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NASA SC(2)-0412 AIRFOIL (sc20412-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: NASA SC(2)-0412 AIRFOIL (sc20412-il)
Reynolds number: 50,000
Max Cl/Cd: 21.84 at α=6.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-sc20412-il-50000-n5.txt
Download as CSV file: xf-sc20412-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NASA SC(2)-0412 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.500  -0.7423   0.08558   0.07698  -0.0409   1.0000   0.0707
 -11.250  -0.7697   0.07879   0.07007  -0.0443   1.0000   0.0705
 -11.000  -0.7961   0.07316   0.06430  -0.0462   1.0000   0.0704
 -10.750  -0.8210   0.06853   0.05949  -0.0466   1.0000   0.0705
 -10.500  -0.8419   0.06418   0.05486  -0.0468   1.0000   0.0707
 -10.250  -0.8404   0.06127   0.05188  -0.0464   1.0000   0.0719
 -10.000  -0.8334   0.05893   0.04948  -0.0459   1.0000   0.0735
  -9.750  -0.8306   0.05611   0.04647  -0.0453   1.0000   0.0752
  -9.500  -0.8277   0.05302   0.04309  -0.0448   1.0000   0.0768
  -9.250  -0.8221   0.04986   0.03956  -0.0441   1.0000   0.0783
  -9.000  -0.8137   0.04684   0.03608  -0.0434   1.0000   0.0804
  -8.750  -0.8002   0.04440   0.03339  -0.0428   1.0000   0.0830
  -8.500  -0.7827   0.04266   0.03160  -0.0420   1.0000   0.0858
  -8.250  -0.7650   0.04073   0.02947  -0.0412   1.0000   0.0888
  -8.000  -0.7466   0.03880   0.02722  -0.0404   1.0000   0.0924
  -7.750  -0.7269   0.03712   0.02541  -0.0395   1.0000   0.0962
  -7.500  -0.7065   0.03577   0.02405  -0.0385   1.0000   0.1002
  -7.250  -0.6854   0.03444   0.02255  -0.0374   1.0000   0.1049
  -7.000  -0.6641   0.03322   0.02126  -0.0361   1.0000   0.1102
  -6.750  -0.6432   0.03221   0.02031  -0.0348   1.0000   0.1158
  -6.500  -0.6215   0.03131   0.01921  -0.0333   1.0000   0.1227
  -6.250  -0.6018   0.03040   0.01846  -0.0317   1.0000   0.1298
  -6.000  -0.5818   0.02960   0.01758  -0.0301   1.0000   0.1388
  -5.750  -0.5637   0.02870   0.01682  -0.0287   1.0000   0.1488
  -5.500  -0.5457   0.02781   0.01600  -0.0273   1.0000   0.1610
  -5.250  -0.5278   0.02686   0.01519  -0.0262   1.0000   0.1776
  -5.000  -0.5096   0.02582   0.01432  -0.0253   1.0000   0.2014
  -4.750  -0.4912   0.02451   0.01339  -0.0250   1.0000   0.2401
  -4.500  -0.4718   0.02290   0.01250  -0.0253   1.0000   0.3238
  -4.250  -0.4626   0.02272   0.01350  -0.0202   1.0000   0.4580
  -4.000  -0.4512   0.02387   0.01495  -0.0141   1.0000   0.5518
  -3.750  -0.4286   0.02431   0.01520  -0.0131   1.0000   0.6129
  -3.250  -0.3915   0.02556   0.01620  -0.0080   1.0000   0.6733
  -3.000  -0.3750   0.02613   0.01669  -0.0049   1.0000   0.6963
  -2.750  -0.3621   0.02676   0.01727  -0.0005   1.0000   0.7169
  -2.500  -0.3499   0.02728   0.01776   0.0039   1.0000   0.7376
  -2.250  -0.3374   0.02764   0.01808   0.0080   1.0000   0.7577
  -2.000  -0.3234   0.02778   0.01817   0.0114   1.0000   0.7752
  -1.750  -0.3080   0.02777   0.01810   0.0142   1.0000   0.7902
  -1.500  -0.2898   0.02763   0.01789   0.0157   1.0000   0.8025
  -1.250  -0.2702   0.02744   0.01764   0.0168   1.0000   0.8121
  -1.000  -0.2497   0.02722   0.01737   0.0175   1.0000   0.8195
  -0.750  -0.2287   0.02703   0.01712   0.0180   1.0000   0.8266
  -0.500  -0.2063   0.02686   0.01691   0.0180   1.0000   0.8332
  -0.250  -0.1857   0.02669   0.01671   0.0186   1.0000   0.8389
   0.000  -0.1617   0.02661   0.01661   0.0181   1.0000   0.8447
   0.250  -0.1311   0.02658   0.01657   0.0165   0.9963   0.8492
   0.500  -0.0950   0.02661   0.01659   0.0140   0.9894   0.8531
   0.750  -0.0553   0.02672   0.01671   0.0106   0.9823   0.8571
   1.000  -0.0166   0.02681   0.01683   0.0074   0.9733   0.8607
   1.250   0.0234   0.02687   0.01694   0.0042   0.9628   0.8637
   1.500   0.0644   0.02689   0.01703   0.0011   0.9509   0.8662
   1.750   0.1065   0.02689   0.01712  -0.0021   0.9381   0.8690
   2.000   0.1501   0.02683   0.01717  -0.0054   0.9240   0.8721
   2.250   0.1933   0.02668   0.01715  -0.0084   0.9069   0.8750
   2.500   0.2407   0.02623   0.01686  -0.0113   0.8818   0.8776
   2.750   0.2901   0.02535   0.01614  -0.0134   0.8507   0.8797
   3.000   0.3299   0.02453   0.01548  -0.0139   0.8189   0.8824
   3.250   0.3633   0.02388   0.01497  -0.0134   0.7828   0.8853
   3.500   0.3956   0.02326   0.01445  -0.0127   0.7333   0.8880
   3.750   0.4268   0.02274   0.01391  -0.0117   0.6497   0.8908
   4.000   0.4584   0.02276   0.01303  -0.0100   0.4698   0.8934
   4.250   0.4731   0.02386   0.01325  -0.0077   0.3402   0.8971
   4.500   0.4908   0.02496   0.01383  -0.0066   0.2642   0.9010
   4.750   0.5128   0.02594   0.01450  -0.0063   0.2206   0.9048
   5.000   0.5357   0.02681   0.01518  -0.0059   0.1937   0.9084
   5.250   0.5600   0.02760   0.01586  -0.0057   0.1743   0.9123
   5.500   0.5864   0.02846   0.01664  -0.0058   0.1597   0.9164
   5.750   0.6153   0.02931   0.01756  -0.0062   0.1466   0.9203
   6.000   0.6441   0.03018   0.01851  -0.0064   0.1366   0.9241
   6.250   0.6727   0.03120   0.01943  -0.0068   0.1282   0.9281
   6.500   0.7024   0.03226   0.02073  -0.0073   0.1200   0.9325
   6.750   0.7300   0.03342   0.02178  -0.0076   0.1138   0.9371
   7.000   0.7575   0.03470   0.02342  -0.0078   0.1072   0.9422
   7.250   0.7842   0.03599   0.02480  -0.0081   0.1019   0.9475
   7.500   0.8102   0.03759   0.02659  -0.0083   0.0971   0.9530
   7.750   0.8352   0.03942   0.02878  -0.0084   0.0925   0.9590
   8.000   0.8600   0.04099   0.03049  -0.0088   0.0885   0.9660
   8.250   0.8829   0.04322   0.03302  -0.0091   0.0850   0.9756
   8.500   0.9021   0.04603   0.03638  -0.0090   0.0821   1.0000
   8.750   0.9206   0.04862   0.03928  -0.0091   0.0791   1.0000
   9.000   0.9413   0.05072   0.04149  -0.0096   0.0764   1.0000
   9.250   0.9534   0.05399   0.04511  -0.0094   0.0744   1.0000
   9.500   0.9551   0.05833   0.05005  -0.0087   0.0732   1.0000
   9.750   0.9514   0.06287   0.05508  -0.0080   0.0722   1.0000
  10.000   0.9416   0.06758   0.06021  -0.0074   0.0713   1.0000
  10.250   0.9239   0.07242   0.06537  -0.0070   0.0708   1.0000
  10.500   0.8992   0.07815   0.07138  -0.0079   0.0708   1.0000
  10.750   0.8670   0.08583   0.07929  -0.0118   0.0712   1.0000
  11.000   0.8315   0.09633   0.08995  -0.0195   0.0720   1.0000
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