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AH 94-145 (ah94145-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: AH 94-145 (ah94145-il)
Reynolds number: 200,000
Max Cl/Cd: 81.3 at α=8°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-ah94145-il-200000-n5.txt
Download as CSV file: xf-ah94145-il-200000-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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.1891   0.08954   0.08472  -0.0710   0.7215   0.0229
  -9.250  -0.1884   0.08487   0.08007  -0.0740   0.7195   0.0230
  -9.000  -0.1873   0.08034   0.07555  -0.0770   0.7175   0.0229
  -8.750  -0.1873   0.07545   0.07067  -0.0806   0.7155   0.0228
  -8.500  -0.1896   0.06974   0.06498  -0.0854   0.7135   0.0226
  -8.250  -0.1977   0.06184   0.05708  -0.0949   0.7116   0.0224
  -8.000  -0.2405   0.03563   0.02978  -0.1173   0.7103   0.0222
  -7.750  -0.2300   0.02895   0.02215  -0.1198   0.7081   0.0229
  -7.500  -0.2080   0.02626   0.01894  -0.1207   0.7058   0.0239
  -7.250  -0.1822   0.02556   0.01818  -0.1212   0.7036   0.0246
  -7.000  -0.1563   0.02454   0.01697  -0.1217   0.7016   0.0256
  -6.750  -0.1302   0.02316   0.01529  -0.1221   0.6996   0.0266
  -6.500  -0.1036   0.02182   0.01360  -0.1224   0.6977   0.0276
  -6.250  -0.0766   0.02088   0.01250  -0.1228   0.6959   0.0285
  -6.000  -0.0492   0.02027   0.01180  -0.1231   0.6942   0.0296
  -5.750  -0.0214   0.01970   0.01112  -0.1234   0.6921   0.0313
  -5.500   0.0065   0.01906   0.01035  -0.1237   0.6900   0.0333
  -5.250   0.0344   0.01863   0.00992  -0.1242   0.6880   0.0351
  -5.000   0.0625   0.01813   0.00934  -0.1245   0.6859   0.0373
  -4.750   0.0907   0.01766   0.00880  -0.1248   0.6838   0.0399
  -4.500   0.1192   0.01737   0.00847  -0.1251   0.6818   0.0433
  -4.250   0.1477   0.01699   0.00803  -0.1255   0.6801   0.0470
  -4.000   0.1764   0.01673   0.00772  -0.1258   0.6786   0.0516
  -3.750   0.2052   0.01648   0.00744  -0.1262   0.6772   0.0569
  -3.500   0.2338   0.01630   0.00724  -0.1266   0.6750   0.0631
  -3.250   0.2623   0.01608   0.00707  -0.1271   0.6728   0.0702
  -3.000   0.2911   0.01588   0.00688  -0.1275   0.6705   0.0781
  -2.750   0.3199   0.01576   0.00671  -0.1279   0.6684   0.0869
  -2.500   0.3489   0.01556   0.00654  -0.1284   0.6666   0.0971
  -2.250   0.3781   0.01540   0.00639  -0.1289   0.6650   0.1089
  -2.000   0.4074   0.01524   0.00625  -0.1294   0.6635   0.1251
  -1.750   0.4368   0.01507   0.00613  -0.1300   0.6620   0.1512
  -1.500   0.4661   0.01483   0.00609  -0.1307   0.6602   0.2066
  -1.250   0.4949   0.01445   0.00616  -0.1316   0.6577   0.3288
  -1.000   0.5236   0.01398   0.00629  -0.1324   0.6555   0.5044
  -0.750   0.5500   0.01372   0.00646  -0.1322   0.6535   0.6412
  -0.500   0.5741   0.01363   0.00661  -0.1312   0.6514   0.7248
  -0.250   0.5959   0.01361   0.00673  -0.1295   0.6495   0.7880
   0.000   0.6182   0.01365   0.00679  -0.1280   0.6478   0.8342
   0.250   0.6398   0.01371   0.00684  -0.1264   0.6463   0.8741
   0.500   0.6556   0.01373   0.00687  -0.1233   0.6449   0.9211
   0.750   0.6752   0.01370   0.00692  -0.1212   0.6423   0.9696
   1.000   0.7098   0.01378   0.00698  -0.1230   0.6397   0.9998
   1.250   0.7389   0.01394   0.00710  -0.1236   0.6373   0.9998
   1.500   0.7683   0.01409   0.00720  -0.1243   0.6352   0.9998
   1.750   0.7980   0.01423   0.00729  -0.1250   0.6334   0.9998
   2.000   0.8280   0.01436   0.00737  -0.1257   0.6318   0.9998
   2.250   0.8583   0.01447   0.00742  -0.1264   0.6302   0.9998
   2.500   0.8870   0.01468   0.00762  -0.1270   0.6280   0.9998
   2.750   0.9142   0.01497   0.00797  -0.1274   0.6250   0.9998
   3.000   0.9421   0.01521   0.00822  -0.1278   0.6223   0.9998
   3.250   0.9707   0.01539   0.00840  -0.1283   0.6199   0.9998
   3.500   0.9997   0.01553   0.00855  -0.1288   0.6178   0.9998
   3.750   1.0292   0.01565   0.00865  -0.1294   0.6160   0.9998
   4.000   1.0592   0.01575   0.00872  -0.1300   0.6143   0.9998
   4.250   1.0848   0.01610   0.00917  -0.1301   0.6111   0.9998
   4.500   1.1106   0.01641   0.00955  -0.1302   0.6077   0.9998
   4.750   1.1379   0.01661   0.00979  -0.1305   0.6047   0.9998
   5.000   1.1663   0.01672   0.00994  -0.1308   0.6022   0.9998
   5.250   1.1959   0.01676   0.00998  -0.1313   0.6000   0.9998
   5.500   1.2224   0.01697   0.01025  -0.1314   0.5966   0.9998
   5.750   1.2458   0.01729   0.01069  -0.1311   0.5915   0.9998
   6.000   1.2734   0.01730   0.01073  -0.1313   0.5873   0.9998
   6.250   1.3039   0.01707   0.01049  -0.1317   0.5832   0.9998
   6.500   1.3241   0.01736   0.01092  -0.1308   0.5747   0.9998
   6.750   1.3537   0.01705   0.01059  -0.1310   0.5685   0.9998
   7.000   1.3731   0.01736   0.01103  -0.1300   0.5587   0.9998
   7.250   1.3979   0.01737   0.01108  -0.1296   0.5506   0.9998
   7.500   1.4202   0.01752   0.01130  -0.1289   0.5412   0.9998
   7.750   1.4405   0.01779   0.01165  -0.1280   0.5312   0.9998
   8.000   1.4617   0.01798   0.01189  -0.1272   0.5209   0.9998
   8.250   1.4813   0.01823   0.01216  -0.1260   0.5090   0.9998
   8.500   1.4964   0.01864   0.01261  -0.1243   0.4944   0.9998
   8.750   1.5070   0.01921   0.01319  -0.1219   0.4768   0.9998
   9.000   1.5152   0.02001   0.01394  -0.1195   0.4540   0.9998
   9.250   1.5189   0.02116   0.01500  -0.1167   0.4263   0.9998
   9.500   1.5162   0.02289   0.01657  -0.1136   0.3944   0.9998
   9.750   1.5082   0.02523   0.01873  -0.1105   0.3619   0.9998
  10.000   1.4983   0.02794   0.02128  -0.1075   0.3312   0.9998
  10.250   1.4883   0.03081   0.02401  -0.1048   0.3028   0.9998
  10.500   1.4792   0.03370   0.02678  -0.1024   0.2770   0.9998
  10.750   1.4706   0.03661   0.02957  -0.1000   0.2530   0.9998
  11.000   1.4642   0.03939   0.03226  -0.0980   0.2308   0.9998
  11.250   1.4589   0.04213   0.03493  -0.0960   0.2107   0.9998
  11.500   1.4547   0.04488   0.03760  -0.0944   0.1923   0.9998
  11.750   1.4528   0.04750   0.04017  -0.0929   0.1753   0.9998
  12.000   1.4518   0.05009   0.04270  -0.0916   0.1597   0.9998
  12.250   1.4519   0.05264   0.04521  -0.0903   0.1460   0.9998
  12.500   1.4523   0.05520   0.04775  -0.0892   0.1337   0.9998
  12.750   1.4536   0.05771   0.05024  -0.0882   0.1225   0.9998
  13.000   1.4563   0.06011   0.05266  -0.0873   0.1128   0.9998
  13.250   1.4590   0.06255   0.05511  -0.0865   0.1044   0.9998
  13.500   1.4604   0.06517   0.05772  -0.0857   0.0968   0.9998
  13.750   1.4647   0.06750   0.06010  -0.0850   0.0899   0.9998
  14.000   1.4659   0.07019   0.06280  -0.0843   0.0840   0.9998
  14.250   1.4702   0.07255   0.06524  -0.0837   0.0782   0.9998
  14.750   1.4754   0.07779   0.07057  -0.0827   0.0687   0.9998
  15.000   1.4771   0.08055   0.07336  -0.0822   0.0646   0.9998
  15.250   1.4790   0.08330   0.07618  -0.0818   0.0610   0.9998
  15.500   1.4821   0.08593   0.07888  -0.0815   0.0573   0.9998
  15.750   1.4821   0.08900   0.08200  -0.0813   0.0543   0.9998
  16.000   1.4845   0.09176   0.08485  -0.0811   0.0517   0.9998
  16.250   1.4867   0.09459   0.08777  -0.0810   0.0489   0.9998
  16.500   1.4870   0.09769   0.09092  -0.0810   0.0466   0.9998
  16.750   1.4864   0.10092   0.09421  -0.0810   0.0447   0.9998
  17.000   1.4890   0.10374   0.09715  -0.0811   0.0426   0.9998
  17.250   1.4897   0.10685   0.10036  -0.0813   0.0407   0.9998
  17.500   1.4889   0.11022   0.10379  -0.0817   0.0391   0.9998
  17.750   1.4875   0.11368   0.10731  -0.0821   0.0377   0.9998
  18.000   1.4894   0.11668   0.11045  -0.0826   0.0362   0.9998
  18.250   1.4899   0.11992   0.11379  -0.0832   0.0347   0.9998
  18.500   1.4893   0.12335   0.11731  -0.0839   0.0335   0.9998
  18.750   1.4871   0.12704   0.12106  -0.0849   0.0324   0.9998
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