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NASA SC(2)-0712 AIRFOIL (sc20712-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: NASA SC(2)-0712 AIRFOIL (sc20712-il)
Reynolds number: 100,000
Max Cl/Cd: 33.44 at α=2°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-sc20712-il-100000-n5.txt
Download as CSV file: xf-sc20712-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NASA SC(2)-0712 AIRFOIL                         
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -13.000  -0.7020   0.08011   0.07384  -0.0571   1.0000   0.0443
 -12.750  -0.7486   0.07008   0.06362  -0.0631   1.0000   0.0439
 -12.500  -0.7830   0.06379   0.05713  -0.0653   1.0000   0.0438
 -12.250  -0.8120   0.05921   0.05238  -0.0651   1.0000   0.0438
 -12.000  -0.8387   0.05579   0.04880  -0.0632   1.0000   0.0439
 -11.750  -0.8611   0.05269   0.04551  -0.0610   1.0000   0.0440
 -11.500  -0.8745   0.04928   0.04181  -0.0601   1.0000   0.0444
 -11.250  -0.8807   0.04596   0.03810  -0.0592   1.0000   0.0450
 -11.000  -0.8791   0.04306   0.03483  -0.0584   1.0000   0.0459
 -10.750  -0.8663   0.04170   0.03346  -0.0576   1.0000   0.0469
 -10.500  -0.8531   0.04028   0.03195  -0.0570   1.0000   0.0480
 -10.250  -0.8392   0.03863   0.03011  -0.0564   1.0000   0.0494
 -10.000  -0.8241   0.03671   0.02792  -0.0560   1.0000   0.0510
  -9.750  -0.8072   0.03474   0.02560  -0.0555   1.0000   0.0524
  -9.500  -0.7887   0.03324   0.02397  -0.0550   1.0000   0.0539
  -9.250  -0.7692   0.03223   0.02295  -0.0546   1.0000   0.0556
  -9.000  -0.7488   0.03116   0.02177  -0.0542   1.0000   0.0577
  -8.750  -0.7278   0.02997   0.02039  -0.0537   1.0000   0.0600
  -8.500  -0.7064   0.02881   0.01907  -0.0531   1.0000   0.0620
  -8.250  -0.6850   0.02792   0.01825  -0.0527   1.0000   0.0642
  -8.000  -0.6625   0.02712   0.01741  -0.0525   1.0000   0.0672
  -7.750  -0.6396   0.02631   0.01646  -0.0520   1.0000   0.0703
  -7.500  -0.6169   0.02544   0.01560  -0.0517   1.0000   0.0731
  -7.250  -0.5930   0.02476   0.01496  -0.0517   1.0000   0.0768
  -7.000  -0.5685   0.02414   0.01427  -0.0516   1.0000   0.0814
  -6.750  -0.5434   0.02341   0.01360  -0.0518   1.0000   0.0856
  -6.500  -0.5174   0.02284   0.01303  -0.0521   1.0000   0.0913
  -6.250  -0.4906   0.02226   0.01246  -0.0526   1.0000   0.0979
  -6.000  -0.4631   0.02173   0.01196  -0.0533   1.0000   0.1058
  -5.750  -0.4346   0.02120   0.01149  -0.0542   1.0000   0.1158
  -5.500  -0.4055   0.02072   0.01110  -0.0553   1.0000   0.1295
  -5.250  -0.3752   0.02022   0.01074  -0.0566   1.0000   0.1510
  -5.000  -0.3427   0.01963   0.01038  -0.0586   1.0000   0.1897
  -4.750  -0.3040   0.01872   0.01000  -0.0623   1.0000   0.2775
  -4.500  -0.2649   0.01786   0.01010  -0.0659   1.0000   0.4411
  -4.250  -0.2486   0.01832   0.01099  -0.0627   0.9998   0.5309
  -4.000  -0.2176   0.01873   0.01142  -0.0631   0.9968   0.5790
  -3.750  -0.1851   0.01919   0.01182  -0.0638   0.9940   0.6085
  -3.500  -0.1529   0.01960   0.01214  -0.0646   0.9909   0.6322
  -3.250  -0.1256   0.02015   0.01267  -0.0640   0.9871   0.6485
  -3.000  -0.0987   0.02082   0.01334  -0.0630   0.9836   0.6644
  -2.750  -0.0760   0.02147   0.01400  -0.0610   0.9794   0.6776
  -2.500  -0.0497   0.02192   0.01444  -0.0602   0.9751   0.6902
  -2.250  -0.0203   0.02229   0.01479  -0.0602   0.9716   0.6998
  -2.000   0.0120   0.02250   0.01497  -0.0610   0.9685   0.7070
  -1.750   0.0360   0.02269   0.01518  -0.0600   0.9631   0.7127
  -1.500   0.0740   0.02274   0.01519  -0.0627   0.9595   0.7210
  -1.250   0.1067   0.02284   0.01530  -0.0635   0.9559   0.7245
  -1.000   0.1338   0.02289   0.01537  -0.0635   0.9501   0.7278
  -0.750   0.1667   0.02291   0.01541  -0.0648   0.9454   0.7315
  -0.500   0.2061   0.02288   0.01540  -0.0676   0.9419   0.7356
  -0.250   0.2427   0.02282   0.01536  -0.0699   0.9358   0.7394
   0.000   0.2774   0.02267   0.01529  -0.0710   0.9279   0.7416
   0.250   0.3140   0.02236   0.01504  -0.0722   0.9163   0.7441
   0.500   0.3591   0.02166   0.01442  -0.0745   0.9004   0.7467
   0.750   0.4062   0.02077   0.01359  -0.0770   0.8825   0.7493
   1.000   0.4517   0.01993   0.01281  -0.0793   0.8631   0.7519
   1.250   0.4875   0.01943   0.01238  -0.0803   0.8390   0.7553
   1.500   0.5199   0.01898   0.01200  -0.0803   0.8106   0.7575
   1.750   0.5533   0.01852   0.01157  -0.0802   0.7663   0.7597
   2.000   0.6043   0.01807   0.01050  -0.0825   0.6050   0.7614
   2.250   0.6236   0.01930   0.01061  -0.0805   0.4089   0.7640
   2.500   0.6432   0.02045   0.01104  -0.0794   0.2806   0.7671
   2.750   0.6677   0.02136   0.01149  -0.0794   0.2035   0.7702
   3.000   0.6941   0.02208   0.01193  -0.0796   0.1620   0.7729
   3.250   0.7166   0.02269   0.01239  -0.0787   0.1392   0.7747
   3.750   0.7643   0.02384   0.01347  -0.0774   0.1115   0.7792
   4.000   0.7891   0.02446   0.01408  -0.0770   0.1022   0.7820
   4.250   0.8142   0.02519   0.01474  -0.0769   0.0946   0.7851
   4.500   0.8424   0.02586   0.01548  -0.0773   0.0876   0.7884
   4.750   0.8641   0.02659   0.01617  -0.0762   0.0829   0.7905
   5.000   0.8880   0.02731   0.01697  -0.0755   0.0780   0.7928
   5.250   0.9124   0.02805   0.01774  -0.0750   0.0737   0.7954
   5.500   0.9371   0.02904   0.01868  -0.0748   0.0706   0.7984
   5.750   0.9646   0.02996   0.01975  -0.0749   0.0670   0.8016
   6.000   0.9910   0.03085   0.02069  -0.0749   0.0637   0.8045
   6.250   1.0136   0.03185   0.02165  -0.0742   0.0614   0.8070
   6.500   1.0387   0.03303   0.02304  -0.0737   0.0591   0.8097
   6.750   1.0634   0.03417   0.02436  -0.0733   0.0566   0.8127
   7.000   1.0880   0.03522   0.02547  -0.0731   0.0544   0.8158
   7.250   1.1135   0.03655   0.02677  -0.0733   0.0526   0.8187
   7.500   1.1356   0.03824   0.02884  -0.0724   0.0510   0.8210
   7.750   1.1559   0.03988   0.03078  -0.0713   0.0493   0.8234
   8.000   1.1754   0.04130   0.03240  -0.0703   0.0476   0.8262
   8.250   1.1950   0.04255   0.03372  -0.0695   0.0463   0.8292
   8.500   1.2137   0.04434   0.03564  -0.0688   0.0451   0.8325
   8.750   1.2252   0.04715   0.03900  -0.0668   0.0440   0.8355
   9.000   1.2320   0.04995   0.04226  -0.0642   0.0432   0.8383
   9.250   1.2361   0.05281   0.04552  -0.0615   0.0423   0.8413
   9.500   1.2385   0.05555   0.04859  -0.0590   0.0416   0.8444
   9.750   1.2409   0.05801   0.05130  -0.0567   0.0408   0.8476
  10.000   1.2418   0.06020   0.05368  -0.0542   0.0402   0.8505
  10.250   1.2373   0.06214   0.05577  -0.0509   0.0397   0.8534
  10.500   1.2347   0.06437   0.05814  -0.0484   0.0393   0.8568
  10.750   1.2214   0.06779   0.06179  -0.0458   0.0390   0.8600
  11.000   1.1919   0.07301   0.06743  -0.0436   0.0388   0.8628
  11.250   1.1618   0.07892   0.07366  -0.0431   0.0388   0.8651
  11.500   1.1290   0.08589   0.08093  -0.0447   0.0388   0.8671
  11.750   1.0949   0.09453   0.08982  -0.0490   0.0390   0.8688
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