Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

AH 94-145 (ah94145-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: AH 94-145 (ah94145-il)
Reynolds number: 100,000
Max Cl/Cd: 30.57 at α=2.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-ah94145-il-100000-n5.txt
Download as CSV file: xf-ah94145-il-100000-n5.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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.1647   0.11364   0.10792  -0.0674   0.7836   0.0582
 -10.250  -0.1592   0.11041   0.10467  -0.0691   0.7807   0.0586
  -9.750  -0.1688   0.09798   0.09218  -0.0774   0.7761   0.0387
  -9.500  -0.1585   0.09523   0.08944  -0.0781   0.7728   0.0382
  -9.250  -0.1514   0.09196   0.08618  -0.0797   0.7697   0.0377
  -9.000  -0.1464   0.08835   0.08258  -0.0818   0.7670   0.0372
  -8.750  -0.1433   0.08438   0.07861  -0.0846   0.7644   0.0372
  -8.500  -0.1414   0.08007   0.07430  -0.0879   0.7620   0.0374
  -8.250  -0.1404   0.07541   0.06962  -0.0919   0.7597   0.0376
  -8.000  -0.1415   0.07057   0.06484  -0.0971   0.7564   0.0376
  -7.750  -0.1391   0.06417   0.05840  -0.1054   0.7531   0.0374
  -7.500  -0.1361   0.05767   0.05175  -0.1121   0.7501   0.0371
  -7.250  -0.1316   0.05117   0.04496  -0.1173   0.7475   0.0368
  -7.000  -0.1236   0.04497   0.03828  -0.1211   0.7453   0.0368
  -6.750  -0.1099   0.03974   0.03243  -0.1235   0.7435   0.0373
  -6.500  -0.0924   0.03493   0.02677  -0.1253   0.7405   0.0387
  -6.250  -0.0688   0.03418   0.02603  -0.1258   0.7375   0.0402
  -6.000  -0.0448   0.03277   0.02437  -0.1263   0.7346   0.0420
  -5.750  -0.0198   0.03063   0.02175  -0.1268   0.7321   0.0437
  -5.500   0.0064   0.02869   0.01929  -0.1271   0.7299   0.0458
  -5.250   0.0328   0.02807   0.01863  -0.1274   0.7281   0.0483
  -5.000   0.0598   0.02715   0.01744  -0.1276   0.7262   0.0517
  -4.750   0.0854   0.02624   0.01637  -0.1277   0.7230   0.0545
  -4.500   0.1113   0.02582   0.01593  -0.1279   0.7199   0.0584
  -4.250   0.1382   0.02517   0.01508  -0.1280   0.7173   0.0634
  -4.000   0.1649   0.02467   0.01460  -0.1281   0.7150   0.0683
  -3.750   0.1923   0.02418   0.01397  -0.1282   0.7132   0.0752
  -3.500   0.2197   0.02376   0.01354  -0.1284   0.7115   0.0828
  -3.250   0.2466   0.02340   0.01315  -0.1285   0.7094   0.0913
  -3.000   0.2711   0.02337   0.01310  -0.1285   0.7057   0.1012
  -2.750   0.2967   0.02318   0.01299  -0.1286   0.7027   0.1124
  -2.500   0.3232   0.02300   0.01283  -0.1288   0.7003   0.1259
  -2.250   0.3504   0.02281   0.01267  -0.1290   0.6982   0.1434
  -2.000   0.3783   0.02256   0.01248  -0.1293   0.6963   0.1698
  -1.750   0.4066   0.02216   0.01231  -0.1297   0.6947   0.2287
  -1.500   0.4309   0.02172   0.01251  -0.1299   0.6920   0.3907
  -1.250   0.4491   0.02157   0.01316  -0.1287   0.6882   0.6053
  -1.000   0.4641   0.02170   0.01363  -0.1258   0.6852   0.7272
  -0.750   0.4781   0.02184   0.01391  -0.1223   0.6826   0.8114
  -0.500   0.4959   0.02195   0.01398  -0.1197   0.6804   0.8728
  -0.250   0.5166   0.02194   0.01390  -0.1176   0.6787   0.9233
   0.000   0.5550   0.02179   0.01364  -0.1193   0.6774   0.9998
   0.250   0.5697   0.02293   0.01477  -0.1188   0.6718   0.9998
   0.500   0.5938   0.02346   0.01520  -0.1189   0.6684   0.9998
   0.750   0.6210   0.02377   0.01540  -0.1193   0.6658   0.9998
   1.000   0.6499   0.02398   0.01550  -0.1198   0.6639   0.9998
   1.250   0.6794   0.02418   0.01559  -0.1204   0.6623   0.9998
   2.250   0.7691   0.02690   0.01818  -0.1201   0.6481   0.9998
   2.500   0.7988   0.02706   0.01828  -0.1206   0.6465   0.9998
   2.750   0.8296   0.02714   0.01831  -0.1211   0.6452   0.9998
   3.250   0.8525   0.02998   0.02124  -0.1190   0.6329   0.9998
   3.500   0.8820   0.03010   0.02134  -0.1194   0.6313   0.9998
   3.750   0.9126   0.03015   0.02136  -0.1198   0.6299   0.9998
   4.250   0.9295   0.03334   0.02467  -0.1172   0.6166   0.9998
   4.500   0.9598   0.03334   0.02467  -0.1175   0.6152   0.9998
   4.750   0.9892   0.03340   0.02474  -0.1177   0.6135   0.9998
   5.250   0.9884   0.03781   0.02928  -0.1138   0.5965   0.9998
   5.500   1.0339   0.03637   0.02786  -0.1148   0.5984   0.9998
   6.000   1.0438   0.04017   0.03178  -0.1120   0.5824   0.9998
   6.500   1.0429   0.04489   0.03664  -0.1088   0.5626   0.9998
   6.750   1.1036   0.04180   0.03361  -0.1102   0.5685   0.9998
   7.250   1.1215   0.04463   0.03659  -0.1077   0.5525   0.9998
   7.750   1.1565   0.04567   0.03778  -0.1060   0.5397   0.9998
   8.250   1.1889   0.04673   0.03902  -0.1039   0.5251   0.9998
   8.750   1.2249   0.04719   0.03966  -0.1019   0.5100   0.9998
   9.250   1.2369   0.05016   0.04284  -0.0991   0.4865   0.9998
   9.500   1.2683   0.04888   0.04165  -0.0985   0.4806   0.9998
   9.750   1.2740   0.05046   0.04332  -0.0972   0.4673   0.9998
  10.000   1.2841   0.05156   0.04454  -0.0960   0.4543   0.9998
  10.250   1.2980   0.05227   0.04533  -0.0949   0.4412   0.9998
  10.500   1.3136   0.05277   0.04591  -0.0938   0.4267   0.9998
  10.750   1.3310   0.05304   0.04623  -0.0928   0.4106   0.9998
  11.000   1.3529   0.05272   0.04593  -0.0917   0.3918   0.9998
  11.250   1.3719   0.05270   0.04584  -0.0905   0.3677   0.9998
  11.500   1.3882   0.05289   0.04588  -0.0890   0.3390   0.9998
  11.750   1.3957   0.05413   0.04694  -0.0874   0.3094   0.9998
  12.000   1.3977   0.05610   0.04873  -0.0858   0.2816   0.9998
  12.250   1.3967   0.05856   0.05107  -0.0844   0.2559   0.9998
  12.500   1.3951   0.06118   0.05356  -0.0830   0.2330   0.9998
  12.750   1.3935   0.06392   0.05621  -0.0819   0.2122   0.9998
  13.000   1.3921   0.06671   0.05892  -0.0808   0.1939   0.9998
  13.250   1.3907   0.06956   0.06169  -0.0799   0.1777   0.9998
  13.500   1.3904   0.07236   0.06447  -0.0791   0.1629   0.9998
  13.750   1.3904   0.07519   0.06727  -0.0783   0.1500   0.9998
  14.000   1.3914   0.07794   0.07003  -0.0777   0.1381   0.9998
  14.250   1.3926   0.08069   0.07280  -0.0772   0.1277   0.9998
  14.500   1.3935   0.08350   0.07561  -0.0766   0.1188   0.9998
  14.750   1.3941   0.08639   0.07851  -0.0762   0.1108   0.9998
  15.000   1.3965   0.08909   0.08128  -0.0759   0.1033   0.9998
  15.250   1.3966   0.09210   0.08428  -0.0756   0.0972   0.9998
  15.500   1.3999   0.09471   0.08700  -0.0753   0.0911   0.9998
  15.750   1.4006   0.09768   0.09000  -0.0752   0.0860   0.9998
  16.000   1.4032   0.10041   0.09279  -0.0751   0.0812   0.9998
  16.250   1.4056   0.10320   0.09568  -0.0751   0.0767   0.9998
<< Back to AH 94-145 (ah94145-il)

Polar data table (+)

Polar graphs


<< Back to AH 94-145 (ah94145-il)