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USA 27 mod. AIRFOIL (usa27m2-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: USA 27 mod. AIRFOIL (usa27m2-il)
Reynolds number: 500,000
Max Cl/Cd: 84.98 at α=6.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-usa27m2-il-500000-n5.txt
Download as CSV file: xf-usa27m2-il-500000-n5.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 =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.2066   0.09177   0.08926  -0.0760   0.9795   0.0218
 -10.000  -0.2009   0.08699   0.08448  -0.0797   0.9766   0.0219
  -9.500  -0.2039   0.07333   0.07082  -0.0914   0.9692   0.0224
  -9.000  -0.3000   0.03821   0.03487  -0.1164   0.9371   0.0223
  -8.750  -0.2932   0.03442   0.03079  -0.1168   0.9315   0.0224
  -8.500  -0.2864   0.03204   0.02820  -0.1151   0.9232   0.0225
  -8.250  -0.2709   0.02990   0.02585  -0.1147   0.9178   0.0226
  -8.000  -0.2545   0.02830   0.02408  -0.1137   0.9106   0.0227
  -7.750  -0.2352   0.02682   0.02244  -0.1131   0.9026   0.0229
  -7.500  -0.2156   0.02560   0.02107  -0.1123   0.8935   0.0231
  -7.250  -0.1938   0.02436   0.01964  -0.1118   0.8843   0.0234
  -7.000  -0.1755   0.02312   0.01819  -0.1105   0.8741   0.0237
  -6.750  -0.1552   0.02176   0.01657  -0.1094   0.8652   0.0239
  -6.500  -0.1350   0.02058   0.01516  -0.1082   0.8555   0.0240
  -6.250  -0.1133   0.01953   0.01390  -0.1072   0.8467   0.0242
  -6.000  -0.0908   0.01859   0.01275  -0.1063   0.8365   0.0244
  -5.750  -0.0684   0.01777   0.01173  -0.1052   0.8250   0.0246
  -5.500  -0.0451   0.01703   0.01080  -0.1043   0.8134   0.0247
  -5.250  -0.0214   0.01636   0.00996  -0.1034   0.8023   0.0249
  -5.000   0.0023   0.01576   0.00922  -0.1026   0.7909   0.0251
  -4.750   0.0262   0.01522   0.00854  -0.1017   0.7776   0.0252
  -4.500   0.0499   0.01476   0.00794  -0.1007   0.7604   0.0254
  -4.250   0.0728   0.01444   0.00744  -0.0996   0.7377   0.0257
  -4.000   0.0946   0.01422   0.00702  -0.0981   0.7076   0.0260
  -3.750   0.1154   0.01402   0.00662  -0.0965   0.6786   0.0261
  -3.500   0.1368   0.01381   0.00624  -0.0951   0.6566   0.0262
  -3.250   0.1587   0.01336   0.00570  -0.0938   0.6402   0.0264
  -3.000   0.1812   0.01300   0.00527  -0.0927   0.6265   0.0266
  -2.750   0.2039   0.01273   0.00494  -0.0916   0.6143   0.0269
  -2.250   0.2503   0.01231   0.00442  -0.0896   0.5910   0.0274
  -2.000   0.2737   0.01214   0.00420  -0.0886   0.5804   0.0277
  -1.750   0.2971   0.01199   0.00401  -0.0877   0.5688   0.0281
  -1.500   0.3208   0.01185   0.00383  -0.0868   0.5566   0.0284
  -1.250   0.3439   0.01174   0.00367  -0.0857   0.5429   0.0287
  -1.000   0.3668   0.01167   0.00353  -0.0846   0.5268   0.0291
  -0.750   0.3890   0.01163   0.00341  -0.0834   0.5074   0.0295
  -0.500   0.4104   0.01165   0.00333  -0.0821   0.4855   0.0301
  -0.250   0.4319   0.01171   0.00328  -0.0807   0.4649   0.0306
   0.000   0.4535   0.01172   0.00319  -0.0795   0.4475   0.0312
   0.250   0.4753   0.01175   0.00314  -0.0782   0.4314   0.0318
   0.750   0.5206   0.01187   0.00310  -0.0761   0.4051   0.0333
   1.000   0.5439   0.01193   0.00310  -0.0752   0.3962   0.0342
   1.250   0.5678   0.01197   0.00310  -0.0744   0.3888   0.0353
   1.500   0.5911   0.01204   0.00313  -0.0735   0.3826   0.0369
   1.750   0.6154   0.01206   0.00316  -0.0727   0.3771   0.0407
   2.000   0.6360   0.01175   0.00324  -0.0715   0.3717   0.1870
   2.250   0.6586   0.01176   0.00335  -0.0705   0.3664   0.2342
   2.500   0.6823   0.01178   0.00345  -0.0697   0.3618   0.2680
   2.750   0.7055   0.01182   0.00356  -0.0689   0.3563   0.3003
   3.000   0.7277   0.01191   0.00367  -0.0678   0.3505   0.3265
   3.250   0.7506   0.01193   0.00377  -0.0669   0.3454   0.3613
   3.500   0.7653   0.01120   0.00386  -0.0646   0.3411   0.6854
   4.000   0.8815   0.01153   0.00483  -0.0777   0.3306   0.9859
   4.250   0.9229   0.01174   0.00503  -0.0809   0.3268   0.9914
   4.500   0.9615   0.01195   0.00521  -0.0835   0.3227   0.9949
   4.750   0.9992   0.01218   0.00539  -0.0860   0.3176   0.9977
   5.000   1.0357   0.01239   0.00558  -0.0881   0.3128   1.0000
   5.250   1.0528   0.01251   0.00571  -0.0861   0.3097   1.0000
   5.500   1.0677   0.01264   0.00583  -0.0835   0.3065   1.0000
   5.750   1.0805   0.01278   0.00597  -0.0805   0.3030   1.0000
   6.000   1.0928   0.01294   0.00612  -0.0774   0.2995   1.0000
   6.250   1.1078   0.01308   0.00627  -0.0749   0.2966   1.0000
   6.500   1.1235   0.01322   0.00642  -0.0726   0.2922   1.0000
   6.750   1.1383   0.01340   0.00660  -0.0701   0.2866   1.0000
   7.000   1.1533   0.01362   0.00679  -0.0678   0.2808   1.0000
   7.250   1.1697   0.01382   0.00699  -0.0657   0.2734   1.0000
   7.500   1.1846   0.01409   0.00723  -0.0634   0.2641   1.0000
   7.750   1.1994   0.01439   0.00748  -0.0612   0.2529   1.0000
   8.000   1.2150   0.01470   0.00776  -0.0591   0.2413   1.0000
   8.250   1.2285   0.01514   0.00811  -0.0568   0.2245   1.0000
   8.500   1.2397   0.01573   0.00859  -0.0542   0.2021   1.0000
   8.750   1.2512   0.01636   0.00911  -0.0517   0.1857   1.0000
   9.000   1.2647   0.01693   0.00963  -0.0496   0.1762   1.0000
   9.250   1.2779   0.01754   0.01020  -0.0476   0.1679   1.0000
   9.500   1.2918   0.01812   0.01078  -0.0457   0.1597   1.0000
   9.750   1.3040   0.01883   0.01145  -0.0436   0.1518   1.0000
  10.000   1.3196   0.01937   0.01200  -0.0421   0.1451   1.0000
  10.250   1.3315   0.02012   0.01272  -0.0401   0.1365   1.0000
  10.500   1.3434   0.02091   0.01346  -0.0383   0.1244   1.0000
  10.750   1.3420   0.02253   0.01484  -0.0349   0.0891   1.0000
  11.000   1.3272   0.02509   0.01717  -0.0303   0.0474   1.0000
  11.250   1.3178   0.02747   0.01946  -0.0267   0.0204   1.0000
  11.500   1.3252   0.02878   0.02081  -0.0250   0.0177   1.0000
  11.750   1.3340   0.03002   0.02212  -0.0236   0.0165   1.0000
  12.000   1.3417   0.03139   0.02356  -0.0222   0.0157   1.0000
  12.250   1.3480   0.03292   0.02517  -0.0208   0.0149   1.0000
  12.500   1.3532   0.03461   0.02694  -0.0194   0.0143   1.0000
  12.750   1.3599   0.03624   0.02866  -0.0184   0.0139   1.0000
  13.000   1.3653   0.03804   0.03054  -0.0174   0.0135   1.0000
  13.250   1.3696   0.04003   0.03263  -0.0165   0.0131   1.0000
  13.500   1.3727   0.04224   0.03493  -0.0158   0.0127   1.0000
  13.750   1.3745   0.04468   0.03745  -0.0152   0.0123   1.0000
  14.000   1.3746   0.04739   0.04026  -0.0148   0.0120   1.0000
  14.250   1.3723   0.05046   0.04343  -0.0145   0.0117   1.0000
  14.500   1.3674   0.05393   0.04700  -0.0143   0.0114   1.0000
  14.750   1.3619   0.05756   0.05075  -0.0144   0.0112   1.0000
  15.000   1.3583   0.06101   0.05431  -0.0145   0.0111   1.0000
  15.250   1.3533   0.06473   0.05814  -0.0148   0.0109   1.0000
  15.500   1.3471   0.06869   0.06221  -0.0152   0.0108   1.0000
  15.750   1.3396   0.07291   0.06655  -0.0158   0.0107   1.0000
  16.000   1.3310   0.07735   0.07110  -0.0166   0.0105   1.0000
  16.250   1.3218   0.08195   0.07581  -0.0175   0.0104   1.0000
  16.500   1.3120   0.08672   0.08070  -0.0185   0.0103   1.0000
  16.750   1.3018   0.09160   0.08569  -0.0196   0.0102   1.0000
  17.000   1.2912   0.09654   0.09074  -0.0208   0.0101   1.0000
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