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NACA 63012A AIRFOIL (n63012a-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: NACA 63012A AIRFOIL (n63012a-il)
Reynolds number: 200,000
Max Cl/Cd: 51.95 at α=4.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-n63012a-il-200000.txt
Download as CSV file: xf-n63012a-il-200000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.250  -0.5141   0.11904   0.11558  -0.0069   1.0000   0.0712
 -12.000  -0.5189   0.11475   0.11130  -0.0085   1.0000   0.0735
 -11.500  -0.6962   0.10499   0.10148  -0.0063   1.0000   0.0680
  -9.750  -0.8905   0.05026   0.04509  -0.0230   1.0000   0.0416
  -9.500  -0.8901   0.04594   0.04049  -0.0212   1.0000   0.0405
  -9.250  -0.8863   0.04211   0.03631  -0.0191   1.0000   0.0399
  -9.000  -0.8795   0.03833   0.03212  -0.0170   1.0000   0.0391
  -8.750  -0.8694   0.03444   0.02774  -0.0148   1.0000   0.0378
  -8.500  -0.8542   0.03145   0.02433  -0.0130   1.0000   0.0374
  -8.250  -0.8354   0.02919   0.02178  -0.0117   1.0000   0.0377
  -8.000  -0.8146   0.02729   0.01967  -0.0106   1.0000   0.0383
  -7.750  -0.7933   0.02581   0.01804  -0.0096   1.0000   0.0396
  -7.500  -0.7717   0.02459   0.01665  -0.0086   1.0000   0.0414
  -7.250  -0.7495   0.02341   0.01530  -0.0075   1.0000   0.0426
  -7.000  -0.7277   0.02172   0.01353  -0.0064   1.0000   0.0439
  -6.750  -0.7088   0.02021   0.01207  -0.0051   1.0000   0.0461
  -6.500  -0.6906   0.01927   0.01116  -0.0035   1.0000   0.0487
  -6.250  -0.6725   0.01857   0.01040  -0.0018   1.0000   0.0525
  -6.000  -0.6589   0.01745   0.00932   0.0005   1.0000   0.0571
  -5.750  -0.6437   0.01672   0.00860   0.0026   1.0000   0.0631
  -5.500  -0.6312   0.01583   0.00776   0.0051   1.0000   0.0717
  -5.250  -0.6182   0.01508   0.00707   0.0075   1.0000   0.0876
  -5.000  -0.6072   0.01404   0.00633   0.0099   1.0000   0.1298
  -4.750  -0.6006   0.01233   0.00556   0.0124   1.0000   0.2914
  -4.500  -0.5886   0.01133   0.00535   0.0144   1.0000   0.4545
  -4.250  -0.5496   0.01104   0.00535   0.0117   0.9938   0.5460
  -4.000  -0.5102   0.01097   0.00535   0.0092   0.9864   0.5925
  -3.750  -0.4710   0.01097   0.00538   0.0069   0.9794   0.6260
  -3.500  -0.4311   0.01100   0.00541   0.0045   0.9724   0.6543
  -3.250  -0.3933   0.01105   0.00545   0.0025   0.9650   0.6786
  -3.000  -0.3540   0.01110   0.00552   0.0005   0.9585   0.7010
  -2.750  -0.3182   0.01114   0.00556  -0.0009   0.9508   0.7196
  -2.500  -0.2821   0.01112   0.00553  -0.0022   0.9431   0.7352
  -2.250  -0.2498   0.01109   0.00548  -0.0029   0.9337   0.7484
  -2.000  -0.2159   0.01101   0.00538  -0.0039   0.9260   0.7605
  -1.750  -0.1877   0.01095   0.00527  -0.0037   0.9147   0.7717
  -1.500  -0.1585   0.01088   0.00522  -0.0036   0.9050   0.7808
  -1.250  -0.1301   0.01080   0.00511  -0.0034   0.8955   0.7911
  -1.000  -0.1044   0.01076   0.00505  -0.0028   0.8839   0.8019
  -0.750  -0.0778   0.01073   0.00502  -0.0021   0.8735   0.8111
  -0.500  -0.0512   0.01068   0.00495  -0.0015   0.8642   0.8216
  -0.250  -0.0261   0.01067   0.00494  -0.0007   0.8525   0.8326
   0.000   0.0000   0.01068   0.00496   0.0000   0.8420   0.8420
   0.250   0.0261   0.01067   0.00494   0.0007   0.8326   0.8525
   0.500   0.0512   0.01068   0.00495   0.0015   0.8216   0.8642
   0.750   0.0778   0.01073   0.00502   0.0021   0.8111   0.8734
   1.000   0.1044   0.01076   0.00505   0.0028   0.8019   0.8839
   1.250   0.1301   0.01080   0.00511   0.0034   0.7911   0.8955
   1.500   0.1585   0.01088   0.00522   0.0037   0.7808   0.9050
   1.750   0.1877   0.01094   0.00527   0.0037   0.7716   0.9148
   2.000   0.2158   0.01101   0.00538   0.0039   0.7605   0.9260
   2.250   0.2497   0.01109   0.00548   0.0029   0.7485   0.9338
   2.500   0.2820   0.01112   0.00553   0.0023   0.7352   0.9431
   2.750   0.3180   0.01114   0.00556   0.0009   0.7196   0.9509
   3.000   0.3539   0.01110   0.00552  -0.0005   0.7010   0.9586
   3.250   0.3930   0.01105   0.00544  -0.0025   0.6787   0.9652
   3.500   0.4310   0.01100   0.00541  -0.0044   0.6543   0.9725
   3.750   0.4708   0.01097   0.00538  -0.0068   0.6261   0.9796
   4.000   0.5101   0.01097   0.00534  -0.0092   0.5926   0.9865
   4.250   0.5494   0.01103   0.00535  -0.0117   0.5461   0.9940
   4.500   0.5881   0.01132   0.00535  -0.0143   0.4560   1.0000
   4.750   0.6001   0.01230   0.00555  -0.0123   0.2941   1.0000
   5.000   0.6067   0.01402   0.00631  -0.0098   0.1309   1.0000
   5.250   0.6176   0.01507   0.00706  -0.0074   0.0879   1.0000
   5.500   0.6308   0.01582   0.00775  -0.0050   0.0718   1.0000
   5.750   0.6433   0.01671   0.00859  -0.0026   0.0632   1.0000
   6.000   0.6586   0.01744   0.00931  -0.0005   0.0571   1.0000
   6.250   0.6723   0.01856   0.01039   0.0018   0.0525   1.0000
   6.500   0.6904   0.01927   0.01115   0.0035   0.0487   1.0000
   6.750   0.7086   0.02020   0.01207   0.0051   0.0461   1.0000
   7.000   0.7276   0.02172   0.01352   0.0064   0.0439   1.0000
   7.250   0.7495   0.02341   0.01529   0.0075   0.0426   1.0000
   7.500   0.7717   0.02459   0.01665   0.0085   0.0414   1.0000
   7.750   0.7934   0.02581   0.01803   0.0096   0.0396   1.0000
   8.000   0.8148   0.02729   0.01968   0.0106   0.0383   1.0000
   8.250   0.8356   0.02919   0.02179   0.0116   0.0377   1.0000
   8.500   0.8546   0.03147   0.02435   0.0129   0.0374   1.0000
   8.750   0.8698   0.03447   0.02777   0.0147   0.0378   1.0000
   9.000   0.8800   0.03837   0.03216   0.0169   0.0391   1.0000
   9.250   0.8869   0.04216   0.03636   0.0190   0.0399   1.0000
   9.500   0.8907   0.04600   0.04055   0.0210   0.0406   1.0000
   9.750   0.8912   0.05035   0.04518   0.0229   0.0416   1.0000
  10.000   0.7736   0.06033   0.05641   0.0315   0.0779   1.0000
  10.250   0.7385   0.06291   0.05919   0.0346   0.0775   1.0000
  10.500   0.7093   0.06724   0.06364   0.0351   0.0775   1.0000
  10.750   0.6830   0.07259   0.06907   0.0341   0.0776   1.0000
  11.000   0.6562   0.07871   0.07526   0.0321   0.0777   1.0000
  11.250   0.6276   0.08575   0.08236   0.0289   0.0778   1.0000
  11.500   0.5978   0.09391   0.09055   0.0243   0.0779   1.0000
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