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


Details Polar file
Airfoil: Cambered plate C=10% T=5% R=1.3 (cp-100-050-gn)
Reynolds number: 100,000
Max Cl/Cd: 30.37 at α=7°
Description: Mach=0 Ncrit=1
Source: Xfoil prediction
Download polar: xf-cp-100-050-gn-100000-n1.txt
Download as CSV file: xf-cp-100-050-gn-100000-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 =     0.100 e 6     Ncrit =   1.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.0670   0.11351   0.10668  -0.1044   0.8771   0.0223
  -8.750  -0.0608   0.11140   0.10458  -0.1047   0.8729   0.0227
  -8.500  -0.0524   0.10924   0.10242  -0.1055   0.8692   0.0230
  -8.250  -0.0427   0.10690   0.10007  -0.1066   0.8658   0.0232
  -7.750  -0.0276   0.10267   0.09585  -0.1077   0.8581   0.0235
  -7.500  -0.0215   0.10069   0.09388  -0.1078   0.8537   0.0237
  -7.250  -0.0132   0.09854   0.09173  -0.1084   0.8496   0.0239
  -7.000  -0.0035   0.09628   0.08946  -0.1095   0.8462   0.0245
  -6.750  -0.0014   0.09442   0.08762  -0.1089   0.8410   0.0253
  -6.500   0.0032   0.09273   0.08596  -0.1084   0.8360   0.0256
  -6.250   0.0103   0.09084   0.08408  -0.1086   0.8316   0.0258
  -6.000   0.0177   0.08890   0.08214  -0.1089   0.8276   0.0259
  -5.750   0.0163   0.08763   0.08091  -0.1070   0.8213   0.0261
  -5.500   0.0183   0.08609   0.07939  -0.1059   0.8159   0.0262
  -5.250   0.0225   0.08436   0.07767  -0.1055   0.8113   0.0264
  -5.000   0.0173   0.08330   0.07665  -0.1027   0.8046   0.0267
  -4.750   0.0190   0.08172   0.07510  -0.1017   0.7989   0.0269
  -4.500   0.0258   0.07967   0.07305  -0.1020   0.7942   0.0277
  -4.250   0.0262   0.07808   0.07149  -0.1008   0.7880   0.0283
  -4.000   0.0305   0.07644   0.06987  -0.1003   0.7824   0.0285
  -3.750   0.0401   0.07453   0.06795  -0.1008   0.7778   0.0287
  -3.500   0.0480   0.07274   0.06618  -0.1010   0.7727   0.0288
  -3.250   0.0542   0.07112   0.06458  -0.1006   0.7669   0.0290
  -3.000   0.0660   0.06919   0.06265  -0.1014   0.7622   0.0292
  -2.750   0.0822   0.06704   0.06047  -0.1031   0.7583   0.0294
  -2.500   0.0922   0.06535   0.05878  -0.1033   0.7526   0.0300
  -2.250   0.1068   0.06334   0.05677  -0.1045   0.7476   0.0309
  -2.000   0.1265   0.06102   0.05441  -0.1068   0.7435   0.0315
  -1.500   0.1655   0.05718   0.05052  -0.1101   0.7347   0.0318
  -1.250   0.1865   0.05532   0.04865  -0.1118   0.7303   0.0320
  -1.000   0.2116   0.05333   0.04662  -0.1142   0.7264   0.0324
  -0.750   0.2403   0.05124   0.04447  -0.1172   0.7232   0.0333
  -0.500   0.2663   0.04930   0.04248  -0.1196   0.7189   0.0344
  -0.250   0.2927   0.04746   0.04059  -0.1219   0.7145   0.0347
   0.000   0.3217   0.04565   0.03873  -0.1243   0.7106   0.0349
   0.250   0.3524   0.04393   0.03696  -0.1268   0.7072   0.0352
   0.500   0.3848   0.04222   0.03518  -0.1295   0.7043   0.0355
   0.750   0.4115   0.04089   0.03381  -0.1310   0.6997   0.0365
   1.000   0.4425   0.03933   0.03217  -0.1331   0.6955   0.0376
   1.250   0.4746   0.03779   0.03055  -0.1353   0.6918   0.0380
   1.500   0.5080   0.03627   0.02895  -0.1374   0.6885   0.0383
   1.750   0.5392   0.03501   0.02763  -0.1390   0.6852   0.0385
   2.000   0.5665   0.03404   0.02660  -0.1397   0.6778   0.0392
   2.250   0.6091   0.03205   0.02431  -0.1424   0.6504   0.0408
   2.500   0.6384   0.03115   0.02185  -0.1419   0.4358   0.0413
   2.750   0.6193   0.03399   0.02315  -0.1349   0.1004   0.0413
   3.000   0.6408   0.03371   0.02249  -0.1344   0.0441   0.0415
   3.250   0.6675   0.03297   0.02157  -0.1345   0.0403   0.0418
   3.750   0.7172   0.03194   0.02028  -0.1337   0.0356   0.0435
   4.000   0.7423   0.03135   0.01951  -0.1333   0.0344   0.0445
   4.250   0.7660   0.03092   0.01892  -0.1325   0.0338   0.0448
   4.500   0.7890   0.03057   0.01841  -0.1316   0.0333   0.0451
   4.750   0.8115   0.03029   0.01798  -0.1306   0.0326   0.0454
   5.000   0.8329   0.03017   0.01774  -0.1294   0.0317   0.0463
   5.250   0.8532   0.03027   0.01777  -0.1281   0.0310   0.0472
   5.500   0.8730   0.03036   0.01777  -0.1267   0.0300   0.0480
   5.750   0.8923   0.03051   0.01783  -0.1252   0.0292   0.0483
   6.000   0.9109   0.03074   0.01799  -0.1236   0.0288   0.0485
   6.250   0.9297   0.03104   0.01826  -0.1221   0.0283   0.0487
   6.500   0.9489   0.03145   0.01863  -0.1207   0.0281   0.0490
   6.750   0.9679   0.03193   0.01909  -0.1193   0.0278   0.0493
   7.000   0.9862   0.03247   0.01961  -0.1178   0.0276   0.0499
   7.250   1.0030   0.03311   0.02027  -0.1162   0.0274   0.0507
   7.500   1.0190   0.03380   0.02099  -0.1144   0.0272   0.0516
   7.750   1.0345   0.03452   0.02175  -0.1126   0.0271   0.0525
   8.000   1.0495   0.03531   0.02256  -0.1108   0.0269   0.0530
   8.250   1.0639   0.03615   0.02342  -0.1089   0.0268   0.0533
   8.500   1.0780   0.03704   0.02435  -0.1071   0.0266   0.0536
   8.750   1.0917   0.03799   0.02533  -0.1052   0.0265   0.0540
   9.000   1.1053   0.03898   0.02635  -0.1033   0.0263   0.0544
   9.250   1.1189   0.03999   0.02740  -0.1015   0.0261   0.0550
   9.500   1.1327   0.04101   0.02846  -0.0998   0.0259   0.0562
   9.750   1.1467   0.04205   0.02954  -0.0981   0.0256   0.0578
  10.000   1.1611   0.04308   0.03058  -0.0965   0.0252   0.0595
  10.250   1.1759   0.04411   0.03164  -0.0949   0.0249   0.0607
  10.500   1.1909   0.04517   0.03273  -0.0934   0.0246   0.0627
  10.750   1.2067   0.04625   0.03389  -0.0919   0.0242   0.0656
  11.000   1.2231   0.04734   0.03505  -0.0904   0.0240   0.0696
  11.250   1.2404   0.04842   0.03621  -0.0891   0.0238   0.0767
  11.500   1.2587   0.04861   0.03756  -0.0884   0.0236   1.0000
  11.750   1.2767   0.04974   0.03873  -0.0871   0.0234   1.0000
  12.000   1.2953   0.05090   0.03992  -0.0858   0.0233   1.0000
  12.250   1.3140   0.05211   0.04118  -0.0846   0.0231   1.0000
  12.500   1.3329   0.05338   0.04253  -0.0834   0.0229   1.0000
  12.750   1.3511   0.05472   0.04397  -0.0823   0.0226   1.0000
  13.000   1.3683   0.05616   0.04551  -0.0810   0.0223   1.0000
  13.250   1.3837   0.05769   0.04716  -0.0797   0.0219   1.0000
  13.500   1.3971   0.05932   0.04892  -0.0784   0.0216   1.0000
  13.750   1.4084   0.06102   0.05075  -0.0769   0.0213   1.0000
  14.000   1.4186   0.06286   0.05273  -0.0754   0.0211   1.0000
  14.250   1.4282   0.06493   0.05496  -0.0739   0.0209   1.0000
  14.500   1.4370   0.06742   0.05769  -0.0724   0.0207   1.0000
  14.750   1.4424   0.07016   0.06069  -0.0708   0.0205   1.0000
  15.000   1.4443   0.07317   0.06397  -0.0692   0.0204   1.0000
  15.250   1.4426   0.07648   0.06755  -0.0676   0.0202   1.0000
  15.500   1.4376   0.08011   0.07146  -0.0661   0.0201   1.0000
  15.750   1.4297   0.08403   0.07566  -0.0649   0.0200   1.0000
  16.000   1.4184   0.08842   0.08034  -0.0639   0.0198   1.0000
  16.250   1.4040   0.09328   0.08549  -0.0634   0.0197   1.0000
  16.500   1.3866   0.09873   0.09123  -0.0634   0.0195   1.0000
  16.750   1.3658   0.10487   0.09767  -0.0643   0.0193   1.0000
  17.000   1.3423   0.11179   0.10488  -0.0661   0.0192   1.0000
  17.250   1.3142   0.12009   0.11347  -0.0695   0.0190   1.0000
  17.500   1.2799   0.13062   0.12430  -0.0752   0.0189   1.0000
  17.750   1.2279   0.14808   0.14210  -0.0869   0.0187   1.0000
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