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Cambered plate C=8% T=5% R=1.6 (cp-080-050-gn) Xfoil prediction polar at RE=200,000 Ncrit=1


Details Polar file
Airfoil: Cambered plate C=8% T=5% R=1.6 (cp-080-050-gn)
Reynolds number: 200,000
Max Cl/Cd: 37.75 at α=7.75°
Description: Mach=0 Ncrit=1
Source: Xfoil prediction
Download polar: xf-cp-080-050-gn-200000-n1.txt
Download as CSV file: xf-cp-080-050-gn-200000-n1.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: Cambered plate C=8% T=5% R=1.6                  
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -12.000  -0.2730   0.14531   0.14038  -0.0685   0.9532   0.0199
 -11.750  -0.2644   0.14256   0.13763  -0.0699   0.9504   0.0204
 -11.500  -0.2556   0.13968   0.13474  -0.0714   0.9480   0.0209
 -11.250  -0.2469   0.13665   0.13170  -0.0731   0.9459   0.0214
 -11.000  -0.2371   0.13368   0.12871  -0.0750   0.9437   0.0217
 -10.500  -0.2178   0.12805   0.12308  -0.0783   0.9387   0.0222
 -10.250  -0.2084   0.12546   0.12049  -0.0796   0.9357   0.0225
 -10.000  -0.1983   0.12277   0.11779  -0.0812   0.9329   0.0229
  -9.750  -0.1880   0.11985   0.11487  -0.0831   0.9301   0.0235
  -9.500  -0.1769   0.11686   0.11186  -0.0853   0.9276   0.0240
  -9.250  -0.1652   0.11388   0.10887  -0.0875   0.9254   0.0242
  -9.000  -0.1564   0.11122   0.10621  -0.0888   0.9220   0.0244
  -8.750  -0.1463   0.10840   0.10339  -0.0906   0.9183   0.0247
  -8.500  -0.1338   0.10582   0.10081  -0.0926   0.9151   0.0250
  -8.250  -0.1206   0.10313   0.09811  -0.0948   0.9121   0.0253
  -8.000  -0.1069   0.10031   0.09528  -0.0973   0.9095   0.0260
  -7.750  -0.0960   0.09764   0.09259  -0.0991   0.9054   0.0266
  -7.500  -0.0847   0.09505   0.09001  -0.1009   0.9010   0.0268
  -7.250  -0.0727   0.09230   0.08725  -0.1030   0.8969   0.0271
  -7.000  -0.0597   0.08950   0.08443  -0.1054   0.8931   0.0275
  -6.750  -0.0477   0.08698   0.08191  -0.1073   0.8886   0.0276
  -6.500  -0.0358   0.08476   0.07969  -0.1088   0.8834   0.0280
  -6.250  -0.0232   0.08237   0.07729  -0.1107   0.8785   0.0286
  -6.000  -0.0098   0.07984   0.07475  -0.1129   0.8738   0.0292
  -5.750  -0.0010   0.07756   0.07248  -0.1140   0.8676   0.0297
  -5.500   0.0091   0.07528   0.07019  -0.1153   0.8614   0.0299
  -5.250   0.0193   0.07285   0.06775  -0.1169   0.8558   0.0303
  -5.000   0.0251   0.07084   0.06574  -0.1173   0.8487   0.0305
  -4.750   0.0304   0.06880   0.06371  -0.1176   0.8418   0.0308
  -4.500   0.0391   0.06685   0.06176  -0.1186   0.8359   0.0312
  -4.250   0.0476   0.06486   0.05978  -0.1194   0.8289   0.0318
  -4.000   0.0584   0.06268   0.05758  -0.1208   0.8226   0.0324
  -3.750   0.0704   0.06043   0.05531  -0.1225   0.8169   0.0328
  -3.500   0.0820   0.05828   0.05315  -0.1237   0.8104   0.0330
  -3.250   0.0958   0.05596   0.05080  -0.1254   0.8043   0.0334
  -3.000   0.1117   0.05358   0.04838  -0.1273   0.7990   0.0338
  -2.750   0.1275   0.05156   0.04635  -0.1285   0.7930   0.0343
  -2.500   0.1455   0.04954   0.04430  -0.1299   0.7872   0.0349
  -2.250   0.1655   0.04741   0.04212  -0.1317   0.7821   0.0356
  -2.000   0.1849   0.04530   0.03996  -0.1330   0.7766   0.0360
  -1.750   0.2053   0.04321   0.03781  -0.1343   0.7708   0.0364
  -1.500   0.2289   0.04106   0.03556  -0.1359   0.7601   0.0368
  -1.250   0.2531   0.03887   0.03318  -0.1374   0.7356   0.0374
  -1.000   0.2757   0.03737   0.03136  -0.1378   0.6878   0.0381
  -0.750   0.2747   0.03716   0.03031  -0.1329   0.5391   0.0386
  -0.500   0.2521   0.03855   0.03046  -0.1240   0.2435   0.0388
  -0.250   0.2567   0.03817   0.02949  -0.1207   0.0547   0.0391
   0.000   0.2781   0.03659   0.02777  -0.1206   0.0484   0.0395
   0.250   0.3001   0.03498   0.02604  -0.1204   0.0457   0.0399
   0.500   0.3223   0.03338   0.02431  -0.1202   0.0439   0.0404
   1.000   0.3655   0.03069   0.02137  -0.1187   0.0405   0.0420
   1.250   0.3868   0.02944   0.01998  -0.1177   0.0393   0.0426
   1.500   0.4083   0.02822   0.01862  -0.1167   0.0385   0.0430
   1.750   0.4302   0.02698   0.01721  -0.1156   0.0380   0.0435
   2.000   0.4528   0.02553   0.01554  -0.1145   0.0377   0.0444
   2.250   0.4747   0.02451   0.01435  -0.1133   0.0373   0.0453
   2.500   0.4966   0.02363   0.01330  -0.1119   0.0369   0.0461
   2.750   0.5186   0.02277   0.01225  -0.1105   0.0365   0.0466
   3.000   0.5404   0.02200   0.01128  -0.1091   0.0362   0.0472
   3.250   0.5625   0.02120   0.01024  -0.1076   0.0359   0.0481
   3.500   0.5838   0.02088   0.00979  -0.1061   0.0356   0.0491
   3.750   0.6048   0.02075   0.00958  -0.1045   0.0354   0.0496
   4.000   0.6257   0.02066   0.00941  -0.1029   0.0351   0.0500
   4.250   0.6464   0.02060   0.00929  -0.1012   0.0350   0.0503
   4.500   0.6669   0.02060   0.00923  -0.0995   0.0347   0.0507
   4.750   0.6870   0.02064   0.00923  -0.0978   0.0343   0.0510
   5.000   0.7069   0.02072   0.00926  -0.0961   0.0341   0.0514
   5.250   0.7266   0.02081   0.00932  -0.0943   0.0337   0.0523
   5.500   0.7459   0.02097   0.00948  -0.0924   0.0332   0.0528
   5.750   0.7649   0.02121   0.00973  -0.0906   0.0329   0.0530
   6.000   0.7835   0.02147   0.01002  -0.0887   0.0326   0.0533
   6.250   0.8019   0.02175   0.01031  -0.0867   0.0324   0.0535
   6.500   0.8199   0.02206   0.01065  -0.0848   0.0322   0.0537
   6.750   0.8379   0.02240   0.01101  -0.0828   0.0321   0.0540
   7.000   0.8554   0.02277   0.01140  -0.0808   0.0319   0.0542
   7.250   0.8728   0.02317   0.01182  -0.0789   0.0317   0.0544
   7.500   0.8902   0.02359   0.01227  -0.0769   0.0316   0.0546
   7.750   0.9075   0.02404   0.01274  -0.0749   0.0314   0.0550
   8.000   0.9246   0.02452   0.01325  -0.0730   0.0313   0.0552
   8.250   0.9419   0.02503   0.01378  -0.0711   0.0312   0.0556
   8.500   0.9593   0.02556   0.01433  -0.0693   0.0310   0.0564
   8.750   0.9768   0.02611   0.01491  -0.0675   0.0309   0.0573
   9.000   0.9942   0.02667   0.01550  -0.0657   0.0306   0.0580
   9.250   1.0113   0.02724   0.01610  -0.0639   0.0305   0.0586
   9.500   1.0284   0.02782   0.01670  -0.0621   0.0303   0.0590
   9.750   1.0456   0.02840   0.01730  -0.0604   0.0301   0.0595
  10.000   1.0627   0.02908   0.01802  -0.0586   0.0298   0.0599
  10.250   1.0805   0.02981   0.01879  -0.0570   0.0294   0.0606
  10.500   1.0986   0.03055   0.01958  -0.0555   0.0293   0.0611
  10.750   1.1170   0.03132   0.02039  -0.0541   0.0291   0.0619
  11.000   1.1356   0.03212   0.02125  -0.0526   0.0289   0.0641
  11.250   1.1544   0.03294   0.02214  -0.0513   0.0287   0.0667
  11.500   1.1733   0.03380   0.02306  -0.0499   0.0285   0.0693
  12.000   1.2110   0.03560   0.02502  -0.0474   0.0281   0.0842
  12.500   1.2665   0.03687   0.02771  -0.0488   0.0274   1.0000
  12.750   1.2834   0.03792   0.02883  -0.0473   0.0271   1.0000
  13.000   1.2992   0.03900   0.02999  -0.0457   0.0268   1.0000
  13.250   1.3141   0.04012   0.03118  -0.0441   0.0265   1.0000
  13.500   1.3281   0.04128   0.03243  -0.0424   0.0263   1.0000
  13.750   1.3413   0.04254   0.03378  -0.0408   0.0262   1.0000
  14.000   1.3555   0.04418   0.03558  -0.0392   0.0260   1.0000
  14.250   1.3675   0.04592   0.03749  -0.0376   0.0258   1.0000
  14.500   1.3776   0.04792   0.03967  -0.0358   0.0255   1.0000
  14.750   1.3850   0.05008   0.04204  -0.0340   0.0252   1.0000
  15.000   1.3894   0.05241   0.04457  -0.0320   0.0250   1.0000
  15.250   1.3908   0.05500   0.04739  -0.0300   0.0248   1.0000
  15.500   1.3887   0.05795   0.05057  -0.0280   0.0245   1.0000
  15.750   1.3838   0.06109   0.05394  -0.0261   0.0241   1.0000
  16.000   1.3752   0.06461   0.05770  -0.0243   0.0238   1.0000
  16.250   1.3641   0.06841   0.06173  -0.0229   0.0236   1.0000
  16.500   1.3493   0.07269   0.06625  -0.0219   0.0233   1.0000
  16.750   1.3319   0.07743   0.07123  -0.0214   0.0232   1.0000
  17.000   1.3100   0.08302   0.07706  -0.0217   0.0230   1.0000
  17.250   1.2815   0.08999   0.08429  -0.0233   0.0229   1.0000
  17.500   1.2455   0.09884   0.09343  -0.0267   0.0228   1.0000
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