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AH 95-160 (ah95160-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: AH 95-160 (ah95160-il)
Reynolds number: 200,000
Max Cl/Cd: 65.45 at α=10°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-ah95160-il-200000.txt
Download as CSV file: xf-ah95160-il-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.1367   0.10266   0.09827  -0.0750   0.7725   0.0604
  -9.750  -0.1367   0.09910   0.09470  -0.0784   0.7707   0.0630
  -9.500  -0.1630   0.09248   0.08817  -0.0913   0.7688   0.0644
  -9.250  -0.1430   0.08967   0.08537  -0.0874   0.7667   0.0652
  -9.000  -0.1271   0.08756   0.08326  -0.0864   0.7643   0.0661
  -8.750  -0.1160   0.08507   0.08078  -0.0870   0.7617   0.0674
  -8.500  -0.1089   0.08207   0.07778  -0.0889   0.7592   0.0691
  -8.250  -0.1072   0.07808   0.07381  -0.0929   0.7570   0.0717
  -8.000  -0.1537   0.06567   0.06111  -0.1167   0.7546   0.0746
  -7.750  -0.1326   0.06301   0.05858  -0.1145   0.7529   0.0755
  -7.500  -0.1599   0.04690   0.04151  -0.1235   0.7512   0.0561
  -7.250  -0.1415   0.04426   0.03894  -0.1242   0.7487   0.0568
  -7.000  -0.1221   0.04248   0.03714  -0.1248   0.7460   0.0577
  -6.750  -0.1128   0.03527   0.02918  -0.1259   0.7435   0.0514
  -6.500  -0.0947   0.03111   0.02437  -0.1261   0.7412   0.0509
  -6.250  -0.0710   0.02920   0.02213  -0.1262   0.7391   0.0520
  -6.000  -0.0459   0.02770   0.02024  -0.1263   0.7374   0.0543
  -5.750  -0.0204   0.02622   0.01836  -0.1263   0.7357   0.0567
  -5.500   0.0055   0.02555   0.01768  -0.1265   0.7337   0.0589
  -5.250   0.0316   0.02490   0.01693  -0.1267   0.7307   0.0617
  -5.000   0.0579   0.02414   0.01598  -0.1268   0.7278   0.0656
  -4.750   0.0846   0.02374   0.01561  -0.1270   0.7254   0.0697
  -4.500   0.1124   0.02342   0.01507  -0.1270   0.7234   0.0744
  -4.250   0.1388   0.02271   0.01445  -0.1272   0.7215   0.0802
  -4.000   0.1667   0.02235   0.01395  -0.1272   0.7198   0.0865
  -3.750   0.1938   0.02190   0.01355  -0.1273   0.7182   0.0940
  -3.500   0.2192   0.02170   0.01335  -0.1273   0.7155   0.1018
  -3.250   0.2439   0.02174   0.01348  -0.1275   0.7122   0.1103
  -3.000   0.2694   0.02157   0.01338  -0.1276   0.7095   0.1198
  -2.750   0.2961   0.02146   0.01327  -0.1277   0.7072   0.1308
  -2.500   0.3237   0.02128   0.01311  -0.1279   0.7052   0.1444
  -2.250   0.3520   0.02096   0.01286  -0.1282   0.7034   0.1634
  -2.000   0.3803   0.02057   0.01266  -0.1286   0.7018   0.2008
  -1.750   0.4071   0.01951   0.01266  -0.1294   0.7003   0.4601
  -1.500   0.4229   0.01988   0.01381  -0.1281   0.6960   0.6586
  -1.250   0.4415   0.02035   0.01452  -0.1266   0.6924   0.7379
  -1.000   0.4619   0.02060   0.01486  -0.1249   0.6897   0.7919
  -0.750   0.4827   0.02071   0.01501  -0.1229   0.6876   0.8323
  -0.500   0.5031   0.02079   0.01507  -0.1208   0.6860   0.8671
  -0.250   0.5224   0.02087   0.01513  -0.1185   0.6846   0.8987
   0.000   0.5423   0.02098   0.01519  -0.1162   0.6833   0.9304
   0.250   0.5507   0.02281   0.01718  -0.1152   0.6752   0.9679
   0.500   0.5895   0.02309   0.01738  -0.1180   0.6726   0.9998
   0.750   0.6180   0.02333   0.01754  -0.1187   0.6707   0.9998
   1.000   0.6489   0.02345   0.01756  -0.1196   0.6692   0.9998
   1.250   0.6814   0.02347   0.01747  -0.1206   0.6681   0.9998
   1.500   0.7138   0.02349   0.01740  -0.1214   0.6669   0.9998
   1.750   0.7029   0.02689   0.02094  -0.1191   0.6558   0.9998
   2.000   0.7328   0.02701   0.02100  -0.1197   0.6539   0.9998
   2.250   0.7652   0.02693   0.02085  -0.1203   0.6527   0.9998
   2.500   0.7984   0.02680   0.02066  -0.1211   0.6516   0.9998
   2.750   0.8087   0.02858   0.02246  -0.1201   0.6463   0.9998
   3.000   0.8571   0.02727   0.02105  -0.1220   0.6485   0.9998
   3.250   0.7810   0.03554   0.02952  -0.1147   0.6251   0.9998
   3.500   0.8068   0.03589   0.02985  -0.1147   0.6224   0.9998
   3.750   0.8382   0.03576   0.02970  -0.1150   0.6209   0.9998
   4.000   0.8727   0.03536   0.02928  -0.1155   0.6200   0.9998
   4.250   0.8476   0.03975   0.03371  -0.1122   0.6070   0.9998
   4.500   0.8788   0.03960   0.03354  -0.1125   0.6053   0.9998
   4.750   0.9120   0.03925   0.03319  -0.1129   0.6042   0.9998
   5.000   0.8962   0.04285   0.03682  -0.1102   0.5926   0.9998
   5.250   0.9260   0.04273   0.03670  -0.1103   0.5904   0.9998
   5.500   0.9597   0.04223   0.03621  -0.1106   0.5890   0.9998
   5.750   0.9956   0.04151   0.03551  -0.1110   0.5881   0.9998
   6.000   1.0331   0.04060   0.03462  -0.1115   0.5875   0.9998
   6.250   1.0718   0.03952   0.03356  -0.1120   0.5871   0.9998
   6.500   1.1125   0.03817   0.03225  -0.1126   0.5870   0.9998
   6.750   1.1549   0.03657   0.03068  -0.1132   0.5869   0.9998
   7.000   1.2017   0.03468   0.02883  -0.1144   0.5869   0.9998
   7.250   1.2557   0.03237   0.02654  -0.1164   0.5869   0.9998
   7.500   1.3168   0.02971   0.02390  -0.1195   0.5868   0.9998
   7.750   1.3798   0.02686   0.02103  -0.1229   0.5861   0.9998
   8.000   1.3473   0.02979   0.02410  -0.1160   0.5738   0.9998
   8.250   1.4137   0.02690   0.02123  -0.1199   0.5730   0.9998
   8.500   1.4701   0.02478   0.01910  -0.1230   0.5710   0.9998
   8.750   1.4462   0.02688   0.02136  -0.1165   0.5604   0.9998
   9.000   1.5034   0.02473   0.01922  -0.1197   0.5573   0.9998
   9.250   1.4961   0.02594   0.02054  -0.1152   0.5484   0.9998
   9.500   1.5366   0.02455   0.01919  -0.1163   0.5426   0.9998
   9.750   1.5313   0.02586   0.02060  -0.1125   0.5326   0.9998
  10.000   1.5773   0.02410   0.01882  -0.1139   0.5250   0.9998
  10.250   1.5649   0.02603   0.02088  -0.1099   0.5123   0.9998
  10.500   1.5658   0.02742   0.02233  -0.1074   0.4987   0.9998
  10.750   1.5732   0.02844   0.02338  -0.1057   0.4836   0.9998
  11.000   1.5822   0.02938   0.02431  -0.1040   0.4662   0.9998
  11.250   1.5840   0.03098   0.02589  -0.1019   0.4458   0.9998
  11.500   1.5847   0.03268   0.02752  -0.0997   0.4214   0.9998
  11.750   1.5823   0.03464   0.02935  -0.0973   0.3934   0.9998
  12.000   1.5750   0.03703   0.03156  -0.0946   0.3639   0.9998
  12.250   1.5637   0.03987   0.03422  -0.0918   0.3352   0.9998
  12.500   1.5507   0.04304   0.03720  -0.0892   0.3081   0.9998
  12.750   1.5383   0.04637   0.04038  -0.0869   0.2823   0.9998
  13.000   1.5267   0.04976   0.04363  -0.0849   0.2587   0.9998
  13.250   1.5163   0.05318   0.04692  -0.0831   0.2366   0.9998
  13.500   1.5065   0.05663   0.05024  -0.0814   0.2173   0.9998
  13.750   1.4997   0.05989   0.05343  -0.0801   0.1992   0.9998
  14.000   1.4941   0.06309   0.05655  -0.0788   0.1833   0.9998
  14.250   1.4895   0.06624   0.05963  -0.0778   0.1695   0.9998
  14.500   1.4853   0.06937   0.06268  -0.0767   0.1575   0.9998
  14.750   1.4835   0.07230   0.06558  -0.0759   0.1464   0.9998
  15.000   1.4834   0.07509   0.06838  -0.0751   0.1365   0.9998
  15.250   1.4822   0.07799   0.07124  -0.0744   0.1282   0.9998
  15.500   1.4823   0.08081   0.07406  -0.0738   0.1202   0.9998
  15.750   1.4834   0.08348   0.07675  -0.0732   0.1131   0.9998
  16.000   1.4836   0.08628   0.07951  -0.0726   0.1068   0.9998
  16.250   1.4859   0.08886   0.08215  -0.0722   0.1007   0.9998
  16.500   1.4870   0.09162   0.08491  -0.0718   0.0954   0.9998
  16.750   1.4899   0.09406   0.08736  -0.0713   0.0904   0.9998
  17.000   1.4921   0.09678   0.09017  -0.0712   0.0858   0.9998
  17.250   1.4955   0.09895   0.09223  -0.0706   0.0815   0.9998
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