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NASA/LANGLEY RC-SC2 AIRFOIL (rcsc2-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: NASA/LANGLEY RC-SC2 AIRFOIL (rcsc2-il)
Reynolds number: 500,000
Max Cl/Cd: 56.35 at α=6.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-rcsc2-il-500000-n5.txt
Download as CSV file: xf-rcsc2-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NASA/LANGLEY RC-SC2 AIRFOIL                     
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -14.000  -0.9596   0.06317   0.05971  -0.0483   1.0000   0.0161
 -13.750  -0.9870   0.05446   0.05074  -0.0552   1.0000   0.0161
 -13.500  -1.0075   0.04868   0.04474  -0.0583   1.0000   0.0161
 -13.250  -1.0232   0.04448   0.04035  -0.0590   1.0000   0.0162
 -13.000  -1.0343   0.04133   0.03702  -0.0583   1.0000   0.0163
 -12.750  -1.0412   0.03891   0.03445  -0.0566   1.0000   0.0163
 -12.500  -1.0459   0.03695   0.03235  -0.0541   1.0000   0.0164
 -12.250  -1.0497   0.03535   0.03063  -0.0508   1.0000   0.0165
 -12.000  -1.0538   0.03399   0.02914  -0.0468   1.0000   0.0165
 -11.750  -1.0539   0.03266   0.02768  -0.0432   1.0000   0.0166
 -11.500  -1.0523   0.03145   0.02634  -0.0396   1.0000   0.0167
 -11.250  -1.0489   0.03031   0.02508  -0.0361   1.0000   0.0168
 -11.000  -1.0437   0.02921   0.02386  -0.0328   1.0000   0.0169
 -10.750  -1.0365   0.02816   0.02269  -0.0297   1.0000   0.0170
 -10.500  -1.0278   0.02715   0.02155  -0.0269   1.0000   0.0171
 -10.250  -1.0175   0.02616   0.02044  -0.0242   1.0000   0.0172
 -10.000  -0.9958   0.02503   0.01917  -0.0239   0.9989   0.0174
  -9.750  -0.9724   0.02395   0.01795  -0.0238   0.9975   0.0175
  -9.500  -0.9480   0.02293   0.01680  -0.0239   0.9962   0.0177
  -9.250  -0.9230   0.02198   0.01572  -0.0240   0.9951   0.0179
  -9.000  -0.8976   0.02109   0.01471  -0.0241   0.9941   0.0181
  -8.750  -0.8740   0.02027   0.01379  -0.0237   0.9926   0.0183
  -8.500  -0.8491   0.01951   0.01292  -0.0235   0.9910   0.0186
  -8.250  -0.8230   0.01879   0.01211  -0.0236   0.9894   0.0188
  -8.000  -0.7961   0.01812   0.01136  -0.0238   0.9880   0.0190
  -7.750  -0.7685   0.01751   0.01066  -0.0240   0.9868   0.0192
  -7.500  -0.7402   0.01689   0.00999  -0.0245   0.9858   0.0194
  -7.250  -0.7121   0.01618   0.00925  -0.0249   0.9848   0.0198
  -7.000  -0.6850   0.01567   0.00873  -0.0251   0.9834   0.0202
  -6.750  -0.6599   0.01524   0.00828  -0.0247   0.9810   0.0206
  -6.500  -0.6329   0.01482   0.00784  -0.0248   0.9792   0.0211
  -6.250  -0.6051   0.01440   0.00739  -0.0250   0.9777   0.0216
  -6.000  -0.5765   0.01399   0.00695  -0.0253   0.9764   0.0221
  -5.750  -0.5466   0.01360   0.00653  -0.0259   0.9752   0.0226
  -5.500  -0.5153   0.01324   0.00614  -0.0268   0.9742   0.0231
  -5.250  -0.4840   0.01278   0.00568  -0.0277   0.9733   0.0239
  -5.000  -0.4521   0.01242   0.00534  -0.0287   0.9725   0.0248
  -4.750  -0.4294   0.01217   0.00507  -0.0276   0.9690   0.0257
  -4.500  -0.4018   0.01191   0.00480  -0.0276   0.9668   0.0268
  -4.250  -0.3731   0.01164   0.00453  -0.0279   0.9650   0.0282
  -4.000  -0.3434   0.01136   0.00428  -0.0283   0.9635   0.0304
  -3.750  -0.3124   0.01110   0.00404  -0.0290   0.9620   0.0335
  -3.500  -0.2811   0.01083   0.00383  -0.0298   0.9605   0.0388
  -3.250  -0.2496   0.01056   0.00363  -0.0306   0.9592   0.0495
  -3.000  -0.2273   0.01037   0.00350  -0.0294   0.9541   0.0603
  -2.500  -0.1699   0.00986   0.00317  -0.0297   0.9483   0.0939
  -2.250  -0.1404   0.00956   0.00302  -0.0301   0.9463   0.1268
  -2.000  -0.1156   0.00928   0.00291  -0.0295   0.9426   0.1665
  -1.750  -0.0917   0.00893   0.00280  -0.0287   0.9379   0.2238
  -1.500  -0.0650   0.00848   0.00262  -0.0285   0.9334   0.2938
  -1.250  -0.0436   0.00785   0.00243  -0.0272   0.9253   0.4113
  -1.000  -0.0212   0.00713   0.00221  -0.0259   0.9169   0.5465
  -0.750  -0.0002   0.00669   0.00210  -0.0243   0.9060   0.6331
  -0.500   0.0243   0.00637   0.00200  -0.0232   0.8949   0.6939
  -0.250   0.0492   0.00608   0.00193  -0.0221   0.8826   0.7570
   0.000   0.0748   0.00589   0.00191  -0.0211   0.8701   0.8145
   0.250   0.1008   0.00581   0.00192  -0.0201   0.8496   0.8503
   0.500   0.1275   0.00581   0.00185  -0.0193   0.8140   0.8717
   0.750   0.1520   0.00597   0.00181  -0.0180   0.7535   0.8904
   1.000   0.1730   0.00637   0.00186  -0.0160   0.6658   0.9058
   1.250   0.1947   0.00680   0.00198  -0.0145   0.5876   0.9189
   1.500   0.2164   0.00729   0.00212  -0.0130   0.4985   0.9306
   1.750   0.2389   0.00784   0.00229  -0.0119   0.4021   0.9397
   2.000   0.2641   0.00828   0.00244  -0.0115   0.3306   0.9457
   2.250   0.2915   0.00865   0.00259  -0.0114   0.2770   0.9508
   2.500   0.3162   0.00900   0.00273  -0.0108   0.2277   0.9576
   2.750   0.3455   0.00943   0.00289  -0.0113   0.1746   0.9611
   3.000   0.3749   0.00981   0.00306  -0.0118   0.1310   0.9652
   3.250   0.4020   0.01013   0.00323  -0.0117   0.1029   0.9707
   3.500   0.4329   0.01041   0.00341  -0.0124   0.0848   0.9736
   3.750   0.4652   0.01067   0.00360  -0.0135   0.0722   0.9759
   4.000   0.4972   0.01094   0.00380  -0.0145   0.0620   0.9784
   4.250   0.5281   0.01121   0.00401  -0.0152   0.0527   0.9819
   4.500   0.5592   0.01150   0.00424  -0.0160   0.0419   0.9849
   4.750   0.5917   0.01184   0.00448  -0.0172   0.0329   0.9866
   5.000   0.6231   0.01215   0.00476  -0.0181   0.0290   0.9887
   5.250   0.6535   0.01247   0.00507  -0.0188   0.0268   0.9910
   5.500   0.6831   0.01278   0.00538  -0.0193   0.0253   0.9933
   5.750   0.7132   0.01312   0.00572  -0.0199   0.0240   0.9950
   6.000   0.7433   0.01354   0.00613  -0.0206   0.0230   0.9966
   6.250   0.7735   0.01388   0.00650  -0.0213   0.0224   0.9984
   6.500   0.8035   0.01426   0.00690  -0.0219   0.0218   1.0000
   6.750   0.8226   0.01460   0.00727  -0.0202   0.0214   1.0000
   7.000   0.8415   0.01496   0.00765  -0.0185   0.0210   1.0000
   7.250   0.8604   0.01534   0.00805  -0.0168   0.0206   1.0000
   7.500   0.8791   0.01574   0.00848  -0.0150   0.0203   1.0000
   7.750   0.8977   0.01617   0.00893  -0.0133   0.0200   1.0000
   8.000   0.9159   0.01666   0.00944  -0.0115   0.0197   1.0000
   8.250   0.9336   0.01722   0.01003  -0.0097   0.0194   1.0000
   8.500   0.9504   0.01790   0.01074  -0.0077   0.0192   1.0000
   8.750   0.9688   0.01843   0.01132  -0.0060   0.0190   1.0000
   9.000   0.9874   0.01900   0.01194  -0.0044   0.0189   1.0000
   9.250   1.0061   0.01958   0.01259  -0.0028   0.0187   1.0000
   9.500   1.0250   0.02019   0.01326  -0.0013   0.0186   1.0000
   9.750   1.0437   0.02083   0.01398   0.0001   0.0184   1.0000
  10.000   1.0623   0.02151   0.01473   0.0016   0.0181   1.0000
  10.250   1.0804   0.02225   0.01555   0.0030   0.0180   1.0000
  10.500   1.0979   0.02304   0.01643   0.0046   0.0178   1.0000
  10.750   1.1148   0.02388   0.01736   0.0061   0.0177   1.0000
  11.000   1.1311   0.02476   0.01834   0.0077   0.0176   1.0000
  11.250   1.1465   0.02570   0.01938   0.0094   0.0175   1.0000
  11.500   1.1609   0.02668   0.02047   0.0112   0.0174   1.0000
  11.750   1.1736   0.02769   0.02159   0.0132   0.0173   1.0000
  12.000   1.1840   0.02875   0.02277   0.0155   0.0172   1.0000
  12.250   1.1930   0.02989   0.02402   0.0180   0.0171   1.0000
  12.500   1.2008   0.03110   0.02537   0.0203   0.0170   1.0000
  12.750   1.2073   0.03243   0.02682   0.0227   0.0170   1.0000
  13.000   1.2122   0.03388   0.02841   0.0250   0.0169   1.0000
  13.250   1.2156   0.03547   0.03014   0.0273   0.0169   1.0000
  13.500   1.2172   0.03724   0.03206   0.0294   0.0168   1.0000
  13.750   1.2169   0.03924   0.03420   0.0313   0.0167   1.0000
  14.000   1.2146   0.04151   0.03664   0.0328   0.0167   1.0000
  14.250   1.2101   0.04414   0.03942   0.0340   0.0167   1.0000
  14.500   1.2031   0.04724   0.04270   0.0345   0.0166   1.0000
  14.750   1.1934   0.05099   0.04662   0.0342   0.0166   1.0000
  15.000   1.1803   0.05561   0.05143   0.0328   0.0166   1.0000
  15.250   1.1630   0.06155   0.05758   0.0298   0.0166   1.0000
  15.500   1.1387   0.06962   0.06588   0.0245   0.0166   1.0000
  15.750   1.0992   0.08224   0.07880   0.0155   0.0167   1.0000
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