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NACA 63-415 AIRFOIL (n63415-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: NACA 63-415 AIRFOIL (n63415-il)
Reynolds number: 50,000
Max Cl/Cd: 29.96 at α=9.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-n63415-il-50000.txt
Download as CSV file: xf-n63415-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 63-415 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
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.3405   0.10948   0.10216  -0.0262   1.0000   0.3472
  -9.750  -0.5478   0.07570   0.06888  -0.0603   1.0000   0.1529
  -9.500  -0.5625   0.07182   0.06509  -0.0594   1.0000   0.1512
  -9.250  -0.5913   0.06833   0.06169  -0.0575   1.0000   0.1489
  -9.000  -0.6287   0.06501   0.05837  -0.0546   1.0000   0.1457
  -8.750  -0.7023   0.06129   0.05411  -0.0502   1.0000   0.1382
  -8.500  -0.7114   0.05825   0.05092  -0.0478   1.0000   0.1377
  -8.250  -0.7196   0.05521   0.04760  -0.0455   1.0000   0.1377
  -8.000  -0.7232   0.05221   0.04424  -0.0436   1.0000   0.1380
  -7.750  -0.7221   0.04929   0.04092  -0.0420   1.0000   0.1387
  -7.500  -0.7131   0.04623   0.03769  -0.0408   1.0000   0.1402
  -7.250  -0.7014   0.04373   0.03503  -0.0396   1.0000   0.1422
  -7.000  -0.6885   0.04167   0.03280  -0.0384   1.0000   0.1463
  -6.750  -0.6743   0.03957   0.03029  -0.0375   1.0000   0.1506
  -6.500  -0.6574   0.03750   0.02775  -0.0367   1.0000   0.1544
  -6.250  -0.6395   0.03582   0.02614  -0.0357   1.0000   0.1611
  -6.000  -0.6206   0.03441   0.02434  -0.0348   1.0000   0.1692
  -5.750  -0.6021   0.03297   0.02308  -0.0336   1.0000   0.1779
  -5.500  -0.5838   0.03175   0.02187  -0.0323   1.0000   0.1904
  -5.250  -0.5659   0.03061   0.02082  -0.0310   1.0000   0.2067
  -5.000  -0.5483   0.02944   0.01976  -0.0297   1.0000   0.2317
  -4.750  -0.5316   0.02782   0.01873  -0.0286   1.0000   0.2814
  -4.500  -0.5217   0.02661   0.01932  -0.0251   1.0000   0.4674
  -4.250  -0.5171   0.02845   0.02137  -0.0183   1.0000   0.5628
  -4.000  -0.5113   0.02999   0.02286  -0.0122   1.0000   0.6082
  -3.750  -0.5061   0.03128   0.02411  -0.0062   1.0000   0.6414
  -3.500  -0.5019   0.03241   0.02520   0.0000   1.0000   0.6703
  -3.250  -0.4987   0.03334   0.02610   0.0063   1.0000   0.6968
  -3.000  -0.4942   0.03398   0.02666   0.0118   1.0000   0.7258
  -2.750  -0.4844   0.03489   0.02748   0.0170   0.9962   0.7549
  -2.500  -0.4676   0.03579   0.02827   0.0210   0.9893   0.7835
  -2.250  -0.4449   0.03648   0.02880   0.0230   0.9823   0.8118
  -2.000  -0.4257   0.03664   0.02880   0.0248   0.9755   0.8366
  -1.750  -0.3937   0.03704   0.02900   0.0239   0.9685   0.8592
  -1.500  -0.3658   0.03701   0.02881   0.0230   0.9616   0.8772
  -1.250  -0.3206   0.03746   0.02904   0.0186   0.9541   0.8946
  -1.000  -0.2891   0.03742   0.02885   0.0162   0.9471   0.9100
  -0.750  -0.2294   0.03816   0.02936   0.0087   0.9389   0.9247
  -0.500  -0.1879   0.03831   0.02938   0.0041   0.9315   0.9381
  -0.250  -0.1093   0.03932   0.03017  -0.0072   0.9226   0.9500
   0.000  -0.0624   0.03962   0.03037  -0.0133   0.9149   0.9616
   0.250   0.0137   0.04055   0.03115  -0.0243   0.9064   0.9729
   0.500   0.0566   0.04090   0.03145  -0.0301   0.8987   0.9845
   0.750   0.1308   0.04177   0.03223  -0.0409   0.8901   0.9960
   1.000   0.1297   0.04196   0.03240  -0.0393   0.8840   1.0000
   1.250   0.1261   0.04213   0.03255  -0.0369   0.8783   1.0000
   1.500   0.1343   0.04256   0.03294  -0.0362   0.8728   1.0000
   1.750   0.1100   0.04236   0.03274  -0.0307   0.8696   1.0000
   2.000   0.0957   0.04229   0.03263  -0.0269   0.8670   1.0000
   2.250   0.1021   0.04273   0.03302  -0.0265   0.8635   1.0000
   2.500   0.1352   0.04391   0.03414  -0.0298   0.8554   1.0000
   2.750   0.1479   0.04469   0.03488  -0.0305   0.8518   1.0000
   3.000   0.1717   0.04579   0.03595  -0.0326   0.8456   1.0000
   3.250   0.2044   0.04723   0.03735  -0.0357   0.8372   1.0000
   3.500   0.2212   0.04838   0.03849  -0.0369   0.8325   1.0000
   3.750   0.2594   0.05002   0.04011  -0.0403   0.8213   1.0000
   4.000   0.2719   0.05126   0.04135  -0.0409   0.8168   1.0000
   4.250   0.3085   0.05292   0.04301  -0.0438   0.8043   1.0000
   4.500   0.3193   0.05430   0.04440  -0.0441   0.7994   1.0000
   4.750   0.3510   0.05590   0.04603  -0.0462   0.7858   1.0000
   5.000   0.3840   0.05747   0.04763  -0.0483   0.7708   1.0000
   5.250   0.3927   0.05901   0.04921  -0.0482   0.7638   1.0000
   5.500   0.4206   0.06048   0.05073  -0.0495   0.7471   1.0000
   5.750   0.4467   0.06199   0.05231  -0.0505   0.7312   1.0000
   6.000   0.4735   0.06344   0.05383  -0.0515   0.7141   1.0000
   6.250   0.5012   0.06482   0.05529  -0.0523   0.6963   1.0000
   6.500   0.5316   0.06610   0.05668  -0.0532   0.6779   1.0000
   6.750   0.5717   0.06708   0.05780  -0.0544   0.6585   1.0000
   7.000   0.5989   0.06820   0.05903  -0.0546   0.6396   1.0000
   7.250   0.6156   0.06955   0.06049  -0.0542   0.6211   1.0000
   7.500   0.6361   0.07076   0.06182  -0.0540   0.6017   1.0000
   7.750   0.6651   0.07154   0.06275  -0.0538   0.5816   1.0000
   8.000   0.7155   0.07084   0.06229  -0.0538   0.5610   1.0000
   8.250   0.7281   0.07212   0.06369  -0.0528   0.5397   1.0000
   8.500   0.7586   0.07190   0.06369  -0.0516   0.5169   1.0000
   8.750   0.8147   0.06878   0.06086  -0.0497   0.4933   1.0000
   9.000   0.8989   0.06041   0.05298  -0.0455   0.4664   1.0000
   9.250   1.0763   0.03691   0.02993  -0.0371   0.3944   1.0000
   9.500   1.0830   0.03615   0.02848  -0.0321   0.3237   1.0000
   9.750   1.0771   0.03826   0.02994  -0.0283   0.2688   1.0000
  10.000   1.0815   0.04069   0.03178  -0.0258   0.2264   1.0000
  10.250   1.0995   0.04302   0.03377  -0.0245   0.1940   1.0000
  10.500   1.1395   0.04535   0.03577  -0.0249   0.1680   1.0000
  10.750   1.1738   0.04807   0.03852  -0.0255   0.1520   1.0000
  11.000   1.2112   0.05119   0.04163  -0.0267   0.1396   1.0000
  11.250   1.2181   0.05402   0.04485  -0.0250   0.1339   1.0000
  11.500   1.2533   0.05785   0.04865  -0.0265   0.1262   1.0000
  11.750   1.2428   0.06079   0.05204  -0.0234   0.1240   1.0000
  12.000   1.2333   0.06416   0.05578  -0.0211   0.1220   1.0000
  12.250   1.2217   0.06786   0.05981  -0.0192   0.1206   1.0000
  12.500   1.2050   0.07199   0.06425  -0.0177   0.1200   1.0000
  12.750   1.1812   0.07673   0.06929  -0.0168   0.1201   1.0000
  13.000   1.1502   0.08236   0.07519  -0.0170   0.1209   1.0000
  13.250   1.1143   0.08916   0.08225  -0.0184   0.1223   1.0000
  13.500   1.0771   0.09713   0.09042  -0.0213   0.1239   1.0000
  13.750   1.0435   0.10597   0.09939  -0.0252   0.1255   1.0000
  14.000   1.0173   0.11509   0.10859  -0.0294   0.1267   1.0000
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