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AH 82-150 A (ah82150a-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: AH 82-150 A (ah82150a-il)
Reynolds number: 100,000
Max Cl/Cd: 42.5 at α=9.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-ah82150a-il-100000.txt
Download as CSV file: xf-ah82150a-il-100000.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 =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.2600   0.10319   0.09914  -0.0698   0.9649   0.1237
  -9.750  -0.2287   0.09926   0.09516  -0.0687   0.9621   0.1312
  -9.500  -0.2453   0.09482   0.09077  -0.0734   0.9592   0.1377
  -9.250  -0.2242   0.09011   0.08603  -0.0745   0.9574   0.1435
  -9.000  -0.3369   0.09551   0.09130  -0.0688   0.9703   0.1305
  -8.750  -0.3503   0.09197   0.08781  -0.0721   0.9632   0.1363
  -8.500  -0.3863   0.08680   0.08267  -0.0801   0.9556   0.1379
  -8.250  -0.3544   0.08423   0.08010  -0.0772   0.9532   0.1492
  -8.000  -0.3845   0.08107   0.07697  -0.0789   0.9455   0.1504
  -7.750  -0.4233   0.07874   0.07457  -0.0782   0.9364   0.1520
  -7.500  -0.4057   0.07567   0.07154  -0.0771   0.9333   0.1620
  -7.250  -0.4438   0.07352   0.06915  -0.0774   0.9261   0.1673
  -6.000  -0.4501   0.04801   0.04110  -0.0703   0.9044   0.0829
  -5.750  -0.4259   0.04490   0.03766  -0.0704   0.9018   0.0792
  -5.500  -0.3957   0.04250   0.03460  -0.0714   0.8995   0.0807
  -5.250  -0.3885   0.04104   0.03280  -0.0684   0.8954   0.0810
  -5.000  -0.3692   0.03929   0.03066  -0.0672   0.8919   0.0813
  -4.750  -0.3442   0.03699   0.02818  -0.0675   0.8893   0.0843
  -4.500  -0.3131   0.03589   0.02696  -0.0685   0.8866   0.0899
  -4.250  -0.2823   0.03488   0.02565  -0.0689   0.8836   0.0937
  -4.000  -0.2718   0.03427   0.02489  -0.0662   0.8795   0.0968
  -3.750  -0.2514   0.03360   0.02430  -0.0655   0.8764   0.1043
  -3.500  -0.2219   0.03294   0.02354  -0.0658   0.8731   0.1111
  -3.250  -0.1854   0.03228   0.02296  -0.0674   0.8703   0.1237
  -3.000  -0.1823   0.03209   0.02292  -0.0640   0.8660   0.1333
  -2.750  -0.1647   0.03173   0.02263  -0.0628   0.8620   0.1530
  -2.500  -0.1401   0.02979   0.02205  -0.0635   0.8587   0.3416
  -2.250  -0.1430   0.03096   0.02476  -0.0533   0.8556   0.7638
  -2.000  -0.1542   0.03174   0.02551  -0.0458   0.8505   0.7909
  -1.750  -0.1522   0.03248   0.02618  -0.0396   0.8462   0.8195
  -1.500  -0.1450   0.03312   0.02674  -0.0337   0.8425   0.8493
  -1.250  -0.1482   0.03351   0.02705  -0.0273   0.8378   0.8735
  -1.000   0.1383   0.03581   0.02869  -0.0669   0.8374   0.9777
  -0.750   0.1641   0.03607   0.02883  -0.0681   0.8319   0.9839
  -0.500   0.2137   0.03606   0.02867  -0.0731   0.8283   0.9870
  -0.250   0.2302   0.03649   0.02904  -0.0728   0.8220   0.9912
   0.000   0.2544   0.03678   0.02925  -0.0736   0.8163   0.9944
   0.250   0.3019   0.03677   0.02913  -0.0779   0.8128   0.9962
   0.500   0.3030   0.03748   0.02982  -0.0753   0.8044   0.9998
   0.750   0.3317   0.03760   0.02988  -0.0761   0.7994   1.0000
   1.000   0.3222   0.03826   0.03053  -0.0711   0.7910   1.0000
   1.250   0.3452   0.03842   0.03064  -0.0709   0.7853   1.0000
   1.500   0.3403   0.03900   0.03122  -0.0666   0.7769   1.0000
   1.750   0.3613   0.03917   0.03135  -0.0661   0.7708   1.0000
   2.000   0.3568   0.03970   0.03188  -0.0618   0.7620   1.0000
   2.250   0.3803   0.03981   0.03197  -0.0615   0.7561   1.0000
   2.500   0.3717   0.04036   0.03252  -0.0567   0.7466   1.0000
   2.750   0.3987   0.04041   0.03254  -0.0568   0.7412   1.0000
   3.000   0.3858   0.04095   0.03309  -0.0514   0.7309   1.0000
   3.250   0.4192   0.04086   0.03299  -0.0522   0.7261   1.0000
   3.500   0.4022   0.04136   0.03350  -0.0463   0.7150   1.0000
   3.750   0.4393   0.04121   0.03335  -0.0475   0.7111   1.0000
   4.000   0.4236   0.04171   0.03386  -0.0420   0.6994   1.0000
   4.250   0.4625   0.04158   0.03374  -0.0434   0.6955   1.0000
   4.500   0.4647   0.04223   0.03441  -0.0410   0.6842   1.0000
   4.750   0.4772   0.04298   0.03519  -0.0401   0.6741   1.0000
   5.000   0.5165   0.04286   0.03512  -0.0418   0.6693   1.0000
   5.250   0.5299   0.04375   0.03604  -0.0413   0.6584   1.0000
   5.500   0.5727   0.04346   0.03584  -0.0433   0.6545   1.0000
   5.750   0.5858   0.04446   0.03689  -0.0429   0.6430   1.0000
   6.000   0.6310   0.04396   0.03648  -0.0449   0.6398   1.0000
   6.250   0.6438   0.04505   0.03763  -0.0445   0.6279   1.0000
   6.500   0.6913   0.04428   0.03700  -0.0465   0.6252   1.0000
   6.750   0.7036   0.04541   0.03821  -0.0461   0.6129   1.0000
   7.000   0.7508   0.04447   0.03741  -0.0479   0.6101   1.0000
   7.250   0.7654   0.04547   0.03853  -0.0475   0.5982   1.0000
   7.500   0.7805   0.04650   0.03966  -0.0472   0.5865   1.0000
   7.750   0.8288   0.04514   0.03848  -0.0488   0.5835   1.0000
   8.250   0.8704   0.04623   0.03987  -0.0485   0.5627   1.0000
   8.500   0.9554   0.04112   0.03510  -0.0512   0.5679   1.0000
   8.750   1.0919   0.02763   0.02199  -0.0537   0.5530   1.0000
   9.000   1.1039   0.02673   0.02113  -0.0507   0.5207   1.0000
   9.250   1.1173   0.02629   0.02060  -0.0481   0.4771   1.0000
   9.500   1.1226   0.02685   0.02090  -0.0450   0.4200   1.0000
   9.750   1.1089   0.02894   0.02242  -0.0407   0.3355   1.0000
  10.000   1.0848   0.03232   0.02507  -0.0365   0.2338   1.0000
  10.250   1.0585   0.03645   0.02831  -0.0330   0.1310   1.0000
  10.500   1.0419   0.04023   0.03152  -0.0304   0.0819   1.0000
  10.750   1.0364   0.04325   0.03443  -0.0287   0.0670   1.0000
  11.000   1.0347   0.04600   0.03720  -0.0273   0.0608   1.0000
  11.250   1.0371   0.04842   0.03974  -0.0262   0.0564   1.0000
  11.500   1.0378   0.05101   0.04232  -0.0250   0.0530   1.0000
  11.750   1.0473   0.05285   0.04419  -0.0237   0.0504   1.0000
  12.000   1.0631   0.05426   0.04567  -0.0228   0.0470   1.0000
  12.250   1.0815   0.05559   0.04695  -0.0220   0.0437   1.0000
  12.500   1.1445   0.05580   0.04699  -0.0217   0.0409   1.0000
  12.750   1.1893   0.05762   0.04908  -0.0218   0.0402   1.0000
  13.000   1.2272   0.06057   0.05234  -0.0221   0.0401   1.0000
  13.250   1.2429   0.06387   0.05597  -0.0214   0.0400   1.0000
  13.500   1.2474   0.06729   0.05973  -0.0204   0.0398   1.0000
  13.750   1.2447   0.07078   0.06354  -0.0193   0.0395   1.0000
  14.000   1.2405   0.07468   0.06774  -0.0183   0.0396   1.0000
  14.250   1.2304   0.07871   0.07207  -0.0174   0.0396   1.0000
  14.500   1.2200   0.08318   0.07682  -0.0169   0.0398   1.0000
  14.750   1.2073   0.08792   0.08182  -0.0167   0.0401   1.0000
  15.000   1.1959   0.09327   0.08739  -0.0170   0.0406   1.0000
  15.250   1.1972   0.09863   0.09295  -0.0174   0.0416   1.0000
  15.500   1.1755   0.10250   0.09709  -0.0180   0.0421   1.0000
  15.750   1.1445   0.10819   0.10310  -0.0200   0.0428   1.0000
  16.000   1.1041   0.11619   0.11143  -0.0240   0.0434   1.0000
  16.250   1.0533   0.12791   0.12349  -0.0312   0.0449   1.0000
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