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Cambered plate C=12% T=5% R=1.1 (cp-120-050-gn) Xfoil prediction polar at RE=100,000 Ncrit=1


Details Polar file
Airfoil: Cambered plate C=12% T=5% R=1.1 (cp-120-050-gn)
Reynolds number: 100,000
Max Cl/Cd: 27 at α=3.75°
Description: Mach=0 Ncrit=1
Source: Xfoil prediction
Download polar: xf-cp-120-050-gn-100000-n1.txt
Download as CSV file: xf-cp-120-050-gn-100000-n1.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: Cambered plate C=12% T=5% R=1.1                 
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -10.000   0.0051   0.12001   0.11321  -0.1228   0.8491   0.0175
  -9.750   0.0098   0.11818   0.11138  -0.1225   0.8450   0.0176
  -9.500   0.0164   0.11614   0.10934  -0.1229   0.8417   0.0178
  -9.250   0.0244   0.11399   0.10718  -0.1235   0.8389   0.0178
  -9.000   0.0336   0.11176   0.10492  -0.1245   0.8362   0.0180
  -8.750   0.0342   0.11034   0.10353  -0.1231   0.8311   0.0182
  -8.500   0.0384   0.10860   0.10180  -0.1227   0.8269   0.0186
  -8.250   0.0445   0.10667   0.09986  -0.1228   0.8236   0.0190
  -8.000   0.0518   0.10448   0.09766  -0.1233   0.8206   0.0197
  -7.750   0.0530   0.10315   0.09636  -0.1219   0.8156   0.0200
  -7.500   0.0549   0.10168   0.09492  -0.1208   0.8109   0.0201
  -7.250   0.0593   0.10000   0.09324  -0.1203   0.8071   0.0202
  -7.000   0.0657   0.09816   0.09139  -0.1203   0.8038   0.0203
  -6.750   0.0637   0.09706   0.09032  -0.1182   0.7983   0.0204
  -6.500   0.0635   0.09579   0.08908  -0.1165   0.7932   0.0205
  -6.250   0.0659   0.09431   0.08762  -0.1155   0.7892   0.0207
  -6.000   0.0672   0.09291   0.08623  -0.1142   0.7851   0.0211
  -5.750   0.0601   0.09220   0.08557  -0.1109   0.7786   0.0216
  -5.500   0.0569   0.09101   0.08440  -0.1088   0.7735   0.0222
  -5.000   0.0533   0.08855   0.08200  -0.1050   0.7633   0.0225
  -4.750   0.0547   0.08715   0.08061  -0.1037   0.7580   0.0226
  -4.500   0.0604   0.08540   0.07888  -0.1035   0.7542   0.0228
  -4.250   0.0621   0.08403   0.07752  -0.1023   0.7492   0.0228
  -4.000   0.0642   0.08268   0.07620  -0.1012   0.7435   0.0229
  -3.750   0.0718   0.08091   0.07443  -0.1014   0.7391   0.0231
  -3.250   0.0866   0.07767   0.07121  -0.1014   0.7301   0.0240
  -3.000   0.0961   0.07592   0.06945  -0.1020   0.7252   0.0247
  -2.750   0.1105   0.07381   0.06732  -0.1035   0.7215   0.0252
  -2.500   0.1283   0.07160   0.06508  -0.1056   0.7186   0.0253
  -2.250   0.1386   0.07014   0.06364  -0.1060   0.7132   0.0254
  -2.000   0.1550   0.06836   0.06185  -0.1076   0.7088   0.0256
  -1.750   0.1760   0.06634   0.05980  -0.1099   0.7052   0.0258
  -1.500   0.2004   0.06422   0.05764  -0.1129   0.7025   0.0262
  -1.250   0.2220   0.06246   0.05585  -0.1153   0.6987   0.0271
  -1.000   0.2453   0.06064   0.05401  -0.1180   0.6943   0.0278
  -0.750   0.2732   0.05863   0.05195  -0.1214   0.6907   0.0282
  -0.500   0.3040   0.05659   0.04986  -0.1252   0.6878   0.0283
  -0.250   0.3369   0.05462   0.04783  -0.1292   0.6855   0.0286
   0.000   0.3671   0.05299   0.04617  -0.1325   0.6822   0.0288
   0.250   0.3971   0.05156   0.04471  -0.1357   0.6782   0.0299
   0.500   0.4320   0.04988   0.04296  -0.1397   0.6748   0.0309
   0.750   0.4684   0.04818   0.04119  -0.1438   0.6721   0.0312
   1.000   0.5060   0.04652   0.03946  -0.1479   0.6697   0.0314
   1.250   0.5446   0.04489   0.03777  -0.1520   0.6675   0.0317
   1.500   0.5748   0.04395   0.03680  -0.1544   0.6633   0.0322
   1.750   0.6085   0.04286   0.03566  -0.1573   0.6596   0.0336
   2.000   0.6443   0.04164   0.03438  -0.1604   0.6565   0.0342
   2.250   0.6802   0.04044   0.03311  -0.1633   0.6536   0.0344
   2.500   0.7169   0.03924   0.03183  -0.1661   0.6510   0.0346
   2.750   0.7485   0.03843   0.03098  -0.1680   0.6473   0.0351
   3.000   0.7772   0.03787   0.03039  -0.1692   0.6431   0.0361
   3.250   0.8097   0.03706   0.02951  -0.1709   0.6395   0.0372
   3.500   0.8441   0.03595   0.02827  -0.1725   0.6270   0.0374
   3.750   0.8966   0.03321   0.02426  -0.1752   0.4834   0.0377
   4.000   0.8691   0.03639   0.02627  -0.1671   0.2868   0.0378
   4.250   0.8575   0.03914   0.02797  -0.1622   0.0438   0.0378
   4.500   0.8828   0.03891   0.02757  -0.1623   0.0345   0.0386
   4.750   0.9063   0.03885   0.02741  -0.1621   0.0314   0.0396
   5.000   0.9304   0.03872   0.02717  -0.1619   0.0292   0.0404
   5.250   0.9536   0.03866   0.02698  -0.1615   0.0279   0.0406
   5.500   0.9764   0.03864   0.02685  -0.1609   0.0274   0.0408
   5.750   0.9987   0.03871   0.02680  -0.1603   0.0268   0.0410
   6.000   1.0213   0.03869   0.02658  -0.1596   0.0263   0.0420
   6.250   1.0399   0.03909   0.02693  -0.1584   0.0254   0.0429
   6.500   1.0583   0.03953   0.02730  -0.1572   0.0248   0.0436
   6.750   1.0772   0.04003   0.02771  -0.1561   0.0239   0.0439
   7.000   1.0963   0.04065   0.02823  -0.1551   0.0232   0.0440
   7.250   1.1150   0.04133   0.02885  -0.1540   0.0226   0.0443
   7.500   1.1326   0.04211   0.02959  -0.1528   0.0220   0.0445
   7.750   1.1489   0.04297   0.03043  -0.1514   0.0218   0.0448
   8.000   1.1645   0.04388   0.03133  -0.1499   0.0216   0.0451
   8.250   1.1792   0.04486   0.03230  -0.1484   0.0214   0.0463
   8.500   1.1925   0.04596   0.03346  -0.1467   0.0213   0.0472
   8.750   1.2054   0.04712   0.03467  -0.1450   0.0211   0.0481
   9.000   1.2178   0.04833   0.03593  -0.1432   0.0209   0.0488
   9.250   1.2296   0.04962   0.03726  -0.1415   0.0208   0.0491
   9.500   1.2409   0.05098   0.03867  -0.1397   0.0207   0.0494
   9.750   1.2518   0.05239   0.04014  -0.1380   0.0206   0.0498
  10.000   1.2622   0.05387   0.04168  -0.1362   0.0205   0.0503
  10.250   1.2725   0.05539   0.04326  -0.1345   0.0203   0.0515
  10.500   1.2827   0.05694   0.04488  -0.1328   0.0202   0.0532
  10.750   1.2929   0.05850   0.04650  -0.1311   0.0202   0.0551
  11.000   1.3034   0.06005   0.04811  -0.1295   0.0200   0.0567
  11.250   1.3144   0.06157   0.04968  -0.1280   0.0198   0.0592
  11.500   1.3258   0.06307   0.05123  -0.1265   0.0196   0.0629
  11.750   1.3375   0.06455   0.05277  -0.1251   0.0194   0.0690
  12.250   1.3615   0.06663   0.05589  -0.1223   0.0186   1.0000
  12.500   1.3754   0.06794   0.05724  -0.1208   0.0182   1.0000
  12.750   1.3899   0.06922   0.05856  -0.1194   0.0180   1.0000
  13.000   1.4052   0.07047   0.05985  -0.1181   0.0179   1.0000
  13.250   1.4211   0.07169   0.06114  -0.1168   0.0177   1.0000
  13.500   1.4376   0.07291   0.06243  -0.1155   0.0176   1.0000
  13.750   1.4542   0.07415   0.06375  -0.1143   0.0174   1.0000
  14.000   1.4708   0.07546   0.06516  -0.1131   0.0173   1.0000
  14.250   1.4870   0.07687   0.06671  -0.1119   0.0171   1.0000
  14.500   1.5020   0.07843   0.06840  -0.1108   0.0170   1.0000
  14.750   1.5154   0.08016   0.07027  -0.1096   0.0167   1.0000
  15.000   1.5266   0.08206   0.07232  -0.1084   0.0164   1.0000
  15.250   1.5357   0.08411   0.07456  -0.1073   0.0162   1.0000
  15.500   1.5431   0.08632   0.07692  -0.1061   0.0159   1.0000
  15.750   1.5492   0.08871   0.07948  -0.1050   0.0157   1.0000
  16.000   1.5565   0.09170   0.08281  -0.1038   0.0153   1.0000
  16.250   1.5587   0.09490   0.08629  -0.1028   0.0151   1.0000
  16.500   1.5576   0.09843   0.09011  -0.1019   0.0150   1.0000
  16.750   1.5537   0.10228   0.09423  -0.1011   0.0149   1.0000
  17.000   1.5471   0.10647   0.09871  -0.1006   0.0148   1.0000
  17.250   1.5380   0.11101   0.10352  -0.1005   0.0147   1.0000
  17.500   1.5265   0.11594   0.10873  -0.1008   0.0146   1.0000
  17.750   1.5129   0.12130   0.11437  -0.1016   0.0145   1.0000
  18.000   1.4969   0.12723   0.12057  -0.1031   0.0145   1.0000
  18.250   1.4789   0.13378   0.12739  -0.1053   0.0144   1.0000
  18.500   1.4582   0.14122   0.13508  -0.1085   0.0144   1.0000
  18.750   1.4341   0.14997   0.14410  -0.1132   0.0143   1.0000
  19.000   1.4049   0.16093   0.15533  -0.1200   0.0143   1.0000
  19.250   1.3665   0.17701   0.17166  -0.1314   0.0143   1.0000
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