Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

CAP 21 (TraCFoil) (cap21c-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: CAP 21 (TraCFoil) (cap21c-il)
Reynolds number: 200,000
Max Cl/Cd: 38.36 at α=10°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-cap21c-il-200000.txt
Download as CSV file: xf-cap21c-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: CAP 21   (TraCFoil)                             
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -14.500  -0.6712   0.16933   0.16498   0.0407   1.0005   0.1154
 -14.250  -1.2198   0.05153   0.04624  -0.0351   1.0005   0.1142
 -14.000  -1.2482   0.04528   0.03978  -0.0391   1.0005   0.1158
 -13.000  -1.1972   0.04184   0.03636  -0.0373   1.0005   0.1241
 -12.750  -1.2160   0.03784   0.03191  -0.0368   1.0005   0.1266
 -12.500  -1.2054   0.03616   0.03013  -0.0360   1.0005   0.1290
 -12.250  -1.1753   0.03677   0.03093  -0.0353   1.0005   0.1308
 -12.000  -1.1481   0.03720   0.03146  -0.0345   1.0005   0.1329
 -11.750  -1.1299   0.03658   0.03078  -0.0338   1.0005   0.1355
 -11.500  -1.1238   0.03439   0.02825  -0.0331   1.0005   0.1393
 -11.250  -1.1079   0.03311   0.02683  -0.0324   1.0005   0.1422
 -11.000  -1.0768   0.03392   0.02783  -0.0317   1.0005   0.1440
 -10.750  -1.0487   0.03447   0.02848  -0.0310   1.0005   0.1461
 -10.500  -1.0265   0.03411   0.02809  -0.0303   1.0005   0.1489
 -10.250  -1.0147   0.03218   0.02582  -0.0295   1.0005   0.1529
 -10.000  -0.9967   0.03088   0.02437  -0.0288   1.0005   0.1558
  -9.750  -0.9690   0.03109   0.02472  -0.0282   1.0005   0.1575
  -9.500  -0.9424   0.03126   0.02498  -0.0275   1.0005   0.1595
  -9.250  -0.9179   0.03114   0.02485  -0.0267   1.0005   0.1622
  -9.000  -0.8997   0.03001   0.02348  -0.0259   1.0005   0.1664
  -8.750  -0.8809   0.02882   0.02211  -0.0250   1.0005   0.1698
  -8.500  -0.8542   0.02889   0.02232  -0.0243   1.0005   0.1716
  -8.250  -0.8287   0.02888   0.02239  -0.0235   1.0005   0.1738
  -8.000  -0.8046   0.02863   0.02215  -0.0227   1.0005   0.1764
  -7.750  -0.7847   0.02773   0.02106  -0.0217   1.0005   0.1805
  -7.500  -0.7657   0.02657   0.01969  -0.0206   1.0005   0.1839
  -7.250  -0.7410   0.02629   0.01952  -0.0198   1.0005   0.1859
  -7.000  -0.7169   0.02605   0.01935  -0.0188   1.0005   0.1880
  -6.750  -0.6934   0.02573   0.01906  -0.0178   1.0005   0.1906
  -6.500  -0.6717   0.02512   0.01834  -0.0167   1.0005   0.1943
  -6.250  -0.6514   0.02430   0.01724  -0.0156   1.0005   0.1979
  -6.000  -0.6285   0.02345   0.01650  -0.0147   1.0005   0.1999
  -5.750  -0.6049   0.02304   0.01616  -0.0137   1.0005   0.2020
  -5.500  -0.5815   0.02265   0.01580  -0.0127   1.0005   0.2043
  -5.250  -0.5584   0.02219   0.01533  -0.0117   1.0005   0.2072
  -5.000  -0.5168   0.02165   0.01463  -0.0144   0.9936   0.2116
  -4.750  -0.4410   0.02054   0.01351  -0.0233   0.9094   0.2157
  -4.500  -0.4124   0.02152   0.01294  -0.0220   0.4611   0.2181
  -4.250  -0.3873   0.02159   0.01265  -0.0213   0.4021   0.2207
  -4.000  -0.3607   0.02144   0.01224  -0.0209   0.3787   0.2240
  -3.750  -0.3336   0.02126   0.01179  -0.0205   0.3641   0.2268
  -3.500  -0.3066   0.02083   0.01117  -0.0202   0.3536   0.2291
  -3.250  -0.2793   0.02044   0.01075  -0.0198   0.3447   0.2312
  -3.000  -0.2517   0.02024   0.01049  -0.0195   0.3375   0.2336
  -2.750  -0.2238   0.02007   0.01024  -0.0192   0.3307   0.2362
  -2.500  -0.1959   0.02000   0.01003  -0.0189   0.3246   0.2394
  -2.250  -0.1675   0.01989   0.00979  -0.0186   0.3186   0.2424
  -2.000  -0.1396   0.01957   0.00939  -0.0183   0.3136   0.2449
  -1.750  -0.1117   0.01941   0.00921  -0.0180   0.3093   0.2473
  -1.500  -0.0833   0.01926   0.00910  -0.0177   0.3049   0.2501
  -1.250  -0.0549   0.01921   0.00900  -0.0174   0.3006   0.2535
  -1.000  -0.0265   0.01925   0.00890  -0.0172   0.2969   0.2567
  -0.750   0.0021   0.01926   0.00884  -0.0169   0.2930   0.2592
  -0.500   0.0302   0.01898   0.00867  -0.0166   0.2888   0.2620
  -0.250   0.0585   0.01892   0.00863  -0.0163   0.2850   0.2650
   0.000   0.0869   0.01898   0.00864  -0.0160   0.2818   0.2683
   0.250   0.1153   0.01918   0.00878  -0.0158   0.2788   0.2718
   0.500   0.1439   0.01917   0.00881  -0.0155   0.2756   0.2751
   0.750   0.1718   0.01908   0.00885  -0.0152   0.2719   0.2790
   1.000   0.2000   0.01913   0.00892  -0.0149   0.2683   0.2838
   1.250   0.2284   0.01937   0.00907  -0.0146   0.2653   0.2885
   1.500   0.2563   0.01951   0.00932  -0.0143   0.2626   0.2930
   1.750   0.2843   0.01957   0.00954  -0.0140   0.2595   0.2981
   2.000   0.3125   0.01971   0.00972  -0.0136   0.2562   0.3040
   2.250   0.3402   0.01974   0.00984  -0.0133   0.2529   0.3102
   2.500   0.3682   0.01998   0.01006  -0.0131   0.2500   0.3184
   2.750   0.3957   0.02025   0.01048  -0.0128   0.2471   0.3275
   3.000   0.4234   0.02035   0.01078  -0.0124   0.2434   0.3390
   3.250   0.4512   0.02042   0.01100  -0.0121   0.2399   0.3543
   3.500   0.4790   0.02044   0.01119  -0.0119   0.2370   0.3820
   3.750   0.5061   0.02027   0.01152  -0.0118   0.2345   0.4976
   4.000   0.5106   0.01975   0.01223  -0.0059   0.2326   0.8371
   4.250   0.5366   0.01996   0.01274  -0.0039   0.2294   0.9664
   4.500   0.5935   0.02030   0.01308  -0.0093   0.2246   0.9995
   4.750   0.6171   0.02054   0.01325  -0.0082   0.2218   0.9995
   5.000   0.6412   0.02089   0.01346  -0.0073   0.2194   0.9995
   5.250   0.6636   0.02154   0.01415  -0.0062   0.2165   0.9995
   5.500   0.6858   0.02206   0.01481  -0.0051   0.2130   0.9995
   5.750   0.7096   0.02247   0.01523  -0.0041   0.2099   0.9995
   6.000   0.7345   0.02271   0.01542  -0.0033   0.2072   0.9995
   6.250   0.7604   0.02291   0.01551  -0.0027   0.2048   0.9995
   6.500   0.7842   0.02357   0.01620  -0.0019   0.2019   0.9995
   6.750   0.8064   0.02417   0.01699  -0.0009   0.1980   0.9995
   7.000   0.8310   0.02458   0.01742  -0.0002   0.1949   0.9995
   7.250   0.8568   0.02481   0.01762   0.0004   0.1924   0.9995
   7.500   0.8834   0.02502   0.01772   0.0009   0.1903   0.9995
   7.750   0.9074   0.02584   0.01854   0.0015   0.1878   0.9995
   8.000   0.9275   0.02677   0.01974   0.0025   0.1839   0.9995
   8.250   0.9517   0.02717   0.02022   0.0031   0.1807   0.9995
   8.500   0.9781   0.02718   0.02018   0.0037   0.1781   0.9995
   8.750   1.0057   0.02717   0.02003   0.0041   0.1760   0.9995
   9.000   1.0291   0.02794   0.02081   0.0047   0.1735   0.9995
   9.250   1.0476   0.02893   0.02207   0.0056   0.1696   0.9995
   9.500   1.0707   0.02934   0.02255   0.0063   0.1665   0.9995
   9.750   1.0968   0.02934   0.02249   0.0069   0.1641   0.9995
  10.000   1.1243   0.02931   0.02236   0.0073   0.1622   0.9995
  10.250   1.1464   0.03021   0.02326   0.0079   0.1598   0.9995
  10.500   1.1603   0.03168   0.02505   0.0091   0.1567   0.9995
  10.750   1.1777   0.03272   0.02626   0.0100   0.1538   0.9995
  11.000   1.1999   0.03311   0.02666   0.0107   0.1515   0.9995
  11.250   1.2268   0.03298   0.02642   0.0112   0.1495   0.9995
  11.500   1.2536   0.03315   0.02642   0.0116   0.1474   0.9995
  11.750   1.2619   0.03494   0.02850   0.0129   0.1448   0.9995
  12.000   1.2687   0.03666   0.03052   0.0142   0.1419   0.9995
  12.250   1.2812   0.03774   0.03171   0.0153   0.1395   0.9995
  12.500   1.3005   0.03818   0.03214   0.0161   0.1376   0.9995
  12.750   1.3247   0.03824   0.03210   0.0169   0.1358   0.9995
  13.000   1.3465   0.03890   0.03264   0.0175   0.1339   0.9995
  13.250   1.3344   0.04168   0.03571   0.0195   0.1324   0.9995
  13.500   1.3017   0.04621   0.04061   0.0203   0.1309   0.9995
  13.750   0.7249   0.16405   0.15971  -0.0505   0.1332   0.9995
<< Back to CAP 21 (TraCFoil) (cap21c-il)

Polar data table (+)

Polar graphs


<< Back to CAP 21 (TraCFoil) (cap21c-il)