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AH 82-150 A (ah82150a-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: AH 82-150 A (ah82150a-il)
Reynolds number: 500,000
Max Cl/Cd: 108.69 at α=6°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-ah82150a-il-500000.txt
Download as CSV file: xf-ah82150a-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: AH 82-150 A                                     
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -11.500  -0.2227   0.08645   0.08382  -0.1069   0.8955   0.0250
 -11.250  -0.2240   0.08101   0.07831  -0.1106   0.8847   0.0250
 -11.000  -0.3195   0.05348   0.05059  -0.1265   0.8715   0.0170
 -10.750  -0.3500   0.04807   0.04498  -0.1277   0.8607   0.0168
 -10.500  -0.3750   0.04407   0.04078  -0.1269   0.8520   0.0166
 -10.250  -0.4069   0.03975   0.03617  -0.1240   0.8434   0.0166
 -10.000  -0.4337   0.03654   0.03271  -0.1195   0.8362   0.0166
  -9.750  -0.4513   0.03295   0.02875  -0.1155   0.8301   0.0165
  -9.500  -0.4579   0.02956   0.02494  -0.1123   0.8253   0.0166
  -9.250  -0.4539   0.02700   0.02204  -0.1100   0.8206   0.0170
  -9.000  -0.4420   0.02524   0.01996  -0.1083   0.8166   0.0174
  -8.750  -0.4253   0.02412   0.01858  -0.1072   0.8132   0.0177
  -8.500  -0.4135   0.02108   0.01524  -0.1058   0.8099   0.0188
  -8.250  -0.3919   0.02076   0.01490  -0.1053   0.8063   0.0198
  -8.000  -0.3699   0.02017   0.01421  -0.1048   0.8029   0.0208
  -7.750  -0.3472   0.01935   0.01323  -0.1043   0.7998   0.0220
  -7.500  -0.3233   0.01866   0.01237  -0.1039   0.7971   0.0232
  -7.250  -0.2993   0.01831   0.01191  -0.1035   0.7942   0.0239
  -7.000  -0.2786   0.01641   0.00992  -0.1028   0.7911   0.0260
  -6.750  -0.2544   0.01600   0.00948  -0.1025   0.7881   0.0277
  -6.500  -0.2291   0.01575   0.00915  -0.1023   0.7853   0.0299
  -6.250  -0.2034   0.01548   0.00878  -0.1022   0.7829   0.0315
  -6.000  -0.1818   0.01448   0.00773  -0.1014   0.7801   0.0337
  -5.750  -0.1584   0.01401   0.00726  -0.1010   0.7771   0.0364
  -5.500  -0.1334   0.01369   0.00691  -0.1008   0.7743   0.0390
  -5.250  -0.1081   0.01337   0.00651  -0.1006   0.7717   0.0412
  -5.000  -0.0833   0.01299   0.00605  -0.1003   0.7694   0.0433
  -4.750  -0.0602   0.01246   0.00552  -0.0999   0.7669   0.0476
  -4.500  -0.0352   0.01217   0.00523  -0.0996   0.7640   0.0513
  -4.250  -0.0091   0.01197   0.00497  -0.0996   0.7612   0.0544
  -4.000   0.0158   0.01155   0.00457  -0.0994   0.7587   0.0623
  -3.750   0.0422   0.01127   0.00427  -0.0994   0.7564   0.0730
  -3.500   0.0679   0.01087   0.00400  -0.0995   0.7541   0.1104
  -3.250   0.0901   0.01004   0.00375  -0.0994   0.7515   0.2532
  -3.000   0.1110   0.00869   0.00336  -0.0996   0.7487   0.5071
  -2.750   0.1358   0.00844   0.00365  -0.0991   0.7460   0.6751
  -2.500   0.1647   0.00858   0.00372  -0.0993   0.7435   0.6995
  -2.250   0.1934   0.00876   0.00384  -0.0994   0.7413   0.7150
  -2.000   0.2225   0.00900   0.00399  -0.0996   0.7391   0.7276
  -1.750   0.2492   0.00913   0.00417  -0.0993   0.7364   0.7348
  -1.500   0.2761   0.00936   0.00439  -0.0990   0.7335   0.7462
  -1.250   0.3011   0.00978   0.00486  -0.0978   0.7308   0.7620
  -1.000   0.3288   0.01003   0.00506  -0.0976   0.7283   0.7720
  -0.750   0.3549   0.01019   0.00523  -0.0969   0.7259   0.7775
  -0.500   0.3820   0.01037   0.00539  -0.0967   0.7232   0.7843
  -0.250   0.4092   0.01036   0.00538  -0.0967   0.7198   0.7879
   0.000   0.4371   0.01032   0.00532  -0.0969   0.7164   0.7893
   0.250   0.4659   0.01027   0.00523  -0.0973   0.7134   0.7906
   0.500   0.4955   0.01027   0.00516  -0.0979   0.7105   0.7918
   0.750   0.5227   0.01023   0.00515  -0.0980   0.7067   0.7933
   1.000   0.5510   0.01019   0.00510  -0.0984   0.7030   0.7946
   1.250   0.5803   0.01014   0.00502  -0.0989   0.6997   0.7958
   1.500   0.6101   0.01013   0.00497  -0.0996   0.6969   0.7971
   1.750   0.6384   0.01013   0.00498  -0.1000   0.6934   0.7986
   2.000   0.6667   0.01010   0.00496  -0.1005   0.6895   0.7997
   2.250   0.6961   0.01008   0.00493  -0.1011   0.6859   0.8007
   2.500   0.7253   0.01004   0.00487  -0.1016   0.6827   0.8016
   2.750   0.7524   0.01003   0.00490  -0.1017   0.6787   0.8026
   3.000   0.7797   0.01001   0.00491  -0.1019   0.6743   0.8038
   3.250   0.8081   0.00999   0.00491  -0.1022   0.6704   0.8048
   3.500   0.8369   0.01000   0.00492  -0.1026   0.6666   0.8058
   3.750   0.8634   0.01000   0.00499  -0.1027   0.6616   0.8069
   4.000   0.8913   0.00998   0.00501  -0.1029   0.6569   0.8080
   4.250   0.9200   0.01000   0.00502  -0.1033   0.6526   0.8091
   4.500   0.9461   0.01000   0.00510  -0.1033   0.6465   0.8104
   4.750   0.9738   0.01000   0.00512  -0.1035   0.6409   0.8120
   5.000   1.0006   0.01002   0.00520  -0.1035   0.6344   0.8134
   5.250   1.0271   0.01000   0.00518  -0.1035   0.6253   0.8146
   5.500   1.0510   0.00996   0.00517  -0.1029   0.6113   0.8157
   5.750   1.0728   0.00995   0.00518  -0.1018   0.5915   0.8169
   6.000   1.0923   0.01005   0.00524  -0.1003   0.5643   0.8182
   6.250   1.1090   0.01032   0.00539  -0.0984   0.5299   0.8197
   6.500   1.1222   0.01075   0.00567  -0.0958   0.4904   0.8213
   6.750   1.1307   0.01135   0.00607  -0.0925   0.4470   0.8232
   7.000   1.1327   0.01209   0.00659  -0.0881   0.4009   0.8257
   7.250   1.1297   0.01293   0.00719  -0.0828   0.3560   0.8282
   7.500   1.1221   0.01410   0.00806  -0.0772   0.3005   0.8304
   7.750   1.1079   0.01567   0.00927  -0.0711   0.2327   0.8329
   8.000   1.0882   0.01782   0.01094  -0.0648   0.1509   0.8358
   8.250   1.0667   0.02043   0.01304  -0.0590   0.0647   0.8388
   8.500   1.0605   0.02243   0.01477  -0.0554   0.0235   0.8415
   8.750   1.0709   0.02350   0.01589  -0.0538   0.0200   0.8438
   9.000   1.0793   0.02467   0.01714  -0.0519   0.0177   0.8462
   9.250   1.0883   0.02583   0.01841  -0.0502   0.0167   0.8489
   9.500   1.0987   0.02695   0.01961  -0.0487   0.0160   0.8519
   9.750   1.1077   0.02821   0.02096  -0.0472   0.0153   0.8550
  10.000   1.1165   0.02953   0.02235  -0.0459   0.0145   0.8580
  10.250   1.1232   0.03098   0.02389  -0.0443   0.0136   0.8610
  10.500   1.1272   0.03267   0.02566  -0.0426   0.0130   0.8645
  10.750   1.1226   0.03516   0.02827  -0.0404   0.0124   0.8684
  11.000   1.1253   0.03720   0.03040  -0.0389   0.0121   0.8723
  11.250   1.1343   0.03864   0.03195  -0.0378   0.0119   0.8766
  11.500   1.1412   0.04033   0.03374  -0.0367   0.0117   0.8817
  11.750   1.1482   0.04209   0.03560  -0.0356   0.0115   0.8876
  12.000   1.1550   0.04380   0.03743  -0.0344   0.0111   0.8952
  12.250   1.1620   0.04548   0.03922  -0.0332   0.0109   0.9060
  12.500   1.1692   0.04709   0.04100  -0.0319   0.0107   0.9306
  12.750   1.1799   0.04880   0.04283  -0.0315   0.0104   1.0000
  13.000   1.1920   0.05052   0.04462  -0.0309   0.0103   1.0000
  13.250   1.2048   0.05222   0.04639  -0.0304   0.0100   1.0000
  13.500   1.2183   0.05391   0.04816  -0.0300   0.0099   1.0000
  13.750   1.2293   0.05578   0.05009  -0.0297   0.0096   1.0000
  14.000   1.2414   0.05767   0.05207  -0.0293   0.0094   1.0000
  14.250   1.2529   0.05969   0.05414  -0.0290   0.0091   1.0000
  14.500   1.2690   0.06186   0.05640  -0.0286   0.0088   1.0000
  14.750   1.2777   0.06446   0.05918  -0.0282   0.0089   1.0000
  15.000   1.2833   0.06745   0.06234  -0.0279   0.0089   1.0000
  15.250   1.2852   0.07081   0.06589  -0.0277   0.0089   1.0000
  15.500   1.2824   0.07432   0.06959  -0.0277   0.0090   1.0000
  15.750   1.1143   0.08742   0.08361  -0.0303   0.0094   0.8967
  16.000   1.0684   0.09674   0.09352  -0.0331   0.0105   0.8907
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