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USA 27 mod. AIRFOIL (usa27m2-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: USA 27 mod. AIRFOIL (usa27m2-il)
Reynolds number: 50,000
Max Cl/Cd: 17.61 at α=2.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-usa27m2-il-50000.txt
Download as CSV file: xf-usa27m2-il-50000.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 =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.3056   0.11742   0.11102  -0.0222   1.0000   0.2200
  -8.250  -0.3248   0.11701   0.11074  -0.0206   1.0000   0.2253
  -8.000  -0.3654   0.11854   0.11246  -0.0185   1.0000   0.2271
  -7.750  -0.3309   0.11184   0.10573  -0.0171   1.0000   0.2326
  -7.500  -0.3363   0.10999   0.10396  -0.0150   1.0000   0.2389
  -7.250  -0.3682   0.11019   0.10431  -0.0124   1.0000   0.2431
  -7.000  -0.4128   0.11112   0.10542  -0.0098   1.0000   0.2444
  -6.750  -0.3714   0.10469   0.09897  -0.0079   1.0000   0.2527
  -6.500  -0.3942   0.10379   0.09819  -0.0049   1.0000   0.2579
  -6.250  -0.4362   0.10428   0.09882  -0.0045   1.0000   0.2616
  -6.000  -0.4187   0.09961   0.09421  -0.0010   1.0000   0.2672
  -5.750  -0.4280   0.09781   0.09249   0.0009   1.0000   0.2748
  -5.500  -0.4542   0.09670   0.09145   0.0004   1.0000   0.2804
  -5.250  -0.4443   0.09325   0.08808   0.0041   1.0000   0.2866
  -5.000  -0.4672   0.09262   0.08745   0.0023   1.0000   0.2969
  -4.750  -0.4586   0.08877   0.08369   0.0063   1.0000   0.3017
  -4.500  -0.4692   0.08738   0.08228   0.0049   1.0000   0.3141
  -4.250  -0.4635   0.08400   0.07898   0.0083   1.0000   0.3196
  -4.000  -0.4661   0.08179   0.07676   0.0079   1.0000   0.3325
  -3.750  -0.4650   0.07979   0.07474   0.0077   1.0000   0.3475
  -3.500  -0.4599   0.07671   0.07174   0.0107   1.0000   0.3551
  -3.250  -0.4512   0.07412   0.06915   0.0104   0.9983   0.3723
  -3.000  -0.4108   0.07062   0.06556   0.0041   0.9838   0.4139
  -2.750  -0.2805   0.06092   0.05383  -0.0310   0.9672   0.1932
  -2.500  -0.2271   0.05465   0.04674  -0.0378   0.9549   0.1613
  -2.250  -0.1827   0.05189   0.04373  -0.0419   0.9404   0.1548
  -2.000  -0.1284   0.04801   0.03871  -0.0469   0.9278   0.1445
  -1.500  -0.0349   0.04442   0.03425  -0.0538   0.8985   0.1440
  -1.250   0.0084   0.04335   0.03303  -0.0566   0.8830   0.1491
  -1.000   0.0526   0.04248   0.03195  -0.0592   0.8672   0.1563
  -0.750   0.0986   0.04164   0.03090  -0.0617   0.8515   0.1645
  -0.500   0.1441   0.04101   0.03020  -0.0641   0.8357   0.1803
  -0.250   0.1849   0.04044   0.02980  -0.0657   0.8200   0.2162
   0.000   0.2187   0.03930   0.02928  -0.0660   0.8049   0.3804
   0.250   0.3132   0.03693   0.02862  -0.0771   0.7914   1.0000
   0.500   0.3499   0.03710   0.02837  -0.0783   0.7757   1.0000
   0.750   0.3854   0.03723   0.02816  -0.0791   0.7610   1.0000
   1.000   0.4472   0.03644   0.02698  -0.0835   0.7520   1.0000
   1.250   0.4717   0.03675   0.02708  -0.0827   0.7371   1.0000
   1.500   0.4936   0.03719   0.02733  -0.0816   0.7226   1.0000
   1.750   0.5140   0.03775   0.02772  -0.0804   0.7091   1.0000
   2.000   0.5697   0.03698   0.02673  -0.0838   0.7015   1.0000
   2.250   0.5886   0.03766   0.02728  -0.0824   0.6893   1.0000
   2.500   0.5904   0.03915   0.02867  -0.0790   0.6762   1.0000
   2.750   0.6617   0.03757   0.02691  -0.0842   0.6710   1.0000
   3.000   0.6439   0.04012   0.02942  -0.0784   0.6573   1.0000
   3.250   0.6240   0.04311   0.03237  -0.0730   0.6455   1.0000
   3.500   0.6736   0.04250   0.03165  -0.0753   0.6394   1.0000
   3.750   0.6283   0.04739   0.03653  -0.0683   0.6266   1.0000
   4.000   0.6863   0.04602   0.03505  -0.0707   0.6218   1.0000
   4.250   0.6176   0.05334   0.04240  -0.0636   0.6102   1.0000
   4.500   0.6570   0.05325   0.04225  -0.0643   0.6047   1.0000
   4.750   0.6155   0.05897   0.04797  -0.0603   0.5966   1.0000
   5.000   0.6209   0.06141   0.05039  -0.0592   0.5904   1.0000
   5.250   0.6522   0.06217   0.05110  -0.0594   0.5847   1.0000
   5.500   0.6148   0.06756   0.05651  -0.0565   0.5786   1.0000
   5.750   0.6764   0.06587   0.05476  -0.0575   0.5689   1.0000
   6.000   0.6320   0.07166   0.06057  -0.0544   0.5611   1.0000
   6.250   0.6736   0.07126   0.06014  -0.0542   0.5501   1.0000
   6.500   0.6551   0.07525   0.06415  -0.0524   0.5413   1.0000
   6.750   0.6765   0.07645   0.06534  -0.0517   0.5316   1.0000
   7.000   0.6763   0.07930   0.06821  -0.0507   0.5229   1.0000
   7.250   0.6837   0.08170   0.07062  -0.0498   0.5141   1.0000
   7.500   0.7001   0.08340   0.07234  -0.0492   0.5046   1.0000
   7.750   0.6899   0.08741   0.07638  -0.0484   0.4971   1.0000
   8.000   0.7152   0.08856   0.07755  -0.0479   0.4873   1.0000
   8.250   0.6941   0.09355   0.08258  -0.0472   0.4801   1.0000
   8.500   0.7338   0.09353   0.08257  -0.0466   0.4684   1.0000
   8.750   0.7010   0.09998   0.08906  -0.0466   0.4652   1.0000
   9.000   0.6937   0.10497   0.09410  -0.0472   0.4662   1.0000
   9.250   0.7019   0.10935   0.09852  -0.0481   0.4686   1.0000
   9.500   0.6259   0.12345   0.11280  -0.0544   0.5524   1.0000
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