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NACA 63(2)-215 MOD B (n63215b-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: NACA 63(2)-215 MOD B (n63215b-il)
Reynolds number: 50,000
Max Cl/Cd: 25.87 at α=3.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-n63215b-il-50000.txt
Download as CSV file: xf-n63215b-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 63(2)-215 MOD B                            
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.5775   0.09084   0.08363  -0.0357   1.0000   0.1539
 -10.750  -0.5782   0.08517   0.07795  -0.0374   1.0000   0.1523
 -10.500  -0.6956   0.07177   0.06435  -0.0461   1.0000   0.1376
 -10.250  -0.7125   0.06752   0.06003  -0.0455   1.0000   0.1368
 -10.000  -0.7297   0.06341   0.05578  -0.0446   1.0000   0.1361
  -9.750  -0.7456   0.05960   0.05176  -0.0431   1.0000   0.1358
  -9.500  -0.7559   0.05611   0.04801  -0.0414   1.0000   0.1359
  -9.250  -0.7631   0.05293   0.04452  -0.0391   1.0000   0.1366
  -9.000  -0.7670   0.05007   0.04133  -0.0366   1.0000   0.1373
  -8.750  -0.7686   0.04749   0.03840  -0.0338   1.0000   0.1380
  -8.500  -0.7619   0.04471   0.03550  -0.0315   1.0000   0.1395
  -8.250  -0.7496   0.04261   0.03347  -0.0296   1.0000   0.1434
  -8.000  -0.7425   0.04083   0.03155  -0.0270   1.0000   0.1475
  -7.750  -0.7365   0.03904   0.02943  -0.0242   1.0000   0.1513
  -7.500  -0.7263   0.03716   0.02730  -0.0218   1.0000   0.1548
  -7.250  -0.7099   0.03550   0.02575  -0.0200   1.0000   0.1610
  -7.000  -0.6977   0.03414   0.02414  -0.0178   1.0000   0.1687
  -6.750  -0.6799   0.03267   0.02290  -0.0160   1.0000   0.1786
  -6.500  -0.6629   0.03131   0.02162  -0.0140   1.0000   0.1906
  -6.250  -0.6485   0.03007   0.02054  -0.0118   1.0000   0.2080
  -6.000  -0.6367   0.02873   0.01940  -0.0094   1.0000   0.2343
  -5.750  -0.6298   0.02704   0.01829  -0.0066   1.0000   0.2793
  -5.500  -0.6306   0.02537   0.01799  -0.0021   1.0000   0.3952
  -5.250  -0.6267   0.02681   0.02001   0.0048   1.0000   0.5143
  -5.000  -0.6167   0.02876   0.02199   0.0109   1.0000   0.5645
  -4.750  -0.6055   0.03082   0.02404   0.0174   1.0000   0.5998
  -4.500  -0.5942   0.03261   0.02580   0.0235   1.0000   0.6297
  -4.250  -0.5841   0.03398   0.02710   0.0293   1.0000   0.6587
  -4.000  -0.5689   0.03575   0.02882   0.0355   1.0000   0.6829
  -3.750  -0.5593   0.03627   0.02925   0.0401   1.0000   0.7082
  -3.500  -0.5406   0.03729   0.03017   0.0446   1.0000   0.7301
  -3.250  -0.5270   0.03753   0.03030   0.0482   1.0000   0.7527
  -3.000  -0.5147   0.03753   0.03021   0.0515   1.0000   0.7748
  -2.750  -0.4869   0.03799   0.03054   0.0532   1.0000   0.7961
  -2.500  -0.4662   0.03783   0.03027   0.0545   1.0000   0.8150
  -2.250  -0.4478   0.03741   0.02974   0.0554   1.0000   0.8311
  -2.000  -0.4306   0.03689   0.02913   0.0561   1.0000   0.8457
  -1.750  -0.4133   0.03638   0.02852   0.0566   1.0000   0.8600
  -1.500  -0.3950   0.03592   0.02797   0.0568   1.0000   0.8743
  -1.250  -0.3790   0.03542   0.02739   0.0571   1.0000   0.8881
  -1.000  -0.3416   0.03535   0.02722   0.0540   1.0000   0.9000
  -0.750  -0.3084   0.03522   0.02701   0.0512   1.0000   0.9116
  -0.500  -0.2757   0.03514   0.02686   0.0482   1.0000   0.9236
  -0.250  -0.1556   0.03675   0.02832   0.0296   0.9739   0.9325
   0.000  -0.0441   0.03758   0.02905   0.0132   0.9462   0.9405
   0.250   0.0535   0.03793   0.02936  -0.0001   0.9204   0.9496
   0.500   0.1556   0.03763   0.02908  -0.0135   0.8931   0.9574
   0.750   0.2497   0.03690   0.02841  -0.0247   0.8648   0.9659
   1.000   0.3941   0.03445   0.02607  -0.0420   0.8306   0.9734
   1.250   0.4799   0.03189   0.02360  -0.0486   0.7957   0.9819
   1.500   0.5352   0.02952   0.02126  -0.0500   0.7569   0.9904
   1.750   0.5755   0.02734   0.01904  -0.0490   0.7093   0.9991
   2.000   0.5889   0.02617   0.01774  -0.0445   0.6597   1.0000
   2.250   0.5993   0.02547   0.01683  -0.0402   0.6054   1.0000
   2.500   0.6119   0.02506   0.01610  -0.0368   0.5577   1.0000
   2.750   0.6249   0.02502   0.01574  -0.0341   0.5173   1.0000
   3.000   0.6387   0.02519   0.01563  -0.0319   0.4855   1.0000
   3.250   0.6535   0.02549   0.01567  -0.0301   0.4604   1.0000
   3.500   0.6679   0.02592   0.01593  -0.0283   0.4382   1.0000
   3.750   0.6830   0.02640   0.01621  -0.0267   0.4195   1.0000
   4.000   0.6980   0.02701   0.01669  -0.0251   0.4036   1.0000
   4.250   0.7126   0.02777   0.01737  -0.0236   0.3900   1.0000
   4.500   0.7268   0.02859   0.01813  -0.0220   0.3777   1.0000
   4.750   0.7421   0.02945   0.01882  -0.0204   0.3662   1.0000
   5.000   0.7531   0.03039   0.01978  -0.0184   0.3551   1.0000
   5.250   0.7620   0.03149   0.02093  -0.0162   0.3459   1.0000
   5.500   0.7754   0.03255   0.02190  -0.0144   0.3368   1.0000
   5.750   0.7769   0.03376   0.02332  -0.0113   0.3291   1.0000
   6.000   0.7892   0.03491   0.02437  -0.0093   0.3210   1.0000
   6.250   0.7938   0.03646   0.02612  -0.0068   0.3146   1.0000
   6.500   0.8069   0.03812   0.02789  -0.0056   0.3078   1.0000
   6.750   0.8271   0.03997   0.02972  -0.0052   0.3016   1.0000
   7.000   0.8313   0.04234   0.03245  -0.0038   0.2955   1.0000
   7.250   0.8544   0.04402   0.03406  -0.0037   0.2881   1.0000
   7.500   0.8582   0.04681   0.03712  -0.0025   0.2826   1.0000
   7.750   0.8550   0.05009   0.04071  -0.0012   0.2783   1.0000
   8.000   0.8536   0.05357   0.04440  -0.0004   0.2751   1.0000
   8.250   0.8905   0.05529   0.04594  -0.0010   0.2699   1.0000
   8.500   0.8622   0.06051   0.05152   0.0005   0.2691   1.0000
   8.750   0.8255   0.06673   0.05795   0.0013   0.2694   1.0000
   9.000   0.4563   0.11429   0.10565  -0.0329   0.4569   1.0000
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