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NACA 63A210 (naca63a210-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: NACA 63A210 (naca63a210-il)
Reynolds number: 100,000
Max Cl/Cd: 40.2 at α=4.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca63a210-il-100000-n5.txt
Download as CSV file: xf-naca63a210-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 63A210                                     
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.5920   0.08842   0.08390  -0.0187   1.0000   0.0280
  -9.500  -0.5977   0.08179   0.07731  -0.0234   1.0000   0.0276
  -9.250  -0.6082   0.07379   0.06932  -0.0306   1.0000   0.0271
  -9.000  -0.6239   0.06753   0.06299  -0.0356   1.0000   0.0267
  -8.750  -0.6354   0.06213   0.05743  -0.0384   0.9692   0.0264
  -8.500  -0.6401   0.05676   0.05181  -0.0405   0.9478   0.0261
  -8.250  -0.6399   0.05172   0.04643  -0.0416   0.9343   0.0260
  -8.000  -0.6347   0.04702   0.04133  -0.0421   0.9223   0.0260
  -7.750  -0.6251   0.04275   0.03660  -0.0422   0.9109   0.0262
  -7.500  -0.6114   0.03929   0.03266  -0.0419   0.9022   0.0274
  -7.250  -0.5943   0.03632   0.02916  -0.0414   0.8943   0.0291
  -7.000  -0.5752   0.03357   0.02587  -0.0408   0.8867   0.0301
  -6.750  -0.5540   0.03099   0.02282  -0.0402   0.8796   0.0305
  -6.500  -0.5310   0.02887   0.02026  -0.0397   0.8728   0.0310
  -6.250  -0.5083   0.02611   0.01722  -0.0393   0.8654   0.0321
  -6.000  -0.4841   0.02442   0.01539  -0.0390   0.8577   0.0339
  -5.750  -0.4594   0.02332   0.01416  -0.0387   0.8500   0.0371
  -5.500  -0.4340   0.02205   0.01272  -0.0383   0.8428   0.0397
  -5.250  -0.4091   0.02081   0.01133  -0.0376   0.8345   0.0416
  -5.000  -0.3842   0.01977   0.01012  -0.0370   0.8214   0.0436
  -4.750  -0.3613   0.01855   0.00887  -0.0363   0.8028   0.0476
  -4.500  -0.3364   0.01785   0.00804  -0.0359   0.7826   0.0553
  -4.250  -0.3123   0.01703   0.00713  -0.0353   0.7624   0.0658
  -4.000  -0.2881   0.01627   0.00631  -0.0347   0.7438   0.0862
  -3.750  -0.2659   0.01517   0.00554  -0.0340   0.7271   0.1571
  -3.500  -0.2488   0.01353   0.00505  -0.0329   0.7121   0.4030
  -3.250  -0.2278   0.01304   0.00497  -0.0313   0.6948   0.5394
  -3.000  -0.2054   0.01289   0.00493  -0.0296   0.6734   0.6169
  -2.750  -0.1833   0.01285   0.00493  -0.0278   0.6615   0.6785
  -2.500  -0.1610   0.01285   0.00490  -0.0259   0.6558   0.7256
  -2.000  -0.1120   0.01271   0.00462  -0.0236   0.6482   0.7775
  -1.750  -0.0858   0.01262   0.00444  -0.0231   0.6460   0.7945
  -1.500  -0.0593   0.01252   0.00424  -0.0226   0.6439   0.8103
  -1.250  -0.0326   0.01243   0.00408  -0.0222   0.6420   0.8261
  -1.000  -0.0055   0.01236   0.00395  -0.0218   0.6401   0.8420
  -0.750   0.0225   0.01229   0.00385  -0.0216   0.6384   0.8584
  -0.500   0.0516   0.01224   0.00375  -0.0217   0.6362   0.8754
  -0.250   0.0826   0.01222   0.00368  -0.0222   0.6334   0.8927
   0.000   0.1159   0.01221   0.00364  -0.0233   0.6303   0.9104
   0.250   0.1515   0.01221   0.00360  -0.0249   0.6270   0.9282
   0.500   0.1887   0.01224   0.00358  -0.0269   0.6229   0.9460
   0.750   0.2271   0.01226   0.00357  -0.0293   0.6182   0.9640
   1.000   0.2659   0.01229   0.00359  -0.0318   0.6141   0.9824
   1.250   0.3066   0.01231   0.00362  -0.0349   0.6109   0.9993
   1.500   0.3311   0.01237   0.00367  -0.0346   0.6071   1.0000
   1.750   0.3555   0.01244   0.00377  -0.0343   0.6031   1.0000
   2.000   0.3806   0.01254   0.00393  -0.0340   0.5989   1.0000
   2.250   0.4060   0.01263   0.00409  -0.0337   0.5940   1.0000
   2.500   0.4315   0.01272   0.00430  -0.0335   0.5869   1.0000
   2.750   0.4568   0.01285   0.00450  -0.0332   0.5764   1.0000
   3.000   0.4817   0.01309   0.00467  -0.0325   0.5660   1.0000
   3.250   0.5072   0.01347   0.00483  -0.0320   0.5566   1.0000
   3.500   0.5363   0.01448   0.00541  -0.0322   0.5443   1.0000
   3.750   0.5645   0.01687   0.00746  -0.0328   0.5235   1.0000
   4.000   0.5849   0.01933   0.01010  -0.0323   0.5004   1.0000
   4.250   0.6051   0.01562   0.00716  -0.0300   0.4567   1.0000
   4.500   0.6287   0.01626   0.00759  -0.0293   0.4273   1.0000
   4.750   0.6521   0.01622   0.00785  -0.0284   0.3451   1.0000
   5.000   0.6678   0.01729   0.00808  -0.0269   0.1913   1.0000
   5.250   0.6841   0.01866   0.00884  -0.0255   0.1005   1.0000
   5.500   0.7028   0.01975   0.00974  -0.0243   0.0697   1.0000
   5.750   0.7226   0.02069   0.01066  -0.0232   0.0556   1.0000
   6.000   0.7431   0.02155   0.01164  -0.0220   0.0480   1.0000
   6.250   0.7617   0.02261   0.01276  -0.0207   0.0434   1.0000
   6.500   0.7789   0.02393   0.01413  -0.0191   0.0406   1.0000
   6.750   0.7990   0.02505   0.01539  -0.0178   0.0379   1.0000
   7.000   0.8195   0.02616   0.01664  -0.0168   0.0346   1.0000
   7.250   0.8396   0.02741   0.01794  -0.0159   0.0322   1.0000
   7.500   0.8596   0.02909   0.01969  -0.0148   0.0308   1.0000
   7.750   0.8797   0.03160   0.02232  -0.0139   0.0296   1.0000
   8.000   0.9011   0.03357   0.02453  -0.0129   0.0290   1.0000
   8.250   0.9209   0.03580   0.02709  -0.0118   0.0285   1.0000
   8.500   0.9384   0.03836   0.03007  -0.0105   0.0280   1.0000
   8.750   0.9526   0.04114   0.03328  -0.0090   0.0275   1.0000
   9.000   0.9637   0.04388   0.03646  -0.0072   0.0265   1.0000
   9.250   0.9717   0.04666   0.03963  -0.0055   0.0252   1.0000
   9.500   0.9762   0.04968   0.04302  -0.0037   0.0243   1.0000
   9.750   0.9751   0.05328   0.04699  -0.0018   0.0241   1.0000
  10.000   0.9685   0.05707   0.05113   0.0001   0.0239   1.0000
  10.250   0.9554   0.06085   0.05519   0.0021   0.0239   1.0000
  10.500   0.9378   0.06496   0.05955   0.0031   0.0239   1.0000
  10.750   0.9171   0.06991   0.06472   0.0022   0.0241   1.0000
  11.000   0.8940   0.07624   0.07123  -0.0012   0.0243   1.0000
  11.250   0.8685   0.08454   0.07968  -0.0075   0.0247   1.0000
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