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AH 95-160 (ah95160-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: AH 95-160 (ah95160-il)
Reynolds number: 500,000
Max Cl/Cd: 130.27 at α=8.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-ah95160-il-500000.txt
Download as CSV file: xf-ah95160-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: AH 95-160                                       
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.2011   0.09845   0.09487  -0.0693   0.7103   0.0320
 -10.250  -0.3986   0.04434   0.04057  -0.1096   0.7118   0.0228
 -10.000  -0.4396   0.03355   0.02898  -0.1156   0.7099   0.0225
  -9.750  -0.4357   0.02910   0.02395  -0.1165   0.7080   0.0228
  -9.500  -0.4193   0.02679   0.02119  -0.1168   0.7061   0.0232
  -9.250  -0.4013   0.02443   0.01853  -0.1171   0.7043   0.0237
  -9.000  -0.3775   0.02344   0.01746  -0.1173   0.7025   0.0242
  -8.750  -0.3530   0.02256   0.01643  -0.1175   0.7005   0.0247
  -8.500  -0.3279   0.02158   0.01532  -0.1177   0.6989   0.0252
  -8.250  -0.3024   0.02057   0.01416  -0.1180   0.6971   0.0258
  -8.000  -0.2764   0.01963   0.01304  -0.1181   0.6952   0.0265
  -7.750  -0.2497   0.01887   0.01210  -0.1183   0.6933   0.0271
  -7.500  -0.2239   0.01778   0.01091  -0.1185   0.6915   0.0279
  -7.250  -0.1966   0.01723   0.01034  -0.1188   0.6898   0.0288
  -7.000  -0.1688   0.01682   0.00986  -0.1190   0.6881   0.0299
  -6.750  -0.1408   0.01640   0.00933  -0.1193   0.6864   0.0311
  -6.500  -0.1136   0.01576   0.00859  -0.1195   0.6846   0.0324
  -6.250  -0.0858   0.01543   0.00826  -0.1197   0.6827   0.0337
  -6.000  -0.0573   0.01506   0.00786  -0.1200   0.6813   0.0354
  -5.750  -0.0292   0.01459   0.00734  -0.1203   0.6798   0.0372
  -5.500  -0.0007   0.01427   0.00705  -0.1207   0.6781   0.0394
  -5.250   0.0283   0.01409   0.00681  -0.1210   0.6763   0.0421
  -5.000   0.0567   0.01371   0.00647  -0.1214   0.6744   0.0453
  -4.750   0.0857   0.01352   0.00622  -0.1217   0.6726   0.0488
  -4.500   0.1145   0.01324   0.00597  -0.1221   0.6710   0.0531
  -4.250   0.1436   0.01303   0.00573  -0.1225   0.6695   0.0579
  -4.000   0.1728   0.01296   0.00564  -0.1229   0.6680   0.0630
  -3.750   0.2017   0.01283   0.00551  -0.1233   0.6663   0.0686
  -3.500   0.2310   0.01278   0.00545  -0.1237   0.6648   0.0741
  -3.250   0.2600   0.01252   0.00525  -0.1242   0.6631   0.0810
  -3.000   0.2893   0.01239   0.00512  -0.1246   0.6613   0.0874
  -2.750   0.3185   0.01222   0.00499  -0.1251   0.6595   0.0956
  -2.500   0.3479   0.01206   0.00485  -0.1256   0.6578   0.1048
  -2.250   0.3773   0.01194   0.00475  -0.1261   0.6562   0.1156
  -2.000   0.4068   0.01177   0.00463  -0.1266   0.6546   0.1338
  -1.750   0.4364   0.01152   0.00453  -0.1272   0.6530   0.1789
  -1.500   0.4657   0.01102   0.00447  -0.1281   0.6514   0.3156
  -1.250   0.4947   0.01054   0.00455  -0.1290   0.6496   0.5040
  -1.000   0.5232   0.01029   0.00468  -0.1294   0.6482   0.6232
  -0.750   0.5516   0.01019   0.00477  -0.1296   0.6465   0.6852
  -0.500   0.5799   0.01015   0.00486  -0.1297   0.6446   0.7283
  -0.250   0.6079   0.01014   0.00493  -0.1297   0.6427   0.7640
   0.000   0.6360   0.01015   0.00499  -0.1298   0.6408   0.7928
   0.250   0.6637   0.01016   0.00504  -0.1297   0.6391   0.8183
   0.500   0.6915   0.01019   0.00509  -0.1296   0.6375   0.8403
   0.750   0.7188   0.01024   0.00514  -0.1294   0.6360   0.8617
   1.000   0.7427   0.01029   0.00523  -0.1284   0.6344   0.8907
   1.250   0.7629   0.01039   0.00537  -0.1264   0.6326   0.9207
   1.500   0.7817   0.01036   0.00541  -0.1243   0.6307   0.9473
   1.750   0.8064   0.01034   0.00543  -0.1236   0.6287   0.9715
   2.000   0.8430   0.01036   0.00545  -0.1256   0.6267   0.9912
   2.250   0.8759   0.01042   0.00549  -0.1271   0.6247   0.9998
   2.500   0.9068   0.01048   0.00553  -0.1280   0.6227   0.9998
   2.750   0.9377   0.01056   0.00556  -0.1290   0.6210   0.9998
   3.000   0.9687   0.01064   0.00561  -0.1299   0.6193   0.9998
   3.250   0.9994   0.01081   0.00572  -0.1307   0.6174   0.9998
   3.500   1.0284   0.01095   0.00590  -0.1313   0.6154   0.9998
   3.750   1.0572   0.01106   0.00605  -0.1319   0.6130   0.9998
   4.000   1.0862   0.01116   0.00617  -0.1324   0.6105   0.9998
   4.250   1.1156   0.01123   0.00625  -0.1330   0.6082   0.9998
   4.500   1.1454   0.01126   0.00628  -0.1336   0.6059   0.9998
   4.750   1.1755   0.01130   0.00628  -0.1342   0.6036   0.9998
   5.000   1.2052   0.01141   0.00637  -0.1348   0.6010   0.9998
   5.250   1.2320   0.01145   0.00650  -0.1350   0.5972   0.9998
   5.500   1.2601   0.01142   0.00650  -0.1352   0.5931   0.9998
   5.750   1.2895   0.01133   0.00638  -0.1357   0.5890   0.9998
   6.000   1.3181   0.01131   0.00634  -0.1360   0.5846   0.9998
   6.250   1.3442   0.01129   0.00640  -0.1359   0.5788   0.9998
   6.500   1.3720   0.01123   0.00635  -0.1361   0.5736   0.9998
   6.750   1.3996   0.01129   0.00640  -0.1363   0.5689   0.9998
   7.000   1.4252   0.01136   0.00656  -0.1362   0.5632   0.9998
   7.250   1.4519   0.01140   0.00662  -0.1362   0.5579   0.9998
   7.500   1.4779   0.01151   0.00676  -0.1362   0.5524   0.9998
   7.750   1.5028   0.01162   0.00694  -0.1360   0.5455   0.9998
   8.000   1.5280   0.01174   0.00706  -0.1358   0.5389   0.9998
   8.250   1.5515   0.01191   0.00730  -0.1354   0.5301   0.9998
   8.500   1.5743   0.01211   0.00752  -0.1348   0.5206   0.9998
   8.750   1.5951   0.01236   0.00777  -0.1339   0.5090   0.9998
   9.000   1.6138   0.01270   0.00812  -0.1327   0.4953   0.9998
   9.250   1.6292   0.01316   0.00856  -0.1309   0.4793   0.9998
   9.500   1.6384   0.01376   0.00913  -0.1281   0.4601   0.9998
   9.750   1.6413   0.01474   0.01005  -0.1247   0.4368   0.9998
  10.000   1.6382   0.01624   0.01145  -0.1210   0.4092   0.9998
  10.250   1.6289   0.01845   0.01352  -0.1172   0.3793   0.9998
  10.500   1.6163   0.02124   0.01618  -0.1137   0.3497   0.9998
  10.750   1.6026   0.02435   0.01916  -0.1105   0.3224   0.9998
  11.000   1.5896   0.02748   0.02218  -0.1075   0.2965   0.9998
  11.250   1.5779   0.03055   0.02514  -0.1047   0.2732   0.9998
  11.500   1.5675   0.03354   0.02804  -0.1021   0.2514   0.9998
  11.750   1.5580   0.03650   0.03092  -0.0996   0.2315   0.9998
  12.000   1.5523   0.03925   0.03359  -0.0976   0.2123   0.9998
  12.250   1.5478   0.04197   0.03623  -0.0957   0.1946   0.9998
  12.500   1.5442   0.04467   0.03886  -0.0940   0.1786   0.9998
  12.750   1.5426   0.04723   0.04137  -0.0925   0.1640   0.9998
  13.000   1.5417   0.04979   0.04388  -0.0911   0.1510   0.9998
  13.250   1.5418   0.05227   0.04632  -0.0898   0.1393   0.9998
  13.500   1.5417   0.05482   0.04884  -0.0886   0.1287   0.9998
  13.750   1.5430   0.05727   0.05125  -0.0876   0.1191   0.9998
  14.000   1.5458   0.05961   0.05360  -0.0866   0.1109   0.9998
  14.250   1.5473   0.06208   0.05605  -0.0856   0.1035   0.9998
  14.500   1.5497   0.06450   0.05847  -0.0848   0.0967   0.9998
  14.750   1.5522   0.06694   0.06093  -0.0840   0.0907   0.9998
  15.000   1.5548   0.06939   0.06339  -0.0832   0.0849   0.9998
  15.250   1.5568   0.07195   0.06596  -0.0825   0.0799   0.9998
  15.500   1.5601   0.07434   0.06838  -0.0819   0.0751   0.9998
  15.750   1.5598   0.07720   0.07125  -0.0813   0.0708   0.9998
  16.000   1.5645   0.07950   0.07360  -0.0808   0.0669   0.9998
  16.250   1.5637   0.08248   0.07658  -0.0803   0.0632   0.9998
  16.500   1.5668   0.08501   0.07918  -0.0799   0.0600   0.9998
  16.750   1.5688   0.08768   0.08189  -0.0795   0.0569   0.9998
  17.000   1.5661   0.09095   0.08516  -0.0792   0.0541   0.9998
  17.250   1.5698   0.09346   0.08775  -0.0790   0.0517   0.9998
  17.500   1.5712   0.09629   0.09064  -0.0788   0.0493   0.9998
  17.750   1.5696   0.09952   0.09389  -0.0787   0.0472   0.9998
  18.000   1.5689   0.10267   0.09710  -0.0787   0.0453   0.9998
  18.250   1.5718   0.10533   0.09984  -0.0788   0.0435   0.9998
  18.500   1.5712   0.10848   0.10304  -0.0789   0.0419   0.9998
  18.750   1.5677   0.11203   0.10662  -0.0792   0.0402   0.9998
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