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Cambered plate C=10% T=5% R=1.3 (cp-100-050-gn) Xfoil prediction polar at RE=500,000 Ncrit=1


Details Polar file
Airfoil: Cambered plate C=10% T=5% R=1.3 (cp-100-050-gn)
Reynolds number: 500,000
Max Cl/Cd: 50.76 at α=6.25°
Description: Mach=0 Ncrit=1
Source: Xfoil prediction
Download polar: xf-cp-100-050-gn-500000-n1.txt
Download as CSV file: xf-cp-100-050-gn-500000-n1.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: Cambered plate C=10% T=5% R=1.3                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   1.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000   0.0624   0.09953   0.09581  -0.1545   0.8822   0.0169
  -9.750   0.0730   0.09704   0.09329  -0.1561   0.8777   0.0172
  -9.500   0.0841   0.09497   0.09120  -0.1573   0.8731   0.0173
  -9.250   0.0949   0.09279   0.08900  -0.1586   0.8679   0.0176
  -9.000   0.1064   0.09073   0.08691  -0.1599   0.8630   0.0178
  -8.750   0.1164   0.08868   0.08485  -0.1608   0.8580   0.0180
  -8.500   0.1263   0.08664   0.08279  -0.1617   0.8530   0.0182
  -8.250   0.1362   0.08461   0.08073  -0.1626   0.8471   0.0185
  -8.000   0.1454   0.08259   0.07869  -0.1633   0.8423   0.0188
  -7.750   0.1530   0.08038   0.07646  -0.1640   0.8370   0.0195
  -7.500   0.1616   0.07842   0.07449  -0.1645   0.8315   0.0199
  -7.250   0.1713   0.07674   0.07279  -0.1649   0.8263   0.0200
  -7.000   0.1797   0.07492   0.07096  -0.1652   0.8206   0.0201
  -6.750   0.1883   0.07323   0.06925  -0.1654   0.8147   0.0206
  -6.500   0.1960   0.07152   0.06753  -0.1655   0.8092   0.0208
  -6.250   0.2031   0.06980   0.06581  -0.1654   0.8039   0.0210
  -6.000   0.2095   0.06815   0.06415  -0.1651   0.7982   0.0212
  -5.750   0.2134   0.06645   0.06244  -0.1645   0.7927   0.0219
  -5.500   0.2140   0.06467   0.06066  -0.1635   0.7862   0.0225
  -5.250   0.2213   0.06327   0.05926  -0.1633   0.7810   0.0227
  -5.000   0.2298   0.06167   0.05764  -0.1635   0.7756   0.0229
  -4.750   0.2399   0.06002   0.05599  -0.1639   0.7701   0.0230
  -4.500   0.2508   0.05836   0.05433  -0.1645   0.7647   0.0234
  -4.250   0.2623   0.05660   0.05255  -0.1653   0.7596   0.0237
  -4.000   0.2751   0.05482   0.05076  -0.1662   0.7544   0.0242
  -3.750   0.2887   0.05282   0.04874  -0.1675   0.7492   0.0248
  -3.500   0.3036   0.05080   0.04669  -0.1690   0.7441   0.0253
  -3.250   0.3201   0.04905   0.04492  -0.1702   0.7394   0.0255
  -3.000   0.3383   0.04737   0.04322  -0.1715   0.7345   0.0258
  -2.750   0.3573   0.04565   0.04148  -0.1729   0.7296   0.0261
  -2.500   0.3772   0.04391   0.03971  -0.1743   0.7250   0.0264
  -2.250   0.3970   0.04218   0.03793  -0.1756   0.7172   0.0269
  -2.000   0.4173   0.04021   0.03589  -0.1770   0.7074   0.0278
  -1.750   0.4328   0.03859   0.03412  -0.1769   0.6864   0.0282
  -1.500   0.4483   0.03725   0.03266  -0.1764   0.6645   0.0285
  -1.250   0.4564   0.03633   0.03156  -0.1739   0.6306   0.0287
  -1.000   0.4535   0.03580   0.03079  -0.1687   0.5824   0.0289
  -0.750   0.4174   0.03697   0.03127  -0.1564   0.4274   0.0288
  -0.500   0.4030   0.03760   0.03124  -0.1493   0.2535   0.0290
  -0.250   0.4014   0.03771   0.03079  -0.1450   0.0384   0.0292
   0.000   0.4273   0.03619   0.02919  -0.1462   0.0319   0.0297
   0.250   0.4547   0.03455   0.02744  -0.1477   0.0288   0.0306
   0.500   0.4830   0.03285   0.02564  -0.1492   0.0273   0.0312
   1.000   0.5364   0.03027   0.02288  -0.1508   0.0259   0.0319
   1.250   0.5629   0.02910   0.02161  -0.1514   0.0254   0.0324
   1.500   0.5898   0.02791   0.02032  -0.1519   0.0251   0.0331
   1.750   0.6188   0.02640   0.01865  -0.1527   0.0248   0.0342
   2.000   0.6471   0.02499   0.01707  -0.1533   0.0246   0.0348
   2.250   0.6730   0.02408   0.01604  -0.1532   0.0244   0.0352
   2.500   0.6986   0.02319   0.01501  -0.1529   0.0242   0.0356
   2.750   0.7247   0.02212   0.01376  -0.1526   0.0239   0.0365
   3.000   0.7534   0.01998   0.01119  -0.1526   0.0238   0.0381
   3.250   0.7769   0.01896   0.00988  -0.1517   0.0236   0.0388
   3.500   0.7987   0.01844   0.00916  -0.1504   0.0236   0.0396
   3.750   0.8201   0.01796   0.00847  -0.1490   0.0232   0.0410
   4.000   0.8406   0.01785   0.00825  -0.1474   0.0231   0.0416
   4.250   0.8605   0.01792   0.00826  -0.1458   0.0230   0.0418
   4.500   0.8802   0.01805   0.00835  -0.1441   0.0229   0.0419
   4.750   0.8996   0.01825   0.00854  -0.1424   0.0227   0.0421
   5.000   0.9190   0.01848   0.00876  -0.1407   0.0226   0.0423
   5.250   0.9379   0.01873   0.00901  -0.1389   0.0225   0.0425
   5.500   0.9565   0.01900   0.00928  -0.1371   0.0224   0.0426
   5.750   0.9750   0.01930   0.00957  -0.1353   0.0222   0.0431
   6.000   0.9934   0.01960   0.00988  -0.1335   0.0221   0.0434
   6.250   1.0116   0.01993   0.01021  -0.1317   0.0219   0.0438
   6.500   1.0293   0.02029   0.01057  -0.1298   0.0217   0.0440
   6.750   1.0469   0.02066   0.01095  -0.1279   0.0214   0.0442
   7.000   1.0643   0.02106   0.01136  -0.1260   0.0214   0.0443
   7.250   1.0814   0.02149   0.01181  -0.1241   0.0213   0.0446
   7.500   1.0981   0.02195   0.01229  -0.1222   0.0212   0.0447
   7.750   1.1147   0.02244   0.01279  -0.1202   0.0211   0.0448
   8.000   1.1310   0.02295   0.01332  -0.1183   0.0210   0.0452
   8.250   1.1471   0.02349   0.01388  -0.1163   0.0210   0.0453
   8.500   1.1627   0.02407   0.01448  -0.1144   0.0209   0.0456
   8.750   1.1784   0.02467   0.01511  -0.1124   0.0208   0.0456
   9.000   1.1937   0.02530   0.01577  -0.1104   0.0208   0.0460
   9.250   1.2085   0.02597   0.01648  -0.1084   0.0207   0.0461
   9.500   1.2232   0.02666   0.01721  -0.1065   0.0207   0.0464
   9.750   1.2379   0.02737   0.01796  -0.1045   0.0207   0.0467
  10.000   1.2521   0.02814   0.01878  -0.1025   0.0205   0.0477
  10.250   1.2662   0.02892   0.01960  -0.1006   0.0205   0.0482
  10.500   1.2800   0.02974   0.02047  -0.0987   0.0204   0.0487
  10.750   1.2938   0.03058   0.02135  -0.0968   0.0201   0.0491
  11.000   1.3069   0.03148   0.02230  -0.0948   0.0200   0.0494
  11.250   1.3204   0.03239   0.02326  -0.0930   0.0198   0.0500
  11.500   1.3336   0.03333   0.02426  -0.0911   0.0195   0.0504
  11.750   1.3464   0.03431   0.02529  -0.0893   0.0194   0.0509
  12.000   1.3592   0.03532   0.02635  -0.0875   0.0193   0.0516
  12.250   1.3722   0.03633   0.02742  -0.0858   0.0191   0.0531
  12.500   1.3844   0.03743   0.02859  -0.0840   0.0191   0.0569
  12.750   1.3971   0.03847   0.02979  -0.0823   0.0188   0.1454
  13.500   1.4614   0.04174   0.03424  -0.0834   0.0185   1.0000
  13.750   1.4730   0.04295   0.03550  -0.0818   0.0183   1.0000
  14.000   1.4849   0.04416   0.03676  -0.0801   0.0182   1.0000
  14.250   1.4963   0.04542   0.03807  -0.0785   0.0181   1.0000
  14.500   1.5075   0.04671   0.03941  -0.0769   0.0180   1.0000
  14.750   1.5186   0.04802   0.04077  -0.0754   0.0179   1.0000
  15.000   1.5298   0.04933   0.04214  -0.0739   0.0179   1.0000
  15.250   1.5404   0.05071   0.04358  -0.0724   0.0177   1.0000
  15.500   1.5509   0.05212   0.04505  -0.0709   0.0176   1.0000
  15.750   1.5613   0.05356   0.04654  -0.0695   0.0176   1.0000
  16.000   1.5709   0.05512   0.04819  -0.0681   0.0174   1.0000
  16.250   1.5801   0.05675   0.04992  -0.0666   0.0172   1.0000
  16.500   1.5893   0.05837   0.05163  -0.0652   0.0170   1.0000
  16.750   1.5982   0.06009   0.05345  -0.0639   0.0169   1.0000
  17.000   1.6064   0.06190   0.05536  -0.0626   0.0167   1.0000
  17.250   1.6138   0.06382   0.05739  -0.0613   0.0166   1.0000
  17.500   1.6207   0.06579   0.05948  -0.0601   0.0165   1.0000
  17.750   1.6268   0.06791   0.06171  -0.0589   0.0164   1.0000
  18.000   1.6316   0.07020   0.06413  -0.0579   0.0162   1.0000
  18.250   1.6358   0.07260   0.06667  -0.0569   0.0161   1.0000
  18.500   1.6386   0.07519   0.06938  -0.0560   0.0160   1.0000
  18.750   1.6402   0.07798   0.07232  -0.0552   0.0158   1.0000
  19.000   1.6400   0.08103   0.07552  -0.0545   0.0157   1.0000
  19.250   1.6385   0.08431   0.07896  -0.0540   0.0156   1.0000
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