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NASA/LANGLEY RC10-64C AIRFOIL (rc1064c-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: NASA/LANGLEY RC10-64C AIRFOIL (rc1064c-il)
Reynolds number: 500,000
Max Cl/Cd: 59.38 at α=7.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-rc1064c-il-500000-n5.txt
Download as CSV file: xf-rc1064c-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NASA/LANGLEY RC10-64C 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
  ------ -------- --------- --------- -------- -------- --------
 -12.750  -0.9440   0.04753   0.04456  -0.0525   1.0000   0.0110
 -12.500  -0.9661   0.04327   0.04007  -0.0514   1.0000   0.0110
 -12.250  -0.9798   0.04049   0.03711  -0.0486   1.0000   0.0111
 -12.000  -0.9913   0.03836   0.03480  -0.0446   1.0000   0.0112
 -11.750  -0.9962   0.03642   0.03269  -0.0410   1.0000   0.0114
 -11.500  -0.9963   0.03451   0.03059  -0.0379   1.0000   0.0115
 -11.250  -0.9935   0.03271   0.02859  -0.0350   1.0000   0.0118
 -11.000  -0.9885   0.03099   0.02665  -0.0322   1.0000   0.0120
 -10.750  -0.9810   0.02942   0.02488  -0.0295   1.0000   0.0123
 -10.500  -0.9712   0.02803   0.02327  -0.0271   1.0000   0.0126
 -10.250  -0.9600   0.02677   0.02182  -0.0247   1.0000   0.0129
 -10.000  -0.9415   0.02548   0.02031  -0.0238   0.9990   0.0133
  -9.750  -0.9187   0.02422   0.01884  -0.0237   0.9969   0.0135
  -9.500  -0.8958   0.02310   0.01752  -0.0235   0.9947   0.0137
  -9.250  -0.8766   0.02147   0.01568  -0.0227   0.9920   0.0141
  -9.000  -0.8562   0.02031   0.01438  -0.0218   0.9883   0.0144
  -8.500  -0.8112   0.01875   0.01266  -0.0206   0.9801   0.0151
  -8.250  -0.7862   0.01811   0.01194  -0.0205   0.9771   0.0156
  -8.000  -0.7597   0.01748   0.01123  -0.0206   0.9742   0.0161
  -7.750  -0.7320   0.01682   0.01047  -0.0209   0.9714   0.0167
  -7.500  -0.7028   0.01612   0.00967  -0.0215   0.9691   0.0172
  -7.250  -0.6720   0.01545   0.00890  -0.0225   0.9668   0.0176
  -7.000  -0.6397   0.01484   0.00820  -0.0238   0.9647   0.0180
  -6.750  -0.6071   0.01416   0.00745  -0.0251   0.9629   0.0184
  -6.250  -0.5423   0.01293   0.00613  -0.0278   0.9591   0.0200
  -6.000  -0.5089   0.01251   0.00568  -0.0293   0.9574   0.0211
  -5.750  -0.4758   0.01211   0.00524  -0.0306   0.9554   0.0223
  -5.500  -0.4431   0.01175   0.00482  -0.0319   0.9533   0.0232
  -5.250  -0.4110   0.01135   0.00439  -0.0330   0.9509   0.0246
  -5.000  -0.3792   0.01103   0.00405  -0.0341   0.9475   0.0269
  -4.750  -0.3500   0.01082   0.00380  -0.0345   0.9433   0.0295
  -4.500  -0.3211   0.01063   0.00360  -0.0348   0.9394   0.0340
  -4.250  -0.2958   0.01048   0.00346  -0.0343   0.9356   0.0403
  -4.000  -0.2697   0.01033   0.00335  -0.0341   0.9320   0.0510
  -3.750  -0.2447   0.01021   0.00327  -0.0335   0.9281   0.0626
  -3.500  -0.2194   0.01011   0.00321  -0.0330   0.9243   0.0739
  -3.250  -0.1950   0.00995   0.00312  -0.0323   0.9202   0.0873
  -3.000  -0.1699   0.00983   0.00304  -0.0318   0.9161   0.1032
  -2.500  -0.1243   0.00928   0.00286  -0.0299   0.8913   0.1761
  -2.250  -0.0975   0.00920   0.00274  -0.0295   0.8752   0.1876
  -2.000  -0.0707   0.00904   0.00253  -0.0291   0.8670   0.1936
  -1.750  -0.0446   0.00883   0.00227  -0.0285   0.8604   0.1992
  -1.500  -0.0196   0.00858   0.00199  -0.0278   0.8535   0.2042
  -1.250   0.0067   0.00844   0.00179  -0.0274   0.8457   0.2073
  -1.000   0.0334   0.00838   0.00169  -0.0271   0.8369   0.2105
  -0.750   0.0602   0.00832   0.00163  -0.0268   0.8284   0.2142
  -0.500   0.0862   0.00823   0.00160  -0.0265   0.8166   0.2199
  -0.250   0.1107   0.00800   0.00155  -0.0258   0.8010   0.2838
   0.000   0.1241   0.00679   0.00139  -0.0233   0.7836   0.5935
   0.250   0.1450   0.00645   0.00137  -0.0218   0.7671   0.6923
   0.500   0.1685   0.00633   0.00138  -0.0207   0.7506   0.7445
   0.750   0.1934   0.00631   0.00140  -0.0199   0.7316   0.7734
   1.000   0.2185   0.00636   0.00142  -0.0191   0.7079   0.7919
   1.250   0.2437   0.00643   0.00145  -0.0184   0.6820   0.8062
   1.500   0.2688   0.00653   0.00149  -0.0177   0.6561   0.8194
   1.750   0.2945   0.00662   0.00155  -0.0172   0.6335   0.8316
   2.000   0.3194   0.00676   0.00161  -0.0164   0.6031   0.8431
   2.250   0.3421   0.00704   0.00170  -0.0153   0.5492   0.8539
   2.500   0.3634   0.00745   0.00182  -0.0140   0.4726   0.8651
   2.750   0.3855   0.00787   0.00199  -0.0129   0.4029   0.8757
   3.000   0.4074   0.00838   0.00220  -0.0118   0.3249   0.8857
   3.250   0.4301   0.00886   0.00241  -0.0110   0.2557   0.8958
   3.500   0.4543   0.00924   0.00263  -0.0104   0.2093   0.9054
   3.750   0.4786   0.00964   0.00286  -0.0098   0.1676   0.9146
   4.000   0.5035   0.01002   0.00310  -0.0094   0.1311   0.9239
   4.250   0.5293   0.01036   0.00334  -0.0091   0.1035   0.9318
   4.500   0.5553   0.01070   0.00359  -0.0089   0.0833   0.9398
   4.750   0.5822   0.01101   0.00385  -0.0089   0.0682   0.9465
   5.000   0.6095   0.01134   0.00413  -0.0089   0.0564   0.9529
   5.250   0.6361   0.01163   0.00441  -0.0088   0.0494   0.9589
   5.500   0.6646   0.01197   0.00473  -0.0092   0.0442   0.9636
   5.750   0.6921   0.01228   0.00506  -0.0093   0.0414   0.9690
   6.000   0.7204   0.01259   0.00540  -0.0096   0.0391   0.9737
   6.250   0.7493   0.01294   0.00576  -0.0102   0.0366   0.9779
   6.500   0.7756   0.01337   0.00619  -0.0101   0.0340   0.9831
   6.750   0.8053   0.01380   0.00666  -0.0109   0.0325   0.9868
   7.000   0.8337   0.01417   0.00709  -0.0113   0.0314   0.9899
   7.250   0.8610   0.01457   0.00754  -0.0115   0.0302   0.9932
   7.500   0.8897   0.01500   0.00801  -0.0121   0.0290   0.9955
   7.750   0.9180   0.01546   0.00850  -0.0126   0.0277   0.9979
   8.000   0.9431   0.01602   0.00909  -0.0126   0.0263   1.0000
   8.250   0.9592   0.01662   0.00973  -0.0105   0.0253   1.0000
   8.500   0.9776   0.01704   0.01021  -0.0089   0.0248   1.0000
   8.750   0.9957   0.01750   0.01073  -0.0072   0.0242   1.0000
   9.000   1.0138   0.01799   0.01129  -0.0056   0.0236   1.0000
   9.250   1.0321   0.01850   0.01187  -0.0041   0.0228   1.0000
   9.500   1.0510   0.01898   0.01240  -0.0027   0.0221   1.0000
   9.750   1.0702   0.01944   0.01291  -0.0014   0.0213   1.0000
  10.000   1.0885   0.01999   0.01348  -0.0001   0.0206   1.0000
  10.250   1.1042   0.02079   0.01434   0.0016   0.0198   1.0000
  10.500   1.1215   0.02147   0.01510   0.0031   0.0192   1.0000
  10.750   1.1396   0.02204   0.01578   0.0044   0.0187   1.0000
  11.000   1.1568   0.02267   0.01650   0.0058   0.0181   1.0000
  11.250   1.1730   0.02328   0.01720   0.0074   0.0174   1.0000
  11.500   1.1882   0.02386   0.01784   0.0090   0.0168   1.0000
  11.750   1.2034   0.02441   0.01845   0.0107   0.0162   1.0000
  12.000   1.2172   0.02509   0.01919   0.0124   0.0157   1.0000
  12.250   1.2280   0.02603   0.02020   0.0144   0.0152   1.0000
  12.500   1.2378   0.02712   0.02140   0.0163   0.0148   1.0000
  12.750   1.2490   0.02811   0.02252   0.0180   0.0144   1.0000
  13.000   1.2591   0.02920   0.02374   0.0197   0.0140   1.0000
  13.250   1.2687   0.03031   0.02498   0.0213   0.0136   1.0000
  13.500   1.2780   0.03148   0.02626   0.0227   0.0131   1.0000
  13.750   1.2870   0.03267   0.02754   0.0240   0.0127   1.0000
  14.000   1.2957   0.03393   0.02890   0.0252   0.0123   1.0000
  14.250   1.3029   0.03537   0.03041   0.0262   0.0119   1.0000
  14.500   1.3064   0.03722   0.03237   0.0272   0.0115   1.0000
  14.750   1.3067   0.03948   0.03476   0.0280   0.0112   1.0000
  15.000   1.3079   0.04181   0.03726   0.0285   0.0109   1.0000
  15.250   1.3068   0.04450   0.04011   0.0288   0.0107   1.0000
  15.500   1.3037   0.04756   0.04333   0.0286   0.0104   1.0000
  15.750   1.2987   0.05107   0.04700   0.0279   0.0102   1.0000
  16.000   1.2910   0.05513   0.05122   0.0268   0.0100   1.0000
  16.250   1.2806   0.05985   0.05611   0.0249   0.0098   1.0000
  16.500   1.2670   0.06540   0.06183   0.0223   0.0097   1.0000
  16.750   1.2485   0.07221   0.06881   0.0187   0.0097   1.0000
  17.000   1.2241   0.08057   0.07737   0.0140   0.0096   1.0000
  17.250   1.1894   0.09146   0.08846   0.0078   0.0097   1.0000
  17.500   1.1386   0.10618   0.10341  -0.0005   0.0100   1.0000
  17.750   1.0576   0.12805   0.12550  -0.0121   0.0106   1.0000
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