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NASA SC(2)-0612 AIRFOIL (sc20612-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: NASA SC(2)-0612 AIRFOIL (sc20612-il)
Reynolds number: 200,000
Max Cl/Cd: 44.55 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-sc20612-il-200000-n5.txt
Download as CSV file: xf-sc20612-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NASA SC(2)-0612 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
  ------ -------- --------- --------- -------- -------- --------
 -15.500  -0.8834   0.08485   0.07994  -0.0481   1.0000   0.0274
 -15.250  -0.9214   0.07366   0.06847  -0.0557   1.0000   0.0273
 -15.000  -0.9482   0.06594   0.06049  -0.0604   1.0000   0.0274
 -14.750  -0.9687   0.05996   0.05426  -0.0634   1.0000   0.0275
 -14.500  -0.9844   0.05509   0.04913  -0.0652   1.0000   0.0276
 -14.250  -0.9926   0.05143   0.04529  -0.0661   1.0000   0.0278
 -14.000  -0.9942   0.04874   0.04251  -0.0664   1.0000   0.0280
 -13.750  -0.9940   0.04638   0.04006  -0.0664   1.0000   0.0283
 -13.500  -0.9929   0.04424   0.03784  -0.0661   1.0000   0.0286
 -13.250  -0.9914   0.04227   0.03577  -0.0655   1.0000   0.0289
 -13.000  -0.9900   0.04044   0.03384  -0.0645   1.0000   0.0292
 -12.750  -0.9891   0.03879   0.03209  -0.0631   1.0000   0.0296
 -12.500  -0.9897   0.03730   0.03049  -0.0610   1.0000   0.0300
 -12.250  -0.9913   0.03593   0.02901  -0.0585   1.0000   0.0305
 -12.000  -0.9875   0.03448   0.02741  -0.0568   1.0000   0.0312
 -11.750  -0.9808   0.03303   0.02578  -0.0553   1.0000   0.0319
 -11.500  -0.9714   0.03169   0.02428  -0.0541   1.0000   0.0326
 -11.250  -0.9594   0.03064   0.02322  -0.0531   1.0000   0.0331
 -11.000  -0.9456   0.02968   0.02222  -0.0522   1.0000   0.0338
 -10.750  -0.9305   0.02873   0.02120  -0.0514   1.0000   0.0346
 -10.500  -0.9146   0.02777   0.02016  -0.0505   1.0000   0.0355
 -10.250  -0.8976   0.02682   0.01909  -0.0496   1.0000   0.0365
 -10.000  -0.8797   0.02590   0.01801  -0.0488   1.0000   0.0377
  -9.750  -0.8610   0.02511   0.01724  -0.0482   1.0000   0.0387
  -9.500  -0.8410   0.02445   0.01656  -0.0478   1.0000   0.0401
  -9.250  -0.8203   0.02378   0.01582  -0.0474   1.0000   0.0417
  -9.000  -0.7991   0.02309   0.01501  -0.0469   1.0000   0.0435
  -8.750  -0.7775   0.02235   0.01428  -0.0467   1.0000   0.0450
  -8.500  -0.7548   0.02176   0.01368  -0.0466   1.0000   0.0468
  -8.250  -0.7267   0.02118   0.01303  -0.0474   0.9991   0.0495
  -8.000  -0.6948   0.02050   0.01233  -0.0491   0.9974   0.0523
  -7.750  -0.6622   0.01995   0.01177  -0.0508   0.9956   0.0553
  -7.250  -0.5969   0.01885   0.01063  -0.0543   0.9926   0.0620
  -7.000  -0.5650   0.01841   0.01016  -0.0558   0.9906   0.0660
  -6.750  -0.5320   0.01790   0.00964  -0.0575   0.9885   0.0699
  -6.500  -0.4982   0.01745   0.00922  -0.0594   0.9866   0.0746
  -6.250  -0.4639   0.01706   0.00881  -0.0613   0.9849   0.0797
  -6.000  -0.4286   0.01662   0.00840  -0.0635   0.9834   0.0862
  -5.750  -0.3927   0.01622   0.00802  -0.0657   0.9820   0.0936
  -5.500  -0.3603   0.01582   0.00766  -0.0672   0.9789   0.1023
  -5.250  -0.3259   0.01540   0.00730  -0.0692   0.9765   0.1146
  -5.000  -0.2907   0.01499   0.00699  -0.0713   0.9746   0.1321
  -4.750  -0.2542   0.01452   0.00668  -0.0738   0.9731   0.1644
  -4.500  -0.2157   0.01389   0.00636  -0.0771   0.9721   0.2246
  -4.250  -0.1748   0.01310   0.00602  -0.0811   0.9715   0.3235
  -4.000  -0.1330   0.01230   0.00590  -0.0851   0.9712   0.4616
  -3.750  -0.0984   0.01227   0.00625  -0.0864   0.9698   0.5509
  -3.500  -0.0696   0.01238   0.00641  -0.0864   0.9654   0.5829
  -3.250  -0.0370   0.01246   0.00648  -0.0874   0.9623   0.6047
  -3.000  -0.0037   0.01260   0.00662  -0.0883   0.9597   0.6234
  -2.750   0.0300   0.01280   0.00685  -0.0892   0.9575   0.6404
  -2.500   0.0653   0.01300   0.00705  -0.0904   0.9558   0.6553
  -2.250   0.0881   0.01332   0.00743  -0.0888   0.9494   0.6649
  -2.000   0.1199   0.01351   0.00764  -0.0893   0.9461   0.6747
  -1.750   0.1521   0.01366   0.00783  -0.0898   0.9437   0.6805
  -1.500   0.1889   0.01364   0.00780  -0.0917   0.9422   0.6856
  -1.250   0.2218   0.01356   0.00771  -0.0928   0.9367   0.6899
  -1.000   0.2551   0.01346   0.00766  -0.0933   0.9303   0.6925
  -0.750   0.2906   0.01328   0.00752  -0.0943   0.9230   0.6955
  -0.500   0.3285   0.01290   0.00715  -0.0955   0.9105   0.6983
  -0.250   0.3600   0.01260   0.00684  -0.0956   0.8908   0.7009
   0.000   0.3940   0.01231   0.00653  -0.0963   0.8688   0.7036
   0.250   0.4289   0.01204   0.00617  -0.0972   0.8375   0.7066
   0.500   0.4603   0.01193   0.00597  -0.0974   0.8016   0.7085
   0.750   0.4887   0.01196   0.00589  -0.0968   0.7555   0.7102
   1.000   0.5144   0.01220   0.00582  -0.0957   0.6752   0.7121
   1.250   0.5330   0.01303   0.00592  -0.0934   0.5288   0.7142
   1.500   0.5518   0.01400   0.00625  -0.0917   0.3981   0.7165
   1.750   0.5742   0.01480   0.00657  -0.0909   0.2961   0.7187
   2.000   0.5986   0.01548   0.00685  -0.0906   0.2198   0.7211
   2.250   0.6252   0.01599   0.00711  -0.0907   0.1707   0.7237
   2.500   0.6531   0.01644   0.00736  -0.0910   0.1389   0.7263
   2.750   0.6785   0.01684   0.00768  -0.0905   0.1203   0.7277
   3.000   0.7038   0.01723   0.00803  -0.0900   0.1076   0.7293
   3.250   0.7292   0.01763   0.00840  -0.0895   0.0977   0.7312
   3.500   0.7552   0.01799   0.00877  -0.0891   0.0901   0.7333
   3.750   0.7806   0.01845   0.00916  -0.0887   0.0836   0.7357
   4.000   0.8073   0.01879   0.00955  -0.0885   0.0784   0.7382
   4.250   0.8336   0.01924   0.00996  -0.0883   0.0736   0.7409
   4.500   0.8607   0.01967   0.01040  -0.0883   0.0696   0.7435
   4.750   0.8872   0.02008   0.01083  -0.0881   0.0656   0.7456
   5.000   0.9108   0.02063   0.01136  -0.0874   0.0623   0.7471
   5.250   0.9357   0.02107   0.01189  -0.0867   0.0592   0.7489
   5.500   0.9601   0.02155   0.01240  -0.0861   0.0561   0.7510
   5.750   0.9838   0.02217   0.01302  -0.0854   0.0534   0.7533
   6.000   1.0087   0.02270   0.01364  -0.0849   0.0506   0.7558
   6.250   1.0334   0.02328   0.01425  -0.0844   0.0483   0.7583
   6.500   1.0574   0.02400   0.01494  -0.0840   0.0463   0.7609
   6.750   1.0826   0.02462   0.01568  -0.0836   0.0440   0.7633
   7.000   1.1055   0.02522   0.01635  -0.0827   0.0420   0.7650
   7.250   1.1278   0.02584   0.01701  -0.0818   0.0405   0.7668
   7.500   1.1496   0.02667   0.01792  -0.0808   0.0392   0.7690
   7.750   1.1720   0.02751   0.01890  -0.0799   0.0378   0.7716
   8.000   1.1942   0.02831   0.01980  -0.0791   0.0365   0.7744
   8.250   1.2162   0.02905   0.02058  -0.0783   0.0353   0.7773
   8.500   1.2377   0.02987   0.02141  -0.0776   0.0344   0.7801
   8.750   1.2575   0.03089   0.02262  -0.0763   0.0333   0.7819
   9.000   1.2765   0.03195   0.02386  -0.0749   0.0323   0.7840
   9.250   1.2947   0.03302   0.02509  -0.0735   0.0315   0.7864
   9.500   1.3122   0.03407   0.02626  -0.0721   0.0308   0.7891
   9.750   1.3291   0.03512   0.02740  -0.0706   0.0302   0.7920
  10.000   1.3451   0.03624   0.02859  -0.0692   0.0297   0.7949
  10.250   1.3594   0.03758   0.03001  -0.0675   0.0293   0.7975
  10.500   1.3700   0.03928   0.03200  -0.0652   0.0288   0.7995
  10.750   1.3775   0.04104   0.03405  -0.0626   0.0282   0.8018
  11.000   1.3802   0.04273   0.03599  -0.0593   0.0277   0.8044
  11.250   1.3831   0.04455   0.03804  -0.0563   0.0272   0.8073
  11.500   1.3855   0.04642   0.04010  -0.0537   0.0268   0.8102
  11.750   1.3871   0.04838   0.04226  -0.0513   0.0264   0.8132
  12.000   1.3866   0.05044   0.04449  -0.0489   0.0261   0.8154
  12.250   1.3851   0.05260   0.04682  -0.0467   0.0258   0.8179
  12.500   1.3819   0.05508   0.04945  -0.0448   0.0256   0.8207
  12.750   1.3766   0.05794   0.05248  -0.0433   0.0254   0.8237
  13.000   1.3691   0.06125   0.05596  -0.0423   0.0253   0.8267
  13.250   1.3588   0.06514   0.06002  -0.0419   0.0251   0.8295
  13.500   1.3451   0.06966   0.06475  -0.0421   0.0250   0.8317
  13.750   1.3250   0.07551   0.07084  -0.0436   0.0249   0.8337
  14.000   1.2968   0.08350   0.07914  -0.0473   0.0249   0.8355
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