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K3311 (original) (k3311-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: K3311 (original) (k3311-il)
Reynolds number: 50,000
Max Cl/Cd: 34.73 at α=9.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-k3311-il-50000.txt
Download as CSV file: xf-k3311-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: K3311  (original)                               
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.3688   0.12252   0.11532  -0.0257   1.0000   0.2119
 -10.000  -0.3604   0.11862   0.11146  -0.0256   1.0000   0.2184
  -9.750  -0.3683   0.11746   0.11039  -0.0264   1.0000   0.2278
  -9.500  -0.3517   0.11294   0.10588  -0.0253   1.0000   0.2390
  -9.250  -0.3489   0.10996   0.10296  -0.0251   1.0000   0.2494
  -9.000  -0.3665   0.10967   0.10282  -0.0258   1.0000   0.2588
  -8.750  -0.3502   0.10541   0.09856  -0.0245   1.0000   0.2724
  -8.500  -0.3394   0.10175   0.09495  -0.0235   1.0000   0.2838
  -8.250  -0.3377   0.09904   0.09229  -0.0227   1.0000   0.2950
  -8.000  -0.3420   0.09694   0.09030  -0.0218   1.0000   0.3071
  -7.750  -0.3509   0.09536   0.08886  -0.0205   1.0000   0.3204
  -7.500  -0.3615   0.09417   0.08779  -0.0186   1.0000   0.3342
  -7.250  -0.3596   0.09161   0.08532  -0.0165   1.0000   0.3493
  -7.000  -0.3329   0.08691   0.08060  -0.0149   1.0000   0.3692
  -6.750  -0.3302   0.08471   0.07849  -0.0123   1.0000   0.3904
  -6.500  -0.3427   0.08358   0.07751  -0.0089   1.0000   0.4083
  -6.250  -0.3342   0.08064   0.07463  -0.0064   1.0000   0.4286
  -6.000  -0.3317   0.07843   0.07251  -0.0034   1.0000   0.4468
  -5.750  -0.3391   0.07690   0.07108   0.0005   1.0000   0.4653
  -5.500  -0.3637   0.07668   0.07105   0.0066   1.0000   0.4841
  -4.500  -0.4174   0.04930   0.04248  -0.0352   1.0000   0.1813
  -4.250  -0.3924   0.04403   0.03607  -0.0383   1.0000   0.1544
  -4.000  -0.3741   0.04107   0.03301  -0.0379   1.0000   0.1486
  -3.750  -0.3498   0.03833   0.02931  -0.0383   1.0000   0.1391
  -3.500  -0.3293   0.03619   0.02692  -0.0378   1.0000   0.1366
  -3.250  -0.3082   0.03443   0.02481  -0.0373   1.0000   0.1349
  -3.000  -0.2872   0.03309   0.02308  -0.0367   1.0000   0.1363
  -2.750  -0.2664   0.03203   0.02164  -0.0359   1.0000   0.1384
  -2.500  -0.2456   0.03113   0.02041  -0.0351   1.0000   0.1398
  -2.250  -0.2254   0.03010   0.01933  -0.0343   1.0000   0.1418
  -2.000  -0.2046   0.02935   0.01855  -0.0336   1.0000   0.1455
  -1.750  -0.1853   0.02889   0.01797  -0.0326   1.0000   0.1506
  -1.500  -0.1584   0.02848   0.01754  -0.0330   0.9976   0.1615
  -1.250  -0.1130   0.02820   0.01734  -0.0369   0.9877   0.1917
  -1.000  -0.0640   0.02477   0.01719  -0.0384   0.9807   1.0000
  -0.750  -0.0188   0.02578   0.01746  -0.0426   0.9695   1.0000
  -0.500   0.0216   0.02666   0.01787  -0.0462   0.9576   1.0000
  -0.250   0.0568   0.02746   0.01831  -0.0489   0.9457   1.0000
   0.000   0.0923   0.02830   0.01883  -0.0515   0.9340   1.0000
   0.250   0.1289   0.02917   0.01944  -0.0542   0.9227   1.0000
   0.500   0.1701   0.03007   0.02009  -0.0576   0.9117   1.0000
   0.750   0.1992   0.03083   0.02067  -0.0589   0.8996   1.0000
   1.000   0.2280   0.03162   0.02130  -0.0601   0.8874   1.0000
   1.250   0.2585   0.03244   0.02198  -0.0616   0.8756   1.0000
   1.500   0.2929   0.03327   0.02269  -0.0635   0.8640   1.0000
   1.750   0.3310   0.03406   0.02338  -0.0659   0.8528   1.0000
   2.000   0.3528   0.03491   0.02415  -0.0658   0.8403   1.0000
   2.250   0.3768   0.03579   0.02498  -0.0661   0.8282   1.0000
   2.500   0.4044   0.03668   0.02582  -0.0668   0.8167   1.0000
   2.750   0.4380   0.03749   0.02662  -0.0683   0.8054   1.0000
   3.000   0.4697   0.03829   0.02741  -0.0694   0.7938   1.0000
   3.250   0.4889   0.03931   0.02843  -0.0690   0.7811   1.0000
   3.500   0.5098   0.04036   0.02948  -0.0687   0.7685   1.0000
   3.750   0.5337   0.04137   0.03053  -0.0688   0.7560   1.0000
   4.000   0.5609   0.04229   0.03149  -0.0691   0.7433   1.0000
   4.250   0.5924   0.04306   0.03232  -0.0698   0.7308   1.0000
   4.500   0.6307   0.04354   0.03291  -0.0710   0.7185   1.0000
   4.750   0.6509   0.04458   0.03402  -0.0703   0.7045   1.0000
   5.000   0.6711   0.04566   0.03516  -0.0697   0.6906   1.0000
   5.250   0.6911   0.04678   0.03636  -0.0690   0.6765   1.0000
   5.500   0.7088   0.04806   0.03776  -0.0681   0.6626   1.0000
   5.750   0.7270   0.04934   0.03913  -0.0673   0.6486   1.0000
   6.000   0.7433   0.05077   0.04066  -0.0664   0.6347   1.0000
   6.250   0.7605   0.05214   0.04214  -0.0655   0.6206   1.0000
   6.500   0.7770   0.05358   0.04372  -0.0646   0.6068   1.0000
   6.750   0.7951   0.05491   0.04518  -0.0637   0.5926   1.0000
   7.000   0.8132   0.05622   0.04663  -0.0627   0.5783   1.0000
   7.250   0.8325   0.05739   0.04795  -0.0617   0.5633   1.0000
   7.500   0.8549   0.05819   0.04893  -0.0606   0.5476   1.0000
   7.750   0.8982   0.05685   0.04790  -0.0592   0.5306   1.0000
   8.000   1.0333   0.04677   0.03853  -0.0598   0.5110   1.0000
   8.250   1.0310   0.04889   0.04078  -0.0567   0.4921   1.0000
   8.500   1.1295   0.04228   0.03464  -0.0574   0.4667   1.0000
   8.750   1.1646   0.04004   0.03258  -0.0548   0.4347   1.0000
   9.000   1.1953   0.03486   0.02716  -0.0497   0.3806   1.0000
   9.250   1.1971   0.03447   0.02671  -0.0447   0.3406   1.0000
   9.500   1.1904   0.03495   0.02693  -0.0391   0.2949   1.0000
   9.750   1.1735   0.03645   0.02804  -0.0330   0.2495   1.0000
  10.000   1.1542   0.03889   0.02995  -0.0277   0.2066   1.0000
  10.250   1.1409   0.04198   0.03265  -0.0238   0.1688   1.0000
  10.500   1.1403   0.04486   0.03525  -0.0211   0.1419   1.0000
  10.750   1.1616   0.04761   0.03774  -0.0197   0.1205   1.0000
  11.000   1.1932   0.05059   0.04073  -0.0194   0.1063   1.0000
  11.250   1.2299   0.05415   0.04429  -0.0202   0.0963   1.0000
  11.500   1.2370   0.05761   0.04824  -0.0183   0.0935   1.0000
  11.750   1.2402   0.06126   0.05228  -0.0165   0.0915   1.0000
  12.000   1.2377   0.06490   0.05627  -0.0146   0.0899   1.0000
  12.250   1.2306   0.06867   0.06034  -0.0129   0.0890   1.0000
  12.500   1.2281   0.07246   0.06431  -0.0118   0.0871   1.0000
  12.750   1.2392   0.07745   0.06929  -0.0116   0.0845   1.0000
  13.250   1.1324   0.08939   0.08219  -0.0128   0.0915   1.0000
  13.500   1.0997   0.09696   0.08996  -0.0160   0.0933   1.0000
  13.750   1.0699   0.10516   0.09828  -0.0200   0.0949   1.0000
  14.000   1.0449   0.11373   0.10691  -0.0243   0.0962   1.0000
  14.250   1.0273   0.12204   0.11526  -0.0282   0.0972   1.0000
  14.500   0.9395   0.14955   0.14260  -0.0479   0.1115   1.0000
  14.750   0.9154   0.16276   0.15565  -0.0558   0.1218   1.0000
  15.000   0.9199   0.16847   0.16136  -0.0575   0.1230   1.0000
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