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Cambered plate C=12% T=5% R=1.1 (cp-120-050-gn) Xfoil prediction polar at RE=200,000 Ncrit=1


Details Polar file
Airfoil: Cambered plate C=12% T=5% R=1.1 (cp-120-050-gn)
Reynolds number: 200,000
Max Cl/Cd: 34.63 at α=6.5°
Description: Mach=0 Ncrit=1
Source: Xfoil prediction
Download polar: xf-cp-120-050-gn-200000-n1.txt
Download as CSV file: xf-cp-120-050-gn-200000-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 =     0.200 e 6     Ncrit =   1.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.750   0.1057   0.11103   0.10571  -0.1587   0.8663   0.0140
 -10.500   0.1144   0.10884   0.10350  -0.1596   0.8630   0.0142
 -10.250   0.1241   0.10655   0.10119  -0.1608   0.8598   0.0145
 -10.000   0.1351   0.10422   0.09885  -0.1623   0.8565   0.0149
  -9.750   0.1476   0.10201   0.09661  -0.1640   0.8535   0.0155
  -9.500   0.1563   0.09998   0.09458  -0.1647   0.8497   0.0157
  -9.250   0.1648   0.09802   0.09261  -0.1653   0.8461   0.0159
  -9.000   0.1743   0.09598   0.09056  -0.1661   0.8422   0.0161
  -8.750   0.1849   0.09388   0.08844  -0.1673   0.8385   0.0163
  -8.500   0.1949   0.09190   0.08644  -0.1681   0.8350   0.0164
  -8.250   0.2018   0.09013   0.08467  -0.1681   0.8310   0.0165
  -8.000   0.2086   0.08815   0.08269  -0.1683   0.8269   0.0172
  -7.750   0.2182   0.08639   0.08092  -0.1688   0.8228   0.0176
  -7.500   0.2277   0.08459   0.07911  -0.1694   0.8189   0.0180
  -7.250   0.2329   0.08305   0.07757  -0.1687   0.8146   0.0183
  -7.000   0.2387   0.08149   0.07602  -0.1682   0.8103   0.0184
  -6.750   0.2455   0.07986   0.07438  -0.1680   0.8060   0.0186
  -6.500   0.2514   0.07829   0.07281  -0.1675   0.8015   0.0187
  -6.250   0.2530   0.07703   0.07157  -0.1658   0.7969   0.0189
  -6.000   0.2542   0.07574   0.07030  -0.1641   0.7921   0.0191
  -5.750   0.2554   0.07436   0.06892  -0.1625   0.7872   0.0195
  -5.500   0.2507   0.07343   0.06802  -0.1592   0.7820   0.0200
  -5.250   0.2496   0.07235   0.06697  -0.1568   0.7771   0.0203
  -5.000   0.2525   0.07104   0.06566  -0.1554   0.7724   0.0206
  -4.750   0.2565   0.06966   0.06428  -0.1543   0.7677   0.0207
  -4.500   0.2573   0.06845   0.06309  -0.1523   0.7627   0.0209
  -4.250   0.2610   0.06709   0.06175  -0.1511   0.7582   0.0210
  -4.000   0.2693   0.06553   0.06018  -0.1509   0.7538   0.0211
  -3.750   0.2754   0.06407   0.05872  -0.1501   0.7491   0.0214
  -3.500   0.2820   0.06261   0.05728  -0.1494   0.7445   0.0216
  -3.250   0.2924   0.06089   0.05555  -0.1497   0.7401   0.0221
  -3.000   0.3073   0.05908   0.05371  -0.1508   0.7363   0.0228
  -2.750   0.3194   0.05755   0.05219  -0.1510   0.7317   0.0232
  -2.500   0.3337   0.05592   0.05056  -0.1517   0.7274   0.0234
  -2.250   0.3515   0.05419   0.04881  -0.1531   0.7236   0.0236
  -2.000   0.3733   0.05233   0.04691  -0.1552   0.7199   0.0238
  -1.750   0.3947   0.05052   0.04508  -0.1572   0.7159   0.0241
  -1.500   0.4170   0.04872   0.04325  -0.1593   0.7119   0.0246
  -1.250   0.4433   0.04674   0.04124  -0.1622   0.7083   0.0255
  -1.000   0.4710   0.04503   0.03950  -0.1650   0.7047   0.0260
  -0.750   0.5016   0.04323   0.03764  -0.1683   0.7013   0.0263
  -0.500   0.5299   0.04160   0.03598  -0.1709   0.6975   0.0265
  -0.250   0.5605   0.03995   0.03429  -0.1740   0.6940   0.0269
   0.000   0.5934   0.03828   0.03257  -0.1773   0.6904   0.0274
   0.500   0.6635   0.03503   0.02920  -0.1844   0.6835   0.0290
   0.750   0.6958   0.03369   0.02782  -0.1870   0.6800   0.0293
   1.000   0.7290   0.03238   0.02646  -0.1897   0.6764   0.0296
   1.250   0.7632   0.03108   0.02511  -0.1924   0.6726   0.0300
   1.500   0.7986   0.02971   0.02358  -0.1952   0.6587   0.0312
   1.750   0.8258   0.02879   0.02235  -0.1960   0.6193   0.0319
   2.000   0.8273   0.02912   0.02214  -0.1915   0.5412   0.0321
   2.250   0.7991   0.03126   0.02353  -0.1819   0.4084   0.0321
   2.500   0.7755   0.03367   0.02515  -0.1739   0.2366   0.0321
   2.750   0.7662   0.03543   0.02627  -0.1687   0.0357   0.0322
   3.000   0.7925   0.03490   0.02563  -0.1693   0.0284   0.0324
   3.250   0.8198   0.03432   0.02496  -0.1701   0.0269   0.0328
   3.500   0.8467   0.03377   0.02432  -0.1707   0.0257   0.0334
   3.750   0.8756   0.03305   0.02344  -0.1715   0.0244   0.0347
   4.000   0.9004   0.03267   0.02296  -0.1715   0.0232   0.0351
   4.250   0.9242   0.03238   0.02258  -0.1713   0.0223   0.0353
   4.500   0.9478   0.03211   0.02220  -0.1709   0.0215   0.0357
   4.750   0.9712   0.03186   0.02183  -0.1705   0.0210   0.0360
   5.000   0.9956   0.03147   0.02126  -0.1701   0.0206   0.0372
   5.250   1.0219   0.03078   0.02028  -0.1698   0.0204   0.0384
   5.500   1.0414   0.03089   0.02028  -0.1686   0.0201   0.0386
   5.750   1.0604   0.03107   0.02035  -0.1672   0.0199   0.0389
   6.000   1.0788   0.03134   0.02052  -0.1658   0.0198   0.0392
   6.250   1.0963   0.03172   0.02081  -0.1643   0.0195   0.0396
   6.500   1.1134   0.03215   0.02116  -0.1627   0.0195   0.0408
   6.750   1.1302   0.03266   0.02159  -0.1612   0.0193   0.0415
   7.000   1.1463   0.03329   0.02220  -0.1595   0.0192   0.0416
   7.250   1.1612   0.03400   0.02291  -0.1577   0.0191   0.0418
   7.500   1.1757   0.03477   0.02371  -0.1559   0.0189   0.0419
   7.750   1.1903   0.03561   0.02457  -0.1542   0.0189   0.0421
   8.000   1.2045   0.03654   0.02553  -0.1524   0.0188   0.0422
   8.250   1.2183   0.03755   0.02659  -0.1508   0.0187   0.0424
   8.500   1.2322   0.03862   0.02772  -0.1491   0.0186   0.0427
   8.750   1.2454   0.03976   0.02890  -0.1474   0.0185   0.0429
   9.000   1.2581   0.04096   0.03014  -0.1457   0.0184   0.0431
   9.250   1.2705   0.04218   0.03141  -0.1440   0.0182   0.0436
   9.500   1.2822   0.04348   0.03276  -0.1422   0.0181   0.0446
   9.750   1.2940   0.04478   0.03410  -0.1405   0.0178   0.0457
  10.000   1.3057   0.04611   0.03548  -0.1388   0.0175   0.0464
  10.250   1.3167   0.04750   0.03692  -0.1371   0.0173   0.0468
  10.500   1.3280   0.04889   0.03835  -0.1354   0.0170   0.0471
  10.750   1.3390   0.05033   0.03984  -0.1337   0.0169   0.0476
  11.000   1.3499   0.05179   0.04135  -0.1321   0.0167   0.0481
  11.250   1.3607   0.05329   0.04290  -0.1305   0.0167   0.0490
  11.500   1.3718   0.05477   0.04443  -0.1289   0.0165   0.0505
  11.750   1.3829   0.05628   0.04600  -0.1274   0.0165   0.0528
  12.000   1.3939   0.05779   0.04756  -0.1259   0.0164   0.0567
  12.250   1.4053   0.05928   0.04911  -0.1244   0.0163   0.0626
  12.500   1.4211   0.06022   0.05103  -0.1241   0.0161   1.0000
  12.750   1.4324   0.06171   0.05255  -0.1227   0.0161   1.0000
  13.000   1.4438   0.06319   0.05407  -0.1212   0.0160   1.0000
  13.250   1.4553   0.06468   0.05559  -0.1198   0.0159   1.0000
  13.500   1.4669   0.06615   0.05711  -0.1184   0.0158   1.0000
  13.750   1.4786   0.06762   0.05861  -0.1171   0.0157   1.0000
  14.000   1.4918   0.06899   0.06008  -0.1157   0.0155   1.0000
  14.250   1.5062   0.07027   0.06147  -0.1143   0.0152   1.0000
  14.500   1.5215   0.07151   0.06283  -0.1129   0.0148   1.0000
  14.750   1.5367   0.07281   0.06425  -0.1117   0.0144   1.0000
  15.000   1.5511   0.07423   0.06579  -0.1104   0.0142   1.0000
  15.250   1.5650   0.07575   0.06745  -0.1092   0.0140   1.0000
  15.500   1.5780   0.07740   0.06925  -0.1080   0.0139   1.0000
  15.750   1.5900   0.07922   0.07123  -0.1068   0.0137   1.0000
  16.000   1.6003   0.08124   0.07343  -0.1056   0.0135   1.0000
  16.250   1.6088   0.08347   0.07584  -0.1044   0.0133   1.0000
  16.500   1.6151   0.08593   0.07850  -0.1033   0.0132   1.0000
  16.750   1.6193   0.08863   0.08139  -0.1022   0.0131   1.0000
  17.000   1.6217   0.09152   0.08448  -0.1012   0.0129   1.0000
  17.250   1.6220   0.09462   0.08779  -0.1003   0.0128   1.0000
  17.500   1.6207   0.09797   0.09134  -0.0996   0.0126   1.0000
  17.750   1.6130   0.10291   0.09664  -0.0989   0.0123   1.0000
  18.000   1.6018   0.10808   0.10213  -0.0987   0.0120   1.0000
  18.250   1.5886   0.11339   0.10772  -0.0989   0.0118   1.0000
  18.500   1.5734   0.11904   0.11363  -0.0997   0.0117   1.0000
  18.750   1.5558   0.12523   0.12008  -0.1010   0.0116   1.0000
  19.000   1.5356   0.13211   0.12721  -0.1032   0.0115   1.0000
  19.250   1.5122   0.13996   0.13532  -0.1065   0.0114   1.0000
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