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Cambered plate C=8% T=5% R=1.6 (cp-080-050-gn) Xfoil prediction polar at RE=500,000 Ncrit=1


Details Polar file
Airfoil: Cambered plate C=8% T=5% R=1.6 (cp-080-050-gn)
Reynolds number: 500,000
Max Cl/Cd: 51.36 at α=8°
Description: Mach=0 Ncrit=1
Source: Xfoil prediction
Download polar: xf-cp-080-050-gn-500000-n1.txt
Download as CSV file: xf-cp-080-050-gn-500000-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 =     0.500 e 6     Ncrit =   1.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.0602   0.09386   0.09036  -0.1196   0.9104   0.0237
  -8.250  -0.0461   0.09106   0.08754  -0.1223   0.9054   0.0240
  -7.750  -0.0197   0.08559   0.08202  -0.1273   0.8941   0.0251
  -7.500  -0.0056   0.08329   0.07969  -0.1294   0.8879   0.0253
  -7.250   0.0059   0.08089   0.07728  -0.1311   0.8812   0.0257
  -7.000   0.0179   0.07857   0.07492  -0.1328   0.8747   0.0261
  -6.750   0.0281   0.07638   0.07271  -0.1340   0.8679   0.0262
  -6.500   0.0376   0.07418   0.07049  -0.1352   0.8601   0.0267
  -6.250   0.0450   0.07181   0.06809  -0.1362   0.8530   0.0272
  -6.000   0.0515   0.06960   0.06586  -0.1368   0.8449   0.0278
  -5.750   0.0597   0.06778   0.06402  -0.1372   0.8377   0.0280
  -5.500   0.0655   0.06589   0.06214  -0.1373   0.8309   0.0284
  -5.250   0.0692   0.06408   0.06031  -0.1371   0.8222   0.0287
  -5.000   0.0708   0.06235   0.05857  -0.1365   0.8148   0.0290
  -4.750   0.0764   0.06034   0.05655  -0.1371   0.8069   0.0294
  -4.500   0.0836   0.05820   0.05437  -0.1380   0.7997   0.0297
  -4.250   0.0912   0.05568   0.05183  -0.1394   0.7932   0.0304
  -4.000   0.1020   0.05355   0.04967  -0.1405   0.7852   0.0309
  -3.750   0.1149   0.05162   0.04770  -0.1416   0.7773   0.0312
  -3.500   0.1279   0.04966   0.04567  -0.1424   0.7647   0.0315
  -3.250   0.1376   0.04798   0.04381  -0.1422   0.7306   0.0319
  -3.000   0.1495   0.04613   0.04182  -0.1423   0.7054   0.0324
  -2.750   0.1550   0.04471   0.04009  -0.1406   0.6464   0.0328
  -2.500   0.1303   0.04583   0.04003  -0.1319   0.3617   0.0329
  -2.250   0.1290   0.04534   0.03879  -0.1288   0.1043   0.0333
  -2.000   0.1456   0.04307   0.03634  -0.1295   0.0456   0.0341
  -1.750   0.1656   0.04139   0.03458  -0.1300   0.0397   0.0345
  -1.500   0.1864   0.03963   0.03274  -0.1304   0.0386   0.0348
  -1.250   0.2075   0.03783   0.03086  -0.1308   0.0379   0.0353
  -1.000   0.2291   0.03594   0.02888  -0.1311   0.0372   0.0358
  -0.750   0.2509   0.03389   0.02671  -0.1314   0.0363   0.0365
  -0.500   0.2731   0.03152   0.02419  -0.1316   0.0359   0.0375
  -0.250   0.2951   0.03015   0.02273  -0.1312   0.0355   0.0379
   0.000   0.3172   0.02867   0.02114  -0.1307   0.0350   0.0383
   0.250   0.3392   0.02705   0.01937  -0.1300   0.0347   0.0389
   0.500   0.3612   0.02521   0.01735  -0.1293   0.0344   0.0397
   0.750   0.3822   0.02237   0.01418  -0.1283   0.0341   0.0412
   1.000   0.4029   0.02110   0.01275  -0.1269   0.0339   0.0417
   1.250   0.4235   0.01947   0.01086  -0.1254   0.0337   0.0425
   1.500   0.4436   0.01670   0.00754  -0.1239   0.0335   0.0448
   1.750   0.4653   0.01634   0.00707  -0.1224   0.0332   0.0451
   2.000   0.4869   0.01604   0.00668  -0.1209   0.0331   0.0455
   2.250   0.5086   0.01580   0.00634  -0.1194   0.0329   0.0460
   2.500   0.5304   0.01562   0.00609  -0.1178   0.0326   0.0464
   2.750   0.5521   0.01547   0.00587  -0.1163   0.0323   0.0468
   3.000   0.5738   0.01538   0.00572  -0.1147   0.0319   0.0473
   3.250   0.5954   0.01531   0.00559  -0.1132   0.0315   0.0479
   3.500   0.6169   0.01530   0.00553  -0.1116   0.0311   0.0484
   3.750   0.6383   0.01535   0.00556  -0.1100   0.0311   0.0486
   4.000   0.6597   0.01546   0.00566  -0.1084   0.0308   0.0487
   4.250   0.6810   0.01557   0.00576  -0.1068   0.0307   0.0489
   4.500   0.7020   0.01570   0.00588  -0.1051   0.0306   0.0491
   4.750   0.7227   0.01584   0.00601  -0.1034   0.0304   0.0492
   5.000   0.7433   0.01598   0.00616  -0.1017   0.0304   0.0494
   5.250   0.7637   0.01615   0.00632  -0.0999   0.0302   0.0496
   5.500   0.7840   0.01632   0.00649  -0.0982   0.0301   0.0498
   5.750   0.8040   0.01652   0.00668  -0.0964   0.0300   0.0500
   6.000   0.8237   0.01673   0.00691  -0.0945   0.0299   0.0506
   6.250   0.8434   0.01694   0.00713  -0.0927   0.0298   0.0508
   6.500   0.8630   0.01718   0.00738  -0.0909   0.0297   0.0513
   6.750   0.8822   0.01743   0.00764  -0.0890   0.0297   0.0515
   7.000   0.9009   0.01771   0.00794  -0.0870   0.0296   0.0516
   7.250   0.9197   0.01800   0.00824  -0.0851   0.0295   0.0518
   7.500   0.9384   0.01831   0.00857  -0.0832   0.0294   0.0519
   7.750   0.9568   0.01863   0.00892  -0.0812   0.0291   0.0522
   8.000   0.9748   0.01898   0.00929  -0.0793   0.0290   0.0523
   8.250   0.9928   0.01934   0.00967  -0.0773   0.0287   0.0524
   8.500   1.0107   0.01972   0.01008  -0.0753   0.0285   0.0526
   8.750   1.0281   0.02013   0.01052  -0.0733   0.0283   0.0528
   9.000   1.0454   0.02055   0.01097  -0.0714   0.0281   0.0531
   9.250   1.0625   0.02100   0.01145  -0.0693   0.0281   0.0533
   9.500   1.0797   0.02146   0.01194  -0.0674   0.0279   0.0535
   9.750   1.0963   0.02195   0.01246  -0.0654   0.0277   0.0538
  10.000   1.1129   0.02246   0.01301  -0.0634   0.0276   0.0544
  10.250   1.1295   0.02297   0.01357  -0.0615   0.0274   0.0552
  10.500   1.1457   0.02353   0.01416  -0.0595   0.0274   0.0555
  10.750   1.1621   0.02408   0.01474  -0.0576   0.0272   0.0565
  11.000   1.1781   0.02467   0.01538  -0.0556   0.0271   0.0571
  11.250   1.1942   0.02527   0.01602  -0.0538   0.0270   0.0577
  11.500   1.2100   0.02589   0.01667  -0.0519   0.0268   0.0581
  11.750   1.2257   0.02653   0.01735  -0.0500   0.0267   0.0588
  12.000   1.2418   0.02714   0.01800  -0.0482   0.0265   0.0596
  12.250   1.2577   0.02777   0.01867  -0.0465   0.0263   0.0608
  13.000   1.3021   0.02992   0.02118  -0.0410   0.0259   0.2267
  13.750   1.3825   0.03217   0.02472  -0.0438   0.0255   1.0000
  14.000   1.3961   0.03311   0.02571  -0.0420   0.0254   1.0000
  14.250   1.4097   0.03406   0.02671  -0.0402   0.0253   1.0000
  14.500   1.4227   0.03508   0.02778  -0.0385   0.0251   1.0000
  14.750   1.4354   0.03613   0.02889  -0.0368   0.0250   1.0000
  15.000   1.4480   0.03719   0.03001  -0.0351   0.0248   1.0000
  15.250   1.4600   0.03832   0.03121  -0.0334   0.0247   1.0000
  15.500   1.4715   0.03950   0.03246  -0.0317   0.0245   1.0000
  15.750   1.4829   0.04069   0.03371  -0.0300   0.0244   1.0000
  16.000   1.4936   0.04198   0.03508  -0.0284   0.0243   1.0000
  16.250   1.5036   0.04331   0.03649  -0.0268   0.0242   1.0000
  16.500   1.5132   0.04471   0.03797  -0.0252   0.0240   1.0000
  16.750   1.5225   0.04614   0.03948  -0.0237   0.0239   1.0000
  17.000   1.5310   0.04764   0.04107  -0.0222   0.0237   1.0000
  17.250   1.5388   0.04926   0.04277  -0.0207   0.0236   1.0000
  17.500   1.5465   0.05083   0.04442  -0.0194   0.0233   1.0000
  17.750   1.5528   0.05263   0.04631  -0.0180   0.0233   1.0000
  18.000   1.5590   0.05441   0.04817  -0.0168   0.0231   1.0000
  18.250   1.5645   0.05632   0.05018  -0.0157   0.0230   1.0000
  18.500   1.5686   0.05841   0.05237  -0.0146   0.0230   1.0000
  18.750   1.5727   0.06054   0.05458  -0.0136   0.0229   1.0000
  19.000   1.5753   0.06288   0.05702  -0.0128   0.0228   1.0000
  19.250   1.5762   0.06549   0.05975  -0.0120   0.0227   1.0000
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