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NACA 63012A AIRFOIL (n63012a-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: NACA 63012A AIRFOIL (n63012a-il)
Reynolds number: 200,000
Max Cl/Cd: 41.93 at α=4.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-n63012a-il-200000-n5.txt
Download as CSV file: xf-n63012a-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 63012A AIRFOIL                             
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -13.750  -0.8479   0.09228   0.08836  -0.0103   1.0000   0.0164
 -13.500  -0.8729   0.08305   0.07899  -0.0165   1.0000   0.0162
 -13.250  -0.8963   0.07509   0.07085  -0.0217   1.0000   0.0162
 -13.000  -0.9185   0.06820   0.06375  -0.0257   1.0000   0.0162
 -12.750  -0.9388   0.06231   0.05763  -0.0286   1.0000   0.0162
 -12.500  -0.9570   0.05726   0.05232  -0.0303   1.0000   0.0162
 -12.250  -0.9729   0.05299   0.04777  -0.0309   1.0000   0.0163
 -12.000  -0.9853   0.04931   0.04385  -0.0305   1.0000   0.0165
 -11.750  -0.9912   0.04642   0.04080  -0.0295   1.0000   0.0168
 -11.500  -0.9926   0.04420   0.03845  -0.0282   1.0000   0.0170
 -11.250  -0.9918   0.04229   0.03640  -0.0265   1.0000   0.0173
 -11.000  -0.9897   0.04045   0.03440  -0.0245   1.0000   0.0176
 -10.750  -0.9846   0.03852   0.03226  -0.0227   1.0000   0.0179
 -10.500  -0.9764   0.03648   0.02998  -0.0211   1.0000   0.0183
 -10.250  -0.9655   0.03452   0.02778  -0.0196   1.0000   0.0186
 -10.000  -0.9522   0.03269   0.02572  -0.0182   1.0000   0.0190
  -9.750  -0.9370   0.03098   0.02377  -0.0170   1.0000   0.0195
  -9.500  -0.9201   0.02940   0.02198  -0.0159   1.0000   0.0200
  -9.250  -0.9020   0.02809   0.02048  -0.0148   1.0000   0.0207
  -9.000  -0.8829   0.02697   0.01916  -0.0138   1.0000   0.0214
  -8.750  -0.8647   0.02542   0.01754  -0.0128   1.0000   0.0221
  -8.500  -0.8462   0.02422   0.01629  -0.0117   1.0000   0.0227
  -8.250  -0.8274   0.02320   0.01520  -0.0106   1.0000   0.0233
  -8.000  -0.8085   0.02225   0.01420  -0.0095   1.0000   0.0241
  -7.750  -0.7898   0.02135   0.01324  -0.0083   1.0000   0.0250
  -7.500  -0.7713   0.02051   0.01232  -0.0069   1.0000   0.0260
  -7.250  -0.7530   0.01972   0.01147  -0.0055   1.0000   0.0271
  -7.000  -0.7353   0.01896   0.01063  -0.0040   1.0000   0.0284
  -6.750  -0.7188   0.01819   0.00987  -0.0024   1.0000   0.0306
  -6.500  -0.7009   0.01762   0.00927  -0.0008   1.0000   0.0331
  -6.250  -0.6831   0.01708   0.00866   0.0008   1.0000   0.0358
  -6.000  -0.6670   0.01643   0.00801   0.0027   1.0000   0.0393
  -5.750  -0.6437   0.01590   0.00744   0.0031   0.9975   0.0448
  -5.500  -0.6101   0.01526   0.00682   0.0013   0.9901   0.0556
  -5.250  -0.5768   0.01460   0.00625  -0.0005   0.9825   0.0753
  -5.000  -0.5451   0.01384   0.00570  -0.0020   0.9738   0.1158
  -4.750  -0.5168   0.01290   0.00514  -0.0030   0.9629   0.1929
  -4.500  -0.4908   0.01185   0.00463  -0.0036   0.9512   0.3039
  -4.250  -0.4646   0.01108   0.00431  -0.0038   0.9395   0.4106
  -4.000  -0.4360   0.01069   0.00413  -0.0041   0.9284   0.4788
  -3.750  -0.4070   0.01044   0.00401  -0.0044   0.9174   0.5255
  -3.500  -0.3794   0.01027   0.00390  -0.0042   0.9049   0.5603
  -3.250  -0.3521   0.01015   0.00381  -0.0039   0.8928   0.5911
  -3.000  -0.3248   0.01007   0.00374  -0.0036   0.8810   0.6167
  -2.750  -0.2977   0.01000   0.00367  -0.0032   0.8696   0.6375
  -2.500  -0.2708   0.00995   0.00358  -0.0028   0.8580   0.6544
  -2.250  -0.2440   0.00991   0.00351  -0.0024   0.8465   0.6683
  -2.000  -0.2170   0.00987   0.00343  -0.0021   0.8357   0.6795
  -1.750  -0.1897   0.00984   0.00332  -0.0018   0.8254   0.6899
  -1.500  -0.1627   0.00981   0.00326  -0.0015   0.8146   0.6992
  -1.250  -0.1356   0.00978   0.00320  -0.0013   0.8044   0.7086
  -1.000  -0.1084   0.00977   0.00313  -0.0010   0.7951   0.7187
  -0.750  -0.0814   0.00975   0.00311  -0.0008   0.7846   0.7276
  -0.500  -0.0542   0.00974   0.00308  -0.0005   0.7752   0.7372
  -0.250  -0.0271   0.00974   0.00306  -0.0002   0.7659   0.7468
   0.000   0.0000   0.00973   0.00307   0.0000   0.7560   0.7560
   0.250   0.0271   0.00974   0.00306   0.0002   0.7468   0.7659
   0.500   0.0542   0.00974   0.00308   0.0005   0.7372   0.7752
   0.750   0.0814   0.00975   0.00311   0.0008   0.7276   0.7847
   1.000   0.1084   0.00977   0.00313   0.0010   0.7187   0.7950
   1.250   0.1356   0.00978   0.00320   0.0013   0.7086   0.8044
   1.500   0.1627   0.00981   0.00326   0.0015   0.6992   0.8146
   1.750   0.1897   0.00984   0.00332   0.0018   0.6899   0.8254
   2.000   0.2170   0.00987   0.00343   0.0021   0.6796   0.8357
   2.250   0.2440   0.00991   0.00351   0.0024   0.6683   0.8465
   2.500   0.2708   0.00995   0.00358   0.0028   0.6544   0.8580
   2.750   0.2977   0.01000   0.00367   0.0032   0.6375   0.8696
   3.000   0.3249   0.01007   0.00374   0.0036   0.6168   0.8810
   3.250   0.3521   0.01015   0.00381   0.0039   0.5910   0.8928
   3.500   0.3794   0.01027   0.00390   0.0042   0.5602   0.9049
   3.750   0.4070   0.01044   0.00401   0.0044   0.5255   0.9174
   4.000   0.4361   0.01069   0.00414   0.0041   0.4789   0.9284
   4.250   0.4646   0.01108   0.00431   0.0038   0.4106   0.9394
   4.500   0.4908   0.01185   0.00463   0.0036   0.3042   0.9511
   4.750   0.5168   0.01290   0.00514   0.0030   0.1929   0.9628
   5.000   0.5451   0.01384   0.00570   0.0020   0.1158   0.9738
   5.250   0.5768   0.01460   0.00625   0.0005   0.0753   0.9824
   5.500   0.6101   0.01526   0.00682  -0.0013   0.0556   0.9901
   5.750   0.6437   0.01590   0.00744  -0.0031   0.0448   0.9974
   6.000   0.6671   0.01643   0.00801  -0.0027   0.0393   1.0000
   6.250   0.6832   0.01708   0.00866  -0.0008   0.0358   1.0000
   6.500   0.7009   0.01762   0.00927   0.0008   0.0331   1.0000
   6.750   0.7188   0.01819   0.00987   0.0024   0.0306   1.0000
   7.000   0.7353   0.01896   0.01063   0.0040   0.0284   1.0000
   7.250   0.7530   0.01972   0.01146   0.0055   0.0271   1.0000
   7.500   0.7713   0.02051   0.01232   0.0069   0.0260   1.0000
   7.750   0.7898   0.02135   0.01324   0.0083   0.0250   1.0000
   8.000   0.8085   0.02225   0.01420   0.0095   0.0241   1.0000
   8.250   0.8274   0.02320   0.01520   0.0106   0.0233   1.0000
   8.500   0.8462   0.02422   0.01629   0.0117   0.0227   1.0000
   8.750   0.8647   0.02542   0.01754   0.0128   0.0221   1.0000
   9.000   0.8829   0.02696   0.01916   0.0138   0.0214   1.0000
   9.250   0.9020   0.02809   0.02047   0.0148   0.0207   1.0000
   9.500   0.9201   0.02939   0.02198   0.0159   0.0200   1.0000
   9.750   0.9370   0.03097   0.02376   0.0170   0.0195   1.0000
  10.000   0.9523   0.03268   0.02571   0.0182   0.0190   1.0000
  10.250   0.9656   0.03452   0.02778   0.0196   0.0186   1.0000
  10.500   0.9765   0.03648   0.02998   0.0210   0.0183   1.0000
  10.750   0.9847   0.03852   0.03226   0.0227   0.0179   1.0000
  11.000   0.9899   0.04046   0.03440   0.0245   0.0176   1.0000
  11.250   0.9921   0.04229   0.03641   0.0265   0.0173   1.0000
  11.500   0.9929   0.04420   0.03846   0.0281   0.0170   1.0000
  11.750   0.9916   0.04643   0.04081   0.0295   0.0167   1.0000
  12.000   0.9857   0.04933   0.04387   0.0304   0.0165   1.0000
  12.250   0.9732   0.05301   0.04779   0.0308   0.0163   1.0000
  12.500   0.9574   0.05730   0.05236   0.0302   0.0162   1.0000
  12.750   0.9392   0.06236   0.05769   0.0284   0.0162   1.0000
  13.000   0.9187   0.06831   0.06387   0.0255   0.0161   1.0000
  13.250   0.8968   0.07520   0.07096   0.0215   0.0162   1.0000
  13.500   0.8734   0.08317   0.07911   0.0162   0.0162   1.0000
  13.750   0.8481   0.09251   0.08859   0.0100   0.0164   1.0000
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