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Cambered plate C=12% T=5% R=1.1 (cp-120-050-gn) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: Cambered plate C=12% T=5% R=1.1 (cp-120-050-gn)
Reynolds number: 1,000,000
Max Cl/Cd: 43.78 at α=5.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-cp-120-050-gn-1000000.txt
Download as CSV file: xf-cp-120-050-gn-1000000.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 =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.750   0.1273   0.11433   0.11207  -0.1720   0.9567   0.0223
 -11.500   0.1373   0.11121   0.10893  -0.1748   0.9542   0.0225
 -11.250   0.1508   0.10822   0.10593  -0.1772   0.9526   0.0226
 -11.000   0.1670   0.10566   0.10337  -0.1798   0.9511   0.0227
 -10.750   0.1858   0.10322   0.10091  -0.1831   0.9499   0.0229
 -10.500   0.2058   0.10063   0.09830  -0.1870   0.9489   0.0233
 -10.250   0.2275   0.09786   0.09551  -0.1914   0.9478   0.0239
 -10.000   0.2377   0.09583   0.09348  -0.1923   0.9443   0.0244
  -9.750   0.2483   0.09340   0.09103  -0.1938   0.9405   0.0252
  -9.500   0.2632   0.09064   0.08824  -0.1973   0.9376   0.0253
  -9.250   0.2815   0.08759   0.08516  -0.2014   0.9353   0.0254
  -9.000   0.3035   0.08503   0.08259  -0.2048   0.9335   0.0256
  -8.750   0.3156   0.08342   0.08097  -0.2055   0.9298   0.0259
  -8.500   0.3249   0.08183   0.07938  -0.2057   0.9253   0.0261
  -8.250   0.3406   0.07978   0.07731  -0.2078   0.9219   0.0264
  -8.000   0.3610   0.07752   0.07501  -0.2112   0.9189   0.0271
  -7.750   0.3739   0.07553   0.07301  -0.2127   0.9149   0.0280
  -7.500   0.3783   0.07381   0.07128  -0.2125   0.9092   0.0283
  -7.250   0.3899   0.07159   0.06902  -0.2151   0.9045   0.0284
  -7.000   0.4102   0.06916   0.06656  -0.2173   0.9015   0.0286
  -6.750   0.4143   0.06803   0.06545  -0.2154   0.8968   0.0287
  -6.500   0.4230   0.06665   0.06406  -0.2150   0.8922   0.0289
  -6.250   0.4374   0.06506   0.06244  -0.2161   0.8882   0.0291
  -6.000   0.4501   0.06361   0.06098  -0.2168   0.8839   0.0297
  -5.750   0.4524   0.06250   0.05989  -0.2148   0.8787   0.0301
  -5.500   0.4581   0.06113   0.05851  -0.2139   0.8738   0.0310
  -5.250   0.4687   0.05947   0.05679  -0.2164   0.8682   0.0315
  -5.000   0.4728   0.05815   0.05549  -0.2166   0.8626   0.0316
  -4.750   0.4836   0.05612   0.05346  -0.2158   0.8589   0.0317
  -4.500   0.4992   0.05446   0.05177  -0.2163   0.8554   0.0318
  -4.250   0.5152   0.05301   0.05031  -0.2172   0.8516   0.0320
  -4.000   0.5250   0.05182   0.04914  -0.2166   0.8473   0.0322
  -3.750   0.5388   0.05051   0.04783  -0.2169   0.8431   0.0326
  -3.500   0.5576   0.04901   0.04630  -0.2185   0.8393   0.0331
  -3.250   0.5787   0.04732   0.04457  -0.2209   0.8354   0.0344
  -3.000   0.6040   0.04537   0.04260  -0.2263   0.8306   0.0349
  -2.750   0.6209   0.04331   0.04052  -0.2272   0.8261   0.0350
  -2.500   0.6384   0.04170   0.03887  -0.2273   0.8217   0.0351
  -2.250   0.6512   0.04050   0.03768  -0.2263   0.8151   0.0352
  -2.000   0.6682   0.03928   0.03645  -0.2263   0.8099   0.0355
  -1.750   0.6919   0.03797   0.03507  -0.2279   0.8034   0.0359
  -1.500   0.7090   0.03678   0.03389  -0.2278   0.7986   0.0366
  -1.250   0.7413   0.03503   0.03208  -0.2317   0.7927   0.0382
  -1.000   0.7874   0.03271   0.02961  -0.2392   0.7870   0.0383
  -0.750   0.8014   0.03103   0.02795  -0.2380   0.7820   0.0385
  -0.500   0.8131   0.02999   0.02689  -0.2358   0.7738   0.0386
  -0.250   0.8264   0.02907   0.02595  -0.2340   0.7668   0.0388
   0.000   0.8388   0.02821   0.02506  -0.2318   0.7575   0.0391
   0.250   0.8559   0.02730   0.02412  -0.2307   0.7490   0.0396
   0.500   0.8706   0.02641   0.02315  -0.2290   0.7366   0.0402
   0.750   0.9074   0.02480   0.02136  -0.2319   0.7213   0.0420
   1.000   0.9284   0.02353   0.01996  -0.2313   0.7049   0.0421
   1.250   0.9319   0.02256   0.01885  -0.2272   0.6756   0.0423
   1.500   0.9222   0.02273   0.01877  -0.2198   0.6272   0.0424
   1.750   0.8992   0.02373   0.01933  -0.2100   0.5420   0.0425
   2.000   0.8689   0.02565   0.02055  -0.1992   0.4035   0.0425
   2.250   0.8412   0.02801   0.02211  -0.1896   0.2190   0.0425
   2.500   0.8329   0.02938   0.02291  -0.1838   0.0409   0.0426
   2.750   0.8538   0.02904   0.02253  -0.1833   0.0348   0.0429
   3.000   0.8766   0.02864   0.02209  -0.1831   0.0329   0.0434
   3.250   0.9017   0.02813   0.02153  -0.1832   0.0320   0.0444
   3.500   0.9472   0.02604   0.01917  -0.1866   0.0312   0.0466
   3.750   0.9664   0.02586   0.01898  -0.1856   0.0307   0.0469
   4.000   0.9854   0.02582   0.01892  -0.1844   0.0301   0.0472
   4.250   1.0048   0.02576   0.01883  -0.1833   0.0294   0.0478
   4.500   1.0248   0.02566   0.01868  -0.1821   0.0290   0.0489
   4.750   1.0558   0.02431   0.01705  -0.1824   0.0288   0.0518
   5.000   1.0717   0.02457   0.01731  -0.1805   0.0284   0.0521
   5.250   1.0879   0.02485   0.01758  -0.1787   0.0282   0.0525
   5.500   1.1020   0.02527   0.01799  -0.1765   0.0280   0.0533
   7.750   1.2429   0.02873   0.02078  -0.1586   0.0269   0.0572
   8.000   1.2561   0.02964   0.02171  -0.1564   0.0266   0.0565
   8.250   1.2693   0.03030   0.02237  -0.1543   0.0263   0.0560
   8.500   1.2818   0.03118   0.02326  -0.1521   0.0260   0.0559
   8.750   1.2939   0.03214   0.02423  -0.1499   0.0259   0.0559
   9.000   1.3057   0.03316   0.02527  -0.1478   0.0257   0.0560
   9.250   1.3177   0.03418   0.02632  -0.1456   0.0255   0.0559
   9.500   1.3302   0.03522   0.02738  -0.1436   0.0254   0.0560
   9.750   1.3434   0.03627   0.02844  -0.1417   0.0252   0.0566
  10.000   1.3567   0.03727   0.02947  -0.1398   0.0250   0.0566
  10.250   1.3709   0.03824   0.03047  -0.1381   0.0249   0.0567
  10.500   1.3861   0.03915   0.03140  -0.1365   0.0247   0.0570
  10.750   1.4029   0.04002   0.03230  -0.1350   0.0247   0.0579
  11.000   1.4199   0.04088   0.03318  -0.1336   0.0244   0.0594
  11.250   1.4385   0.04168   0.03400  -0.1324   0.0243   0.0612
  11.500   1.4596   0.04238   0.03471  -0.1315   0.0241   0.0630
  11.750   1.4875   0.04283   0.03514  -0.1313   0.0238   0.0686
  12.000   1.5576   0.04230   0.03574  -0.1372   0.0232   1.0000
  12.250   1.5698   0.04334   0.03684  -0.1352   0.0230   1.0000
  12.500   1.5965   0.04412   0.03765  -0.1349   0.0229   1.0000
  12.750   1.6212   0.04504   0.03864  -0.1343   0.0228   1.0000
  13.000   1.6476   0.04611   0.03977  -0.1340   0.0227   1.0000
  13.250   1.6812   0.04738   0.04113  -0.1345   0.0227   1.0000
  13.500   1.7196   0.04918   0.04305  -0.1358   0.0228   1.0000
  14.250   1.8590   0.06345   0.05782  -0.1451   0.0234   1.0000
  14.500   1.8519   0.06593   0.06048  -0.1406   0.0233   1.0000
  14.750   1.8416   0.06853   0.06327  -0.1359   0.0233   1.0000
  15.000   1.8304   0.07118   0.06610  -0.1313   0.0233   1.0000
  15.250   1.8163   0.07404   0.06915  -0.1268   0.0233   1.0000
  15.500   1.7997   0.07701   0.07231  -0.1223   0.0233   1.0000
  15.750   1.7823   0.08017   0.07566  -0.1181   0.0233   1.0000
  16.000   1.7633   0.08348   0.07916  -0.1142   0.0233   1.0000
  16.250   1.7434   0.08698   0.08284  -0.1106   0.0232   1.0000
  16.500   1.7216   0.09064   0.08669  -0.1074   0.0232   1.0000
  16.750   1.6988   0.09438   0.09062  -0.1045   0.0232   1.0000
  17.000   1.6614   0.09733   0.09396  -0.1005   0.0217   1.0000
  17.250   1.6428   0.10191   0.09871  -0.0993   0.0215   1.0000
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