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USA 27 mod. AIRFOIL (usa27m2-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: USA 27 mod. AIRFOIL (usa27m2-il)
Reynolds number: 200,000
Max Cl/Cd: 64.37 at α=6.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-usa27m2-il-200000.txt
Download as CSV file: xf-usa27m2-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: USA 27 mod. AIRFOIL                             
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.3183   0.09886   0.09566  -0.0368   0.9904   0.0614
  -8.000  -0.3396   0.09300   0.08979  -0.0520   0.9787   0.0642
  -7.750  -0.3304   0.08686   0.08364  -0.0563   0.9737   0.0651
  -7.500  -0.3068   0.08443   0.08122  -0.0554   0.9721   0.0662
  -7.250  -0.2919   0.08186   0.07866  -0.0559   0.9662   0.0676
  -7.000  -0.2697   0.07799   0.07475  -0.0605   0.9604   0.0703
  -6.750  -0.2692   0.06932   0.06580  -0.0728   0.9475   0.0763
  -6.500  -0.2370   0.06655   0.06309  -0.0742   0.9450   0.0777
  -6.250  -0.2174   0.06443   0.06097  -0.0742   0.9367   0.0797
  -5.750  -0.1731   0.05578   0.05203  -0.0816   0.9217   0.0910
  -5.500  -0.1399   0.05327   0.04948  -0.0842   0.9172   0.0951
  -5.250  -0.1075   0.04851   0.04446  -0.0892   0.9141   0.1047
  -5.000  -0.0930   0.04704   0.04299  -0.0874   0.9037   0.1079
  -4.750  -0.0611   0.04350   0.03923  -0.0906   0.9003   0.1190
  -4.500  -0.0242   0.04061   0.03610  -0.0940   0.8983   0.1323
  -4.250  -0.0095   0.03930   0.03484  -0.0916   0.8875   0.1352
  -4.000   0.0135   0.02774   0.02116  -0.0899   0.8835   0.0754
  -3.750   0.0320   0.02441   0.01724  -0.0873   0.8740   0.0651
  -3.500   0.0711   0.02242   0.01511  -0.0891   0.8701   0.0627
  -3.250   0.1133   0.02058   0.01304  -0.0914   0.8671   0.0609
  -3.000   0.1385   0.01953   0.01183  -0.0902   0.8567   0.0600
  -2.750   0.1801   0.01828   0.01043  -0.0923   0.8516   0.0594
  -2.500   0.2075   0.01748   0.00957  -0.0917   0.8407   0.0594
  -2.250   0.2480   0.01658   0.00862  -0.0938   0.8341   0.0609
  -2.000   0.2736   0.01601   0.00803  -0.0928   0.8210   0.0621
  -1.750   0.3019   0.01543   0.00742  -0.0925   0.8082   0.0627
  -1.500   0.3309   0.01490   0.00686  -0.0923   0.7948   0.0635
  -1.250   0.3587   0.01447   0.00638  -0.0918   0.7799   0.0646
  -1.000   0.3842   0.01402   0.00589  -0.0910   0.7636   0.0669
  -0.750   0.4099   0.01374   0.00552  -0.0902   0.7462   0.0703
  -0.500   0.4355   0.01353   0.00520  -0.0894   0.7279   0.0755
  -0.250   0.4581   0.01297   0.00493  -0.0881   0.7093   0.1463
   0.000   0.4815   0.01273   0.00496  -0.0870   0.6901   0.2683
   0.250   0.5064   0.01274   0.00493  -0.0862   0.6707   0.3168
   0.500   0.5290   0.01278   0.00491  -0.0850   0.6506   0.3494
   0.750   0.5504   0.01280   0.00489  -0.0835   0.6308   0.3823
   1.000   0.5691   0.01267   0.00484  -0.0817   0.6119   0.4353
   1.250   0.7506   0.01262   0.00569  -0.1132   0.5717   1.0000
   1.500   0.7698   0.01284   0.00574  -0.1115   0.5533   1.0000
   1.750   0.7887   0.01305   0.00580  -0.1097   0.5360   1.0000
   2.000   0.8074   0.01326   0.00586  -0.1079   0.5199   1.0000
   2.250   0.8260   0.01347   0.00594  -0.1061   0.5051   1.0000
   2.500   0.8450   0.01369   0.00605  -0.1044   0.4921   1.0000
   2.750   0.8644   0.01394   0.00617  -0.1028   0.4813   1.0000
   3.000   0.8841   0.01420   0.00630  -0.1012   0.4717   1.0000
   3.250   0.9043   0.01445   0.00648  -0.0998   0.4630   1.0000
   3.500   0.9248   0.01473   0.00665  -0.0984   0.4552   1.0000
   3.750   0.9454   0.01500   0.00685  -0.0971   0.4478   1.0000
   4.000   0.9655   0.01526   0.00706  -0.0956   0.4404   1.0000
   4.250   0.9868   0.01557   0.00728  -0.0945   0.4338   1.0000
   4.500   1.0066   0.01581   0.00752  -0.0930   0.4274   1.0000
   4.750   1.0285   0.01612   0.00775  -0.0919   0.4221   1.0000
   5.000   1.0501   0.01644   0.00804  -0.0908   0.4167   1.0000
   5.250   1.0690   0.01668   0.00831  -0.0892   0.4107   1.0000
   5.500   1.0905   0.01699   0.00856  -0.0881   0.4055   1.0000
   5.750   1.1130   0.01734   0.00889  -0.0872   0.4008   1.0000
   6.000   1.1314   0.01760   0.00920  -0.0855   0.3958   1.0000
   6.250   1.1516   0.01789   0.00949  -0.0841   0.3909   1.0000
   6.500   1.1765   0.01831   0.00980  -0.0838   0.3860   1.0000
   6.750   1.1915   0.01853   0.01016  -0.0814   0.3810   1.0000
   7.000   1.2096   0.01880   0.01046  -0.0797   0.3758   1.0000
   7.250   1.2313   0.01915   0.01076  -0.0787   0.3709   1.0000
   7.500   1.2492   0.01948   0.01117  -0.0770   0.3661   1.0000
   7.750   1.2649   0.01975   0.01151  -0.0748   0.3608   1.0000
   8.000   1.2831   0.02004   0.01178  -0.0731   0.3553   1.0000
   8.250   1.2975   0.02034   0.01213  -0.0707   0.3491   1.0000
   8.500   1.3077   0.02053   0.01237  -0.0675   0.3420   1.0000
   8.750   1.3217   0.02082   0.01263  -0.0651   0.3349   1.0000
   9.000   1.3263   0.02100   0.01293  -0.0608   0.3279   1.0000
   9.250   1.3384   0.02129   0.01316  -0.0580   0.3212   1.0000
   9.500   1.3451   0.02158   0.01358  -0.0544   0.3140   1.0000
   9.750   1.3540   0.02189   0.01391  -0.0512   0.3064   1.0000
  10.000   1.3616   0.02227   0.01438  -0.0480   0.2979   1.0000
  10.250   1.3702   0.02269   0.01479  -0.0451   0.2896   1.0000
  10.500   1.3789   0.02317   0.01539  -0.0423   0.2805   1.0000
  10.750   1.3878   0.02376   0.01594  -0.0397   0.2724   1.0000
  11.000   1.3967   0.02435   0.01668  -0.0373   0.2623   1.0000
  11.250   1.4044   0.02506   0.01743  -0.0348   0.2519   1.0000
  11.500   1.4108   0.02591   0.01826  -0.0323   0.2418   1.0000
  11.750   1.4182   0.02681   0.01921  -0.0301   0.2305   1.0000
  12.000   1.4253   0.02782   0.02025  -0.0280   0.2198   1.0000
  12.250   1.4302   0.02901   0.02146  -0.0259   0.2092   1.0000
  12.500   1.4324   0.03046   0.02288  -0.0237   0.1984   1.0000
  12.750   1.4351   0.03199   0.02442  -0.0217   0.1882   1.0000
  13.000   1.4373   0.03364   0.02609  -0.0198   0.1788   1.0000
  13.250   1.4354   0.03569   0.02812  -0.0178   0.1694   1.0000
  13.500   1.4351   0.03774   0.03021  -0.0162   0.1598   1.0000
  13.750   1.4365   0.03977   0.03231  -0.0150   0.1508   1.0000
  14.000   1.4341   0.04227   0.03483  -0.0137   0.1417   1.0000
  14.250   1.4331   0.04478   0.03739  -0.0128   0.1290   1.0000
  14.500   1.4303   0.04760   0.04023  -0.0121   0.1106   1.0000
  14.750   1.4144   0.05197   0.04450  -0.0116   0.0889   1.0000
  15.000   1.3932   0.05716   0.04960  -0.0113   0.0705   1.0000
  15.250   1.3668   0.06318   0.05555  -0.0115   0.0476   1.0000
  15.500   1.3443   0.06901   0.06137  -0.0119   0.0401   1.0000
  15.750   1.3284   0.07420   0.06664  -0.0126   0.0373   1.0000
  16.000   1.3141   0.07936   0.07191  -0.0135   0.0353   1.0000
  16.250   1.3019   0.08438   0.07706  -0.0145   0.0340   1.0000
  16.500   1.2899   0.08946   0.08228  -0.0156   0.0331   1.0000
  16.750   1.2772   0.09473   0.08768  -0.0169   0.0323   1.0000
  17.000   1.2637   0.10020   0.09329  -0.0184   0.0317   1.0000
  17.250   1.2499   0.10583   0.09906  -0.0201   0.0311   1.0000
  17.500   1.2357   0.11158   0.10494  -0.0219   0.0306   1.0000
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