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USA 27 mod. AIRFOIL (usa27m2-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: USA 27 mod. AIRFOIL (usa27m2-il)
Reynolds number: 100,000
Max Cl/Cd: 47.76 at α=5.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-usa27m2-il-100000.txt
Download as CSV file: xf-usa27m2-il-100000.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 =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.3625   0.11090   0.10654  -0.0237   1.0000   0.1140
  -8.000  -0.3994   0.11071   0.10648  -0.0227   1.0000   0.1148
  -7.750  -0.4361   0.11015   0.10601  -0.0220   1.0000   0.1151
  -7.500  -0.4353   0.10607   0.10199  -0.0197   1.0000   0.1162
  -7.250  -0.3998   0.10230   0.09822  -0.0156   1.0000   0.1197
  -7.000  -0.4126   0.10078   0.09678  -0.0130   1.0000   0.1218
  -6.750  -0.4280   0.09914   0.09520  -0.0114   1.0000   0.1243
  -6.500  -0.4467   0.09588   0.09183  -0.0244   0.9936   0.1302
  -6.250  -0.4194   0.09171   0.08777  -0.0204   0.9904   0.1329
  -6.000  -0.3882   0.08811   0.08412  -0.0249   0.9833   0.1399
  -5.750  -0.3631   0.08282   0.07870  -0.0346   0.9714   0.1475
  -5.500  -0.3335   0.07941   0.07528  -0.0366   0.9609   0.1534
  -5.250  -0.3077   0.07488   0.07058  -0.0442   0.9479   0.1633
  -5.000  -0.2776   0.07165   0.06733  -0.0461   0.9384   0.1703
  -4.750  -0.2457   0.06755   0.06308  -0.0519   0.9299   0.1811
  -4.500  -0.2229   0.06491   0.06023  -0.0554   0.9174   0.1951
  -4.250  -0.1956   0.06171   0.05710  -0.0556   0.9097   0.2017
  -4.000  -0.1658   0.05852   0.05376  -0.0588   0.9006   0.2151
  -3.750  -0.1419   0.05632   0.05134  -0.0607   0.8890   0.2293
  -3.500  -0.0998   0.03934   0.03238  -0.0677   0.8852   0.1045
  -3.250  -0.0692   0.03612   0.02860  -0.0679   0.8764   0.0962
  -3.000  -0.0295   0.03308   0.02460  -0.0690   0.8697   0.0892
  -2.750   0.0056   0.03178   0.02295  -0.0697   0.8610   0.0884
  -2.500   0.0456   0.02986   0.02085  -0.0714   0.8539   0.0896
  -2.250   0.0965   0.02808   0.01889  -0.0748   0.8504   0.0902
  -2.000   0.1235   0.02715   0.01788  -0.0740   0.8382   0.0905
  -1.750   0.1744   0.02556   0.01627  -0.0773   0.8347   0.0921
  -1.500   0.2017   0.02478   0.01549  -0.0766   0.8227   0.0942
  -1.250   0.2532   0.02340   0.01409  -0.0799   0.8187   0.0987
  -1.000   0.2811   0.02265   0.01339  -0.0792   0.8063   0.1055
  -0.750   0.3321   0.02130   0.01220  -0.0823   0.8014   0.1281
  -0.500   0.3610   0.02051   0.01198  -0.0817   0.7880   0.2491
  -0.250   0.3934   0.02007   0.01166  -0.0818   0.7751   0.3423
   0.000   0.4306   0.01929   0.01096  -0.0829   0.7629   0.4043
   0.250   0.6235   0.01694   0.00991  -0.1142   0.7479   1.0000
   0.500   0.6508   0.01679   0.00951  -0.1135   0.7270   1.0000
   0.750   0.6803   0.01666   0.00910  -0.1132   0.7064   1.0000
   1.000   0.7094   0.01663   0.00878  -0.1130   0.6859   1.0000
   1.250   0.7336   0.01679   0.00870  -0.1120   0.6640   1.0000
   1.500   0.7589   0.01702   0.00867  -0.1112   0.6439   1.0000
   1.750   0.7835   0.01734   0.00875  -0.1104   0.6257   1.0000
   2.000   0.8068   0.01771   0.00892  -0.1095   0.6093   1.0000
   2.250   0.8294   0.01811   0.00916  -0.1084   0.5949   1.0000
   2.500   0.8532   0.01850   0.00939  -0.1076   0.5824   1.0000
   2.750   0.8757   0.01888   0.00963  -0.1066   0.5706   1.0000
   3.000   0.8945   0.01929   0.01000  -0.1049   0.5591   1.0000
   3.250   0.9178   0.01965   0.01022  -0.1041   0.5493   1.0000
   3.500   0.9371   0.02001   0.01054  -0.1024   0.5390   1.0000
   3.750   0.9575   0.02039   0.01086  -0.1011   0.5300   1.0000
   4.000   0.9791   0.02073   0.01112  -0.0999   0.5212   1.0000
   4.250   0.9979   0.02113   0.01150  -0.0982   0.5125   1.0000
   4.500   1.0202   0.02145   0.01172  -0.0972   0.5043   1.0000
   4.750   1.0386   0.02189   0.01217  -0.0955   0.4965   1.0000
   5.000   1.0601   0.02224   0.01248  -0.0943   0.4889   1.0000
   5.250   1.0798   0.02267   0.01289  -0.0929   0.4814   1.0000
   5.500   1.0992   0.02306   0.01327  -0.0913   0.4737   1.0000
   5.750   1.1228   0.02351   0.01366  -0.0907   0.4673   1.0000
   6.000   1.1381   0.02403   0.01427  -0.0885   0.4602   1.0000
   6.250   1.1644   0.02444   0.01459  -0.0883   0.4540   1.0000
   6.500   1.1792   0.02506   0.01532  -0.0861   0.4476   1.0000
   6.750   1.1984   0.02557   0.01587  -0.0846   0.4410   1.0000
   7.000   1.2250   0.02610   0.01632  -0.0845   0.4351   1.0000
   7.250   1.2352   0.02676   0.01715  -0.0815   0.4281   1.0000
   7.500   1.2603   0.02722   0.01757  -0.0812   0.4215   1.0000
   7.750   1.2736   0.02791   0.01838  -0.0787   0.4145   1.0000
   8.000   1.2915   0.02843   0.01893  -0.0771   0.4070   1.0000
   8.250   1.3116   0.02904   0.01955  -0.0759   0.3997   1.0000
   8.500   1.3236   0.02964   0.02027  -0.0732   0.3916   1.0000
   8.750   1.3484   0.03021   0.02080  -0.0728   0.3842   1.0000
   9.000   1.3546   0.03095   0.02172  -0.0693   0.3759   1.0000
   9.250   1.3823   0.03148   0.02217  -0.0694   0.3682   1.0000
   9.500   1.3841   0.03227   0.02317  -0.0651   0.3594   1.0000
   9.750   1.4068   0.03265   0.02350  -0.0644   0.3506   1.0000
  10.000   1.4115   0.03317   0.02415  -0.0605   0.3412   1.0000
  10.250   1.4241   0.03354   0.02452  -0.0581   0.3320   1.0000
  10.500   1.4376   0.03364   0.02459  -0.0557   0.3227   1.0000
  10.750   1.4400   0.03431   0.02541  -0.0518   0.3145   1.0000
  11.000   1.4548   0.03445   0.02550  -0.0497   0.3063   1.0000
  11.250   1.4545   0.03525   0.02644  -0.0455   0.2994   1.0000
  11.500   1.4594   0.03582   0.02710  -0.0421   0.2926   1.0000
  11.750   1.4692   0.03624   0.02752  -0.0396   0.2858   1.0000
  12.000   1.4632   0.03714   0.02861  -0.0350   0.2790   1.0000
  12.250   1.4782   0.03723   0.02860  -0.0333   0.2720   1.0000
  12.500   1.4669   0.03868   0.03033  -0.0286   0.2661   1.0000
  12.750   1.4755   0.03917   0.03083  -0.0264   0.2598   1.0000
  13.000   1.4714   0.04043   0.03224  -0.0232   0.2537   1.0000
  13.250   1.4675   0.04163   0.03356  -0.0201   0.2470   1.0000
  13.500   1.4692   0.04264   0.03461  -0.0178   0.2407   1.0000
  13.750   1.4603   0.04464   0.03682  -0.0151   0.2346   1.0000
  14.000   1.4651   0.04551   0.03765  -0.0134   0.2280   1.0000
  14.250   1.4506   0.04836   0.04077  -0.0112   0.2221   1.0000
  14.500   1.4476   0.05025   0.04271  -0.0097   0.2158   1.0000
  14.750   1.4407   0.05284   0.04545  -0.0084   0.2103   1.0000
  15.000   1.4317   0.05585   0.04863  -0.0074   0.2048   1.0000
  15.250   1.4267   0.05843   0.05123  -0.0067   0.1981   1.0000
  15.500   1.4114   0.06265   0.05566  -0.0066   0.1925   1.0000
  15.750   1.4085   0.06532   0.05830  -0.0063   0.1857   1.0000
  16.000   1.3910   0.07033   0.06354  -0.0068   0.1810   1.0000
  16.250   1.3765   0.07501   0.06834  -0.0075   0.1751   1.0000
  16.500   1.3644   0.07948   0.07286  -0.0083   0.1687   1.0000
  16.750   1.3450   0.08538   0.07896  -0.0097   0.1641   1.0000
  17.000   1.3369   0.08942   0.08297  -0.0106   0.1566   1.0000
  17.250   1.3113   0.09673   0.09054  -0.0130   0.1526   1.0000
  17.500   1.2903   0.10338   0.09732  -0.0153   0.1467   1.0000
  17.750   1.2727   0.10958   0.10363  -0.0175   0.1402   1.0000
  18.000   1.2476   0.11733   0.11158  -0.0205   0.1352   1.0000
  18.250   1.2306   0.12378   0.11814  -0.0232   0.1277   1.0000
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