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FX74_CL5_140 (fx74cl5140-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: FX74_CL5_140 (fx74cl5140-il)
Reynolds number: 100,000
Max Cl/Cd: 46.79 at α=2.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx74cl5140-il-100000-n5.txt
Download as CSV file: xf-fx74cl5140-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX74_CL5_140                                    
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.000   0.2169   0.11496   0.10783  -0.1245   0.6196   0.0296
 -10.750   0.2257   0.11323   0.10604  -0.1262   0.6148   0.0298
 -10.500   0.2323   0.11191   0.10470  -0.1279   0.6107   0.0300
 -10.250   0.2460   0.10831   0.10109  -0.1284   0.6059   0.0303
 -10.000   0.2581   0.10548   0.09822  -0.1290   0.6016   0.0310
  -9.750   0.2689   0.10322   0.09592  -0.1300   0.5982   0.0316
  -9.500   0.2792   0.10107   0.09372  -0.1310   0.5952   0.0326
  -9.250   0.2889   0.09904   0.09169  -0.1319   0.5917   0.0333
  -9.000   0.2979   0.09711   0.08977  -0.1329   0.5885   0.0344
  -8.750   0.3059   0.09552   0.08816  -0.1341   0.5856   0.0352
  -8.500   0.3090   0.09492   0.08757  -0.1358   0.5830   0.0358
  -8.250   0.3200   0.09215   0.08477  -0.1364   0.5804   0.0363
  -8.000   0.3345   0.08911   0.08170  -0.1362   0.5776   0.0379
  -7.750   0.3440   0.08721   0.07982  -0.1367   0.5746   0.0391
  -7.500   0.3529   0.08542   0.07805  -0.1374   0.5719   0.0402
  -7.250   0.3594   0.08399   0.07663  -0.1383   0.5696   0.0421
  -7.000   0.3624   0.08317   0.07584  -0.1395   0.5674   0.0428
  -6.750   0.3601   0.08282   0.07553  -0.1404   0.5656   0.0431
  -6.500   0.3732   0.07979   0.07246  -0.1404   0.5635   0.0436
  -6.250   0.3899   0.07662   0.06928  -0.1398   0.5612   0.0449
  -6.000   0.3973   0.07491   0.06762  -0.1394   0.5587   0.0462
  -5.750   0.4028   0.07350   0.06626  -0.1391   0.5565   0.0475
  -5.500   0.4102   0.07203   0.06482  -0.1399   0.5544   0.0492
  -5.250   0.4191   0.07092   0.06374  -0.1429   0.5526   0.0511
  -5.000   0.4382   0.06989   0.06270  -0.1528   0.5507   0.0519
  -4.750   0.4461   0.06684   0.05965  -0.1490   0.5491   0.0527
  -4.500   0.4583   0.06462   0.05741  -0.1475   0.5475   0.0542
  -4.000   0.4915   0.06083   0.05361  -0.1520   0.5441   0.0591
  -3.750   0.5406   0.05817   0.05083  -0.1691   0.5418   0.0628
  -3.500   0.5455   0.05585   0.04861  -0.1652   0.5397   0.0639
  -3.250   0.5597   0.05399   0.04677  -0.1645   0.5377   0.0659
  -3.000   0.6296   0.05175   0.04409  -0.1822   0.5353   0.0751
  -2.750   0.6416   0.04869   0.04114  -0.1810   0.5336   0.0765
  -2.500   0.6610   0.04676   0.03920  -0.1810   0.5320   0.0791
  -2.250   0.7155   0.04421   0.03631  -0.1911   0.5305   0.0909
  -2.000   0.7375   0.04257   0.03470  -0.1915   0.5290   0.0962
  -1.500   0.8623   0.03522   0.02636  -0.2099   0.5249   0.0443
  -1.250   0.9026   0.03356   0.02447  -0.2135   0.5230   0.0391
  -1.000   0.9497   0.03183   0.02222  -0.2179   0.5212   0.0348
  -0.750   0.9887   0.03075   0.02083  -0.2208   0.5193   0.0333
  -0.500   1.0272   0.02982   0.01951  -0.2231   0.5175   0.0318
  -0.250   1.0634   0.02914   0.01843  -0.2248   0.5158   0.0306
   0.000   1.0968   0.02876   0.01777  -0.2259   0.5143   0.0300
   0.250   1.1289   0.02847   0.01731  -0.2269   0.5130   0.0299
   0.500   1.1542   0.02852   0.01740  -0.2268   0.5110   0.0299
   0.750   1.1806   0.02863   0.01758  -0.2271   0.5091   0.0304
   1.000   1.2077   0.02885   0.01782  -0.2274   0.5071   0.0326
   1.250   1.2354   0.02913   0.01806  -0.2279   0.5051   0.0353
   1.500   1.2646   0.02939   0.01825  -0.2285   0.5031   0.0376
   1.750   1.2938   0.02967   0.01843  -0.2291   0.5013   0.0412
   2.000   1.3245   0.02991   0.01865  -0.2300   0.4996   0.0580
   2.250   1.3548   0.02929   0.01948  -0.2309   0.4982   0.7990
   2.500   1.3611   0.02909   0.01941  -0.2262   0.4969   0.9622
   2.750   1.3867   0.02976   0.01996  -0.2263   0.4951   1.0000
   3.000   1.4043   0.03075   0.02099  -0.2253   0.4924   1.0000
   3.250   1.4239   0.03168   0.02192  -0.2246   0.4901   1.0000
   3.500   1.4450   0.03250   0.02270  -0.2242   0.4879   1.0000
   3.750   1.4679   0.03320   0.02335  -0.2239   0.4858   1.0000
   4.000   1.4924   0.03380   0.02387  -0.2238   0.4840   1.0000
   4.250   1.5182   0.03433   0.02434  -0.2240   0.4825   1.0000
   4.500   1.5448   0.03486   0.02478  -0.2242   0.4811   1.0000
   4.750   1.5723   0.03539   0.02522  -0.2246   0.4800   1.0000
   5.000   1.5763   0.03714   0.02717  -0.2219   0.4773   1.0000
   5.250   1.5742   0.03923   0.02945  -0.2184   0.4741   1.0000
   5.500   1.5782   0.04090   0.03126  -0.2158   0.4713   1.0000
   5.750   1.5903   0.04207   0.03246  -0.2141   0.4690   1.0000
   6.000   1.6092   0.04285   0.03323  -0.2133   0.4672   1.0000
   6.250   1.6325   0.04341   0.03377  -0.2131   0.4658   1.0000
   6.500   1.6590   0.04388   0.03425  -0.2133   0.4646   1.0000
  10.000   1.3371   0.12438   0.11646  -0.1909   0.3750   1.0000
  10.250   1.3114   0.13233   0.12453  -0.1923   0.3651   1.0000
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