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MRC-16 (mrc-16-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: MRC-16 (mrc-16-il)
Reynolds number: 200,000
Max Cl/Cd: 71.07 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-mrc-16-il-200000-n5.txt
Download as CSV file: xf-mrc-16-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MRC-16                                          
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.3940   0.10114   0.09743  -0.0487   1.0000   0.0196
 -11.000  -0.4025   0.09536   0.09171  -0.0511   1.0000   0.0195
 -10.500  -0.6196   0.04916   0.04502  -0.0757   0.9939   0.0176
 -10.250  -0.6222   0.04456   0.04007  -0.0782   0.9839   0.0177
 -10.000  -0.6152   0.04119   0.03642  -0.0794   0.9756   0.0179
  -9.750  -0.6004   0.03815   0.03308  -0.0810   0.9704   0.0182
  -9.500  -0.5888   0.03560   0.03023  -0.0808   0.9618   0.0185
  -9.250  -0.5699   0.03301   0.02729  -0.0816   0.9568   0.0190
  -9.000  -0.5548   0.03083   0.02478  -0.0809   0.9487   0.0195
  -8.750  -0.5336   0.02874   0.02231  -0.0810   0.9432   0.0204
  -8.500  -0.5139   0.02686   0.01995  -0.0804   0.9366   0.0213
  -8.250  -0.4913   0.02550   0.01848  -0.0802   0.9302   0.0220
  -8.000  -0.4649   0.02439   0.01725  -0.0806   0.9258   0.0227
  -7.750  -0.4437   0.02338   0.01610  -0.0797   0.9180   0.0234
  -7.500  -0.4186   0.02229   0.01481  -0.0795   0.9124   0.0243
  -7.250  -0.3945   0.02127   0.01361  -0.0790   0.9062   0.0254
  -7.000  -0.3709   0.02039   0.01259  -0.0784   0.8993   0.0266
  -6.750  -0.3448   0.01969   0.01187  -0.0784   0.8943   0.0280
  -6.500  -0.3223   0.01908   0.01119  -0.0776   0.8863   0.0296
  -6.250  -0.2971   0.01836   0.01034  -0.0771   0.8803   0.0311
  -6.000  -0.2740   0.01766   0.00958  -0.0763   0.8731   0.0327
  -5.750  -0.2497   0.01713   0.00902  -0.0758   0.8663   0.0349
  -5.500  -0.2246   0.01666   0.00846  -0.0753   0.8600   0.0378
  -5.250  -0.2012   0.01611   0.00788  -0.0746   0.8523   0.0406
  -5.000  -0.1755   0.01566   0.00737  -0.0742   0.8464   0.0443
  -4.750  -0.1519   0.01525   0.00692  -0.0734   0.8382   0.0490
  -4.500  -0.1259   0.01485   0.00646  -0.0731   0.8321   0.0551
  -4.250  -0.1019   0.01447   0.00610  -0.0724   0.8239   0.0629
  -4.000  -0.0762   0.01410   0.00570  -0.0720   0.8174   0.0743
  -3.750  -0.0517   0.01376   0.00539  -0.0715   0.8094   0.0909
  -3.500  -0.0264   0.01337   0.00507  -0.0710   0.8024   0.1175
  -3.250  -0.0025   0.01296   0.00482  -0.0705   0.7945   0.1611
  -3.000   0.0213   0.01246   0.00456  -0.0699   0.7872   0.2311
  -2.750   0.0437   0.01195   0.00437  -0.0691   0.7792   0.3200
  -2.500   0.0661   0.01146   0.00420  -0.0682   0.7717   0.4168
  -2.250   0.0877   0.01104   0.00411  -0.0670   0.7636   0.5100
  -2.000   0.1102   0.01070   0.00404  -0.0657   0.7560   0.5965
  -1.750   0.1332   0.01048   0.00404  -0.0645   0.7479   0.6696
  -1.500   0.1578   0.01035   0.00403  -0.0634   0.7402   0.7308
  -1.250   0.1828   0.01029   0.00407  -0.0623   0.7319   0.7814
  -1.000   0.2095   0.01029   0.00409  -0.0615   0.7242   0.8221
  -0.750   0.2368   0.01034   0.00414  -0.0610   0.7156   0.8522
  -0.500   0.2652   0.01039   0.00412  -0.0607   0.7079   0.8757
  -0.250   0.2947   0.01047   0.00416  -0.0608   0.6988   0.8941
   0.000   0.3255   0.01055   0.00415  -0.0612   0.6908   0.9098
   0.250   0.3559   0.01063   0.00417  -0.0616   0.6816   0.9239
   0.500   0.3899   0.01071   0.00417  -0.0627   0.6729   0.9348
   0.750   0.4240   0.01080   0.00417  -0.0640   0.6637   0.9445
   1.000   0.4558   0.01088   0.00420  -0.0648   0.6544   0.9551
   1.250   0.4934   0.01097   0.00419  -0.0669   0.6454   0.9615
   1.500   0.5271   0.01106   0.00423  -0.0682   0.6352   0.9700
   1.750   0.5659   0.01114   0.00424  -0.0707   0.6254   0.9752
   2.000   0.6005   0.01123   0.00426  -0.0723   0.6155   0.9824
   2.250   0.6384   0.01130   0.00430  -0.0746   0.6047   0.9873
   2.500   0.6740   0.01140   0.00434  -0.0765   0.5943   0.9931
   3.000   0.7384   0.01159   0.00445  -0.0790   0.5725   1.0000
   3.250   0.7593   0.01171   0.00454  -0.0778   0.5623   1.0000
   3.500   0.7799   0.01185   0.00462  -0.0765   0.5522   1.0000
   3.750   0.8004   0.01199   0.00473  -0.0752   0.5412   1.0000
   4.000   0.8208   0.01214   0.00487  -0.0739   0.5307   1.0000
   4.250   0.8410   0.01231   0.00500  -0.0726   0.5203   1.0000
   4.500   0.8612   0.01249   0.00515  -0.0712   0.5093   1.0000
   4.750   0.8813   0.01267   0.00532  -0.0698   0.4982   1.0000
   5.000   0.9013   0.01287   0.00550  -0.0684   0.4875   1.0000
   5.250   0.9209   0.01309   0.00569  -0.0669   0.4762   1.0000
   5.500   0.9407   0.01330   0.00590  -0.0655   0.4646   1.0000
   5.750   0.9604   0.01354   0.00613  -0.0641   0.4530   1.0000
   6.000   0.9800   0.01379   0.00637  -0.0626   0.4413   1.0000
   6.250   0.9993   0.01407   0.00661  -0.0612   0.4293   1.0000
   6.500   1.0190   0.01434   0.00689  -0.0598   0.4165   1.0000
   6.750   1.0385   0.01464   0.00719  -0.0584   0.4039   1.0000
   7.000   1.0577   0.01495   0.00750  -0.0570   0.3910   1.0000
   7.250   1.0764   0.01529   0.00783  -0.0555   0.3778   1.0000
   7.500   1.0946   0.01566   0.00820  -0.0540   0.3643   1.0000
   7.750   1.1122   0.01605   0.00858  -0.0524   0.3505   1.0000
   8.000   1.1291   0.01647   0.00899  -0.0507   0.3364   1.0000
   8.250   1.1452   0.01692   0.00942  -0.0489   0.3220   1.0000
   8.500   1.1595   0.01740   0.00989  -0.0468   0.3075   1.0000
   9.000   1.1861   0.01849   0.01096  -0.0426   0.2777   1.0000
   9.250   1.1989   0.01912   0.01157  -0.0405   0.2624   1.0000
   9.500   1.2111   0.01982   0.01226  -0.0385   0.2468   1.0000
   9.750   1.2227   0.02058   0.01302  -0.0365   0.2309   1.0000
  10.000   1.2336   0.02143   0.01384  -0.0346   0.2151   1.0000
  10.250   1.2437   0.02235   0.01475  -0.0326   0.1993   1.0000
  10.500   1.2532   0.02337   0.01574  -0.0308   0.1836   1.0000
  10.750   1.2618   0.02448   0.01683  -0.0289   0.1683   1.0000
  11.000   1.2696   0.02569   0.01803  -0.0271   0.1534   1.0000
  11.250   1.2767   0.02700   0.01932  -0.0254   0.1391   1.0000
  11.500   1.2830   0.02843   0.02073  -0.0238   0.1254   1.0000
  11.750   1.2887   0.02995   0.02224  -0.0222   0.1126   1.0000
  12.000   1.2936   0.03159   0.02387  -0.0207   0.1007   1.0000
  12.250   1.2979   0.03334   0.02563  -0.0194   0.0899   1.0000
  12.500   1.3011   0.03524   0.02754  -0.0181   0.0801   1.0000
  12.750   1.3033   0.03729   0.02959  -0.0169   0.0713   1.0000
  13.000   1.3056   0.03939   0.03173  -0.0158   0.0635   1.0000
  13.250   1.3074   0.04159   0.03397  -0.0149   0.0568   1.0000
  13.500   1.3071   0.04407   0.03649  -0.0141   0.0512   1.0000
  13.750   1.3083   0.04650   0.03899  -0.0134   0.0462   1.0000
  14.000   1.3069   0.04926   0.04181  -0.0129   0.0422   1.0000
  14.250   1.3069   0.05198   0.04462  -0.0125   0.0386   1.0000
  14.500   1.3035   0.05518   0.04787  -0.0123   0.0357   1.0000
  14.750   1.3027   0.05815   0.05096  -0.0122   0.0332   1.0000
  15.000   1.3000   0.06143   0.05434  -0.0123   0.0310   1.0000
  15.250   1.2946   0.06515   0.05814  -0.0126   0.0294   1.0000
  15.500   1.2911   0.06872   0.06182  -0.0130   0.0278   1.0000
  15.750   1.2874   0.07239   0.06562  -0.0135   0.0263   1.0000
  16.000   1.2820   0.07636   0.06969  -0.0142   0.0250   1.0000
  16.250   1.2746   0.08073   0.07414  -0.0152   0.0240   1.0000
  16.500   1.2675   0.08511   0.07863  -0.0162   0.0231   1.0000
  16.750   1.2623   0.08929   0.08295  -0.0172   0.0222   1.0000
  17.000   1.2561   0.09368   0.08746  -0.0184   0.0214   1.0000
  17.250   1.2495   0.09823   0.09212  -0.0198   0.0207   1.0000
  17.500   1.2422   0.10293   0.09695  -0.0213   0.0201   1.0000
  17.750   1.2340   0.10782   0.10193  -0.0231   0.0196   1.0000
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