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Cambered plate C=10% T=5% R=1.3 (cp-100-050-gn) Xfoil prediction polar at RE=200,000 Ncrit=1


Details Polar file
Airfoil: Cambered plate C=10% T=5% R=1.3 (cp-100-050-gn)
Reynolds number: 200,000
Max Cl/Cd: 38.3 at α=6.25°
Description: Mach=0 Ncrit=1
Source: Xfoil prediction
Download polar: xf-cp-100-050-gn-200000-n1.txt
Download as CSV file: xf-cp-100-050-gn-200000-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 =     0.200 e 6     Ncrit =   1.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.0223   0.11159   0.10643  -0.1252   0.8939   0.0185
  -9.750  -0.0122   0.10915   0.10398  -0.1266   0.8904   0.0187
  -9.500  -0.0007   0.10663   0.10144  -0.1284   0.8869   0.0189
  -9.250   0.0117   0.10401   0.09880  -0.1304   0.8835   0.0191
  -9.000   0.0248   0.10139   0.09616  -0.1326   0.8806   0.0193
  -8.750   0.0351   0.09908   0.09384  -0.1339   0.8770   0.0195
  -8.500   0.0450   0.09675   0.09151  -0.1351   0.8727   0.0200
  -8.250   0.0572   0.09453   0.08928  -0.1367   0.8685   0.0205
  -8.000   0.0700   0.09219   0.08692  -0.1385   0.8648   0.0209
  -7.750   0.0812   0.08992   0.08464  -0.1399   0.8611   0.0213
  -7.500   0.0905   0.08786   0.08258  -0.1407   0.8564   0.0215
  -7.250   0.1010   0.08572   0.08043  -0.1418   0.8515   0.0217
  -7.000   0.1126   0.08360   0.07828  -0.1431   0.8473   0.0218
  -6.750   0.1213   0.08148   0.07616  -0.1438   0.8430   0.0223
  -6.500   0.1291   0.07958   0.07427  -0.1441   0.8376   0.0226
  -6.250   0.1387   0.07778   0.07247  -0.1447   0.8325   0.0231
  -6.000   0.1485   0.07591   0.07058  -0.1453   0.8279   0.0235
  -5.750   0.1535   0.07430   0.06900  -0.1448   0.8225   0.0239
  -5.500   0.1586   0.07266   0.06736  -0.1443   0.8167   0.0241
  -5.250   0.1638   0.07099   0.06569  -0.1439   0.8114   0.0244
  -5.000   0.1678   0.06944   0.06415  -0.1432   0.8063   0.0246
  -4.750   0.1750   0.06777   0.06248  -0.1432   0.8006   0.0247
  -4.500   0.1840   0.06584   0.06054  -0.1439   0.7954   0.0252
  -4.250   0.1941   0.06410   0.05880  -0.1444   0.7907   0.0258
  -4.000   0.2038   0.06247   0.05718  -0.1446   0.7855   0.0262
  -3.750   0.2157   0.06069   0.05539  -0.1454   0.7802   0.0266
  -3.500   0.2304   0.05879   0.05347  -0.1467   0.7757   0.0268
  -3.250   0.2426   0.05704   0.05172  -0.1473   0.7710   0.0271
  -3.000   0.2569   0.05522   0.04989  -0.1482   0.7658   0.0273
  -2.750   0.2740   0.05330   0.04794  -0.1496   0.7609   0.0276
  -2.500   0.2927   0.05118   0.04579  -0.1515   0.7566   0.0283
  -2.250   0.3102   0.04950   0.04410  -0.1525   0.7520   0.0289
  -2.000   0.3300   0.04776   0.04233  -0.1538   0.7471   0.0294
  -1.750   0.3521   0.04592   0.04046  -0.1555   0.7427   0.0297
  -1.500   0.3751   0.04410   0.03860  -0.1573   0.7386   0.0300
  -1.250   0.3964   0.04237   0.03685  -0.1584   0.7341   0.0303
  -1.000   0.4204   0.04057   0.03499  -0.1600   0.7293   0.0308
  -0.750   0.4478   0.03859   0.03295  -0.1623   0.7250   0.0317
  -0.500   0.4743   0.03707   0.03139  -0.1638   0.7211   0.0323
  -0.250   0.4995   0.03553   0.02981  -0.1650   0.7166   0.0327
   0.000   0.5272   0.03396   0.02816  -0.1665   0.7086   0.0330
   0.250   0.5559   0.03244   0.02642  -0.1680   0.6811   0.0334
   0.500   0.5740   0.03140   0.02499  -0.1668   0.6248   0.0338
   0.750   0.5616   0.03160   0.02454  -0.1592   0.5171   0.0341
   1.000   0.5364   0.03283   0.02497  -0.1496   0.3538   0.0342
   1.250   0.5194   0.03410   0.02535  -0.1424   0.1080   0.0347
   1.500   0.5369   0.03360   0.02458  -0.1414   0.0374   0.0353
   1.750   0.5630   0.03260   0.02348  -0.1418   0.0348   0.0358
   2.000   0.5892   0.03162   0.02239  -0.1422   0.0335   0.0361
   2.250   0.6157   0.03066   0.02132  -0.1425   0.0325   0.0365
   2.500   0.6425   0.02974   0.02027  -0.1428   0.0311   0.0369
   2.750   0.6714   0.02851   0.01883  -0.1433   0.0298   0.0383
   3.250   0.7205   0.02720   0.01727  -0.1425   0.0280   0.0392
   3.500   0.7445   0.02655   0.01647  -0.1418   0.0274   0.0396
   3.750   0.7683   0.02590   0.01565  -0.1410   0.0268   0.0401
   4.000   0.7949   0.02457   0.01396  -0.1405   0.0266   0.0420
   4.250   0.8157   0.02440   0.01367  -0.1391   0.0263   0.0424
   4.500   0.8362   0.02423   0.01337  -0.1377   0.0261   0.0427
   4.750   0.8561   0.02415   0.01318  -0.1362   0.0258   0.0430
   5.000   0.8755   0.02415   0.01308  -0.1346   0.0256   0.0434
   5.250   0.8946   0.02422   0.01306  -0.1329   0.0255   0.0439
   5.500   0.9133   0.02433   0.01308  -0.1312   0.0252   0.0449
   5.750   0.9314   0.02451   0.01319  -0.1294   0.0251   0.0457
   6.000   0.9489   0.02483   0.01350  -0.1276   0.0250   0.0459
   6.250   0.9660   0.02522   0.01390  -0.1257   0.0248   0.0460
   6.500   0.9827   0.02566   0.01434  -0.1238   0.0247   0.0462
   6.750   0.9990   0.02614   0.01485  -0.1219   0.0246   0.0463
   7.000   1.0151   0.02667   0.01540  -0.1200   0.0245   0.0465
   7.250   1.0312   0.02723   0.01599  -0.1181   0.0244   0.0468
   7.500   1.0466   0.02784   0.01665  -0.1162   0.0242   0.0470
   7.750   1.0616   0.02849   0.01733  -0.1142   0.0240   0.0472
   8.000   1.0762   0.02917   0.01805  -0.1122   0.0238   0.0476
   8.250   1.0908   0.02991   0.01882  -0.1103   0.0235   0.0483
   8.500   1.1055   0.03067   0.01963  -0.1084   0.0232   0.0492
   8.750   1.1203   0.03148   0.02047  -0.1066   0.0229   0.0498
   9.000   1.1350   0.03235   0.02138  -0.1048   0.0227   0.0505
   9.250   1.1495   0.03324   0.02231  -0.1031   0.0225   0.0507
   9.500   1.1640   0.03416   0.02326  -0.1013   0.0224   0.0510
   9.750   1.1783   0.03510   0.02424  -0.0996   0.0223   0.0513
  10.000   1.1924   0.03608   0.02525  -0.0978   0.0222   0.0517
  10.250   1.2067   0.03705   0.02626  -0.0962   0.0220   0.0521
  10.500   1.2210   0.03806   0.02731  -0.0945   0.0219   0.0527
  10.750   1.2355   0.03907   0.02836  -0.0929   0.0218   0.0536
  11.000   1.2497   0.04013   0.02945  -0.0913   0.0217   0.0553
  11.250   1.2645   0.04116   0.03053  -0.0898   0.0216   0.0580
  11.500   1.2792   0.04221   0.03163  -0.0883   0.0214   0.0603
  11.750   1.2941   0.04326   0.03273  -0.0868   0.0213   0.0651
  12.000   1.3089   0.04432   0.03386  -0.0854   0.0211   0.0753
  12.750   1.3648   0.04710   0.03788  -0.0834   0.0202   1.0000
  13.000   1.3806   0.04827   0.03912  -0.0820   0.0200   1.0000
  13.250   1.3966   0.04948   0.04041  -0.0806   0.0198   1.0000
  13.500   1.4126   0.05074   0.04177  -0.0792   0.0196   1.0000
  13.750   1.4286   0.05207   0.04320  -0.0779   0.0194   1.0000
  14.000   1.4439   0.05348   0.04473  -0.0766   0.0192   1.0000
  14.250   1.4584   0.05501   0.04639  -0.0753   0.0190   1.0000
  14.500   1.4718   0.05665   0.04818  -0.0739   0.0188   1.0000
  14.750   1.4838   0.05844   0.05011  -0.0725   0.0186   1.0000
  15.000   1.4942   0.06038   0.05221  -0.0710   0.0184   1.0000
  15.250   1.5025   0.06247   0.05447  -0.0696   0.0181   1.0000
  15.500   1.5088   0.06472   0.05690  -0.0681   0.0179   1.0000
  15.750   1.5132   0.06707   0.05941  -0.0666   0.0177   1.0000
  16.000   1.5156   0.07012   0.06271  -0.0651   0.0174   1.0000
  16.250   1.5135   0.07389   0.06677  -0.0636   0.0171   1.0000
  16.500   1.5081   0.07770   0.07084  -0.0622   0.0169   1.0000
  16.750   1.4987   0.08202   0.07543  -0.0611   0.0167   1.0000
  17.000   1.4865   0.08669   0.08037  -0.0603   0.0166   1.0000
  17.250   1.4706   0.09195   0.08590  -0.0600   0.0164   1.0000
  17.500   1.4521   0.09769   0.09191  -0.0602   0.0163   1.0000
  17.750   1.4297   0.10423   0.09872  -0.0613   0.0162   1.0000
  18.000   1.4036   0.11177   0.10653  -0.0634   0.0161   1.0000
  18.250   1.3714   0.12096   0.11601  -0.0673   0.0160   1.0000
  18.500   1.3272   0.13373   0.12911  -0.0745   0.0159   1.0000
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