998
   1.750   0.8220   0.00977   0.00484  -0.1282   0.6345   0.9998
   2.000   0.8534   0.00985   0.00488  -0.1293   0.6327   0.9998
   2.250   0.8849   0.00996   0.00494  -0.1303   0.6310   0.9998
   2.500   0.9160   0.01014   0.00509  -0.1312   0.6290   0.9998
   2.750   0.9462   0.01023   0.00522  -0.1321   0.6269   0.9998
   3.000   0.9765   0.01033   0.00534  -0.1329   0.6246   0.9998
   3.250   1.0069   0.01043   0.00545  -0.1337   0.6222   0.9998
   3.500   1.0375   0.01051   0.00553  -0.1346   0.6200   0.9998
   3.750   1.0681   0.01057   0.00558  -0.1354   0.6179   0.9998
   4.000   1.0989   0.01065   0.00563  -0.1362   0.6159   0.9998
   4.250   1.1292   0.01081   0.00577  -0.1369   0.6136   0.9998
   4.500   1.1579   0.01088   0.00592  -0.1374   0.6105   0.9998
   4.750   1.1870   0.01091   0.00599  -0.1380   0.6069   0.9998
   5.000   1.2169   0.01085   0.00593  -0.1385   0.6030   0.9998
   5.250   1.2472   0.01081   0.00583  -0.1391   0.5990   0.9998
   5.500   1.2747   0.01079   0.00590  -0.1393   0.5935   0.9998
   5.750   1.3035   0.01071   0.00583  -0.1397   0.5878   0.9998
   6.000   1.3326   0.01071   0.00579  -0.1401   0.5830   0.9998
   6.250   1.3595   0.01073   0.00592  -0.1402   0.5768   0.9998
   6.500   1.3875   0.01074   0.00594  -0.1405   0.5712   0.9998
   6.750   1.4151   0.01082   0.00606  -0.1407   0.5659   0.9998
   7.000   1.4420   0.01089   0.00621  -0.1408   0.5593   0.9998
   7.250   1.4690   0.01097   0.00628  -0.1409   0.5526   0.9998
   7.500   1.4947   0.01107   0.00646  -0.1408   0.5430   0.9998
   7.750   1.5201   0.01121   0.00664  -0.1407   0.5328   0.9998
   8.000   1.5446   0.01140   0.00683  -0.1404   0.5215   0.9998
   8.250   1.5678   0.01165   0.00709  -0.1399   0.5076   0.9998
   8.500   1.5891   0.01198   0.00742  -0.1391   0.4893   0.9998
   8.750   1.6059   0.01252   0.00787  -0.1376   0.4646   0.9998
   9.000   1.6166   0.01333   0.00856  -0.1352   0.4314   0.9998
   9.250   1.6151   0.01455   0.00959  -0.1308   0.3933   0.9998
   9.500   1.6065   0.01635   0.01120  -0.1262   0.3568   0.9998
   9.750   1.5969   0.01864   0.01333  -0.1223   0.3219   0.9998
  10.000   1.5875   0.02131   0.01586  -0.1191   0.2905   0.9998
  10.250   1.5792   0.02412   0.01854  -0.1165   0.2625   0.9998
  10.500   1.5710   0.02699   0.02130  -0.1139   0.2370   0.9998
  10.750   1.5652   0.02970   0.02390  -0.1116   0.2136   0.9998
  11.000   1.5590   0.03244   0.02655  -0.1093   0.1930   0.9998
  11.250   1.5551   0.03499   0.02903  -0.1073   0.1745   0.9998
  11.500   1.5521   0.03748   0.03145  -0.1053   0.1577   0.9998
  11.750   1.5504   0.03993   0.03385  -0.1035   0.1430   0.9998
  12.000   1.5500   0.04231   0.03619  -0.1019   0.1298   0.9998
  12.250   1.5503   0.04469   0.03852  -0.1005   0.1179   0.9998
  12.500   1.5508   0.04711   0.04091  -0.0991   0.1073   0.9998
  12.750   1.5524   0.04945   0.04321  -0.0978   0.0979   0.9998
  13.000   1.5557   0.05167   0.04544  -0.0967   0.0899   0.9998
  13.250   1.5578   0.05404   0.04780  -0.0956   0.0827   0.9998
  13.500   1.5608   0.05637   0.05014  -0.0946   0.0762   0.9998
  13.750   1.5639   0.05869   0.05248  -0.0936   0.0706   0.9998
  14.000   1.5664   0.06110   0.05489  -0.0927   0.0655   0.9998
  14.250   1.5689   0.06356   0.05739  -0.0918   0.0611   0.9998
  14.500   1.5728   0.06589   0.05975  -0.0911   0.0572   0.9998
  14.750   1.5712   0.06887   0.06273  -0.0902   0.0535   0.9998
  15.000   1.5777   0.07095   0.06489  -0.0896   0.0507   0.9998
  15.250   1.5794   0.07360   0.06757  -0.0890   0.0479   0.9998
  15.500   1.5774   0.07671   0.07070  -0.0883   0.0451   0.9998
  15.750   1.5826   0.07903   0.07311  -0.0878   0.0431   0.9998
  16.000   1.5851   0.08167   0.07580  -0.0874   0.0410   0.9998
  16.250   1.5832   0.08486   0.07902  -0.0869   0.0390   0.9998
  16.500   1.5831   0.08785   0.08209  -0.0866   0.0374   0.9998
  16.750   1.5864   0.09048   0.08480  -0.0863   0.0359   0.9998
  17.000   1.5878   0.09335   0.08773  -0.0862   0.0344   0.9998
  17.250   1.5856   0.09671   0.09113  -0.0860   0.0330   0.9998
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