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Fage & Collins 4 (fg4-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: Fage & Collins 4 (fg4-il)
Reynolds number: 500,000
Max Cl/Cd: 58.75 at α=4.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fg4-il-500000-n5.txt
Download as CSV file: xf-fg4-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: Fage & Collins 4                                
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.1843   0.09300   0.09048  -0.0667   0.9691   0.0240
  -9.750  -0.1939   0.09042   0.08794  -0.0649   0.9495   0.0240
  -9.500  -0.1907   0.08657   0.08409  -0.0675   0.9394   0.0241
  -9.250  -0.1815   0.08281   0.08033  -0.0707   0.9333   0.0241
  -9.000  -0.1723   0.07799   0.07549  -0.0763   0.9279   0.0241
  -8.750  -0.1615   0.07341   0.07090  -0.0822   0.9230   0.0241
  -8.500  -0.1448   0.07061   0.06810  -0.0839   0.9199   0.0243
  -8.250  -0.1308   0.06582   0.06325  -0.0906   0.9153   0.0243
  -8.000  -0.1082   0.06252   0.05991  -0.0948   0.9112   0.0246
  -7.750  -0.0821   0.05844   0.05576  -0.1009   0.9067   0.0248
  -7.500  -0.0529   0.05424   0.05145  -0.1077   0.9024   0.0251
  -7.250  -0.0285   0.05048   0.04759  -0.1126   0.8964   0.0255
  -7.000  -0.0044   0.04671   0.04368  -0.1169   0.8891   0.0259
  -6.750   0.0113   0.04075   0.03731  -0.1195   0.8808   0.0279
  -6.500   0.0241   0.03770   0.03405  -0.1188   0.8722   0.0280
  -6.000   0.0297   0.02966   0.02546  -0.1126   0.8542   0.0242
  -5.750   0.0391   0.02781   0.02343  -0.1093   0.8442   0.0241
  -5.500   0.0488   0.02600   0.02141  -0.1061   0.8317   0.0242
  -5.250   0.0565   0.02451   0.01973  -0.1021   0.8146   0.0241
  -5.000   0.0667   0.02315   0.01813  -0.0985   0.7895   0.0241
  -4.750   0.0772   0.02167   0.01636  -0.0951   0.7581   0.0243
  -4.500   0.0904   0.02105   0.01550  -0.0922   0.7236   0.0245
  -4.250   0.1047   0.02081   0.01508  -0.0895   0.6945   0.0248
  -4.000   0.1164   0.01993   0.01395  -0.0860   0.6702   0.0248
  -3.750   0.1259   0.01834   0.01197  -0.0817   0.6502   0.0246
  -3.500   0.1405   0.01759   0.01102  -0.0788   0.6341   0.0247
  -3.250   0.1537   0.01671   0.00987  -0.0754   0.6126   0.0247
  -3.000   0.1694   0.01613   0.00911  -0.0726   0.5953   0.0248
  -2.500   0.2036   0.01522   0.00789  -0.0676   0.5629   0.0251
  -2.250   0.2217   0.01478   0.00730  -0.0653   0.5476   0.0253
  -2.000   0.2411   0.01439   0.00678  -0.0633   0.5356   0.0255
  -1.750   0.2599   0.01409   0.00634  -0.0612   0.5215   0.0258
  -1.500   0.2819   0.01371   0.00588  -0.0598   0.5121   0.0260
  -1.250   0.3018   0.01346   0.00551  -0.0579   0.4985   0.0263
  -1.000   0.3216   0.01324   0.00519  -0.0560   0.4845   0.0266
  -0.750   0.3414   0.01305   0.00490  -0.0541   0.4672   0.0269
  -0.500   0.3597   0.01304   0.00476  -0.0519   0.4452   0.0275
  -0.250   0.3793   0.01294   0.00455  -0.0500   0.4276   0.0278
   0.000   0.3955   0.01296   0.00441  -0.0475   0.3949   0.0279
   0.250   0.4096   0.01313   0.00434  -0.0446   0.3524   0.0280
   0.750   0.4423   0.01321   0.00418  -0.0398   0.2992   0.0286
   1.000   0.4577   0.01337   0.00420  -0.0372   0.2675   0.0289
   1.250   0.4738   0.01356   0.00425  -0.0349   0.2376   0.0296
   1.500   0.4890   0.01382   0.00434  -0.0324   0.2036   0.0298
   2.000   0.5027   0.01522   0.00505  -0.0244   0.0592   0.0308
   2.250   0.5223   0.01533   0.00516  -0.0227   0.0560   0.0313
   2.500   0.5425   0.01542   0.00525  -0.0212   0.0549   0.0320
   2.750   0.5625   0.01555   0.00538  -0.0197   0.0537   0.0327
   3.000   0.5829   0.01566   0.00551  -0.0183   0.0529   0.0344
   3.250   0.6029   0.01584   0.00569  -0.0168   0.0519   0.0354
   3.500   0.6226   0.01604   0.00589  -0.0153   0.0510   0.0367
   3.750   0.6426   0.01623   0.00608  -0.0139   0.0505   0.0384
   4.000   0.6629   0.01642   0.00629  -0.0126   0.0501   0.0409
   4.250   0.6832   0.01662   0.00651  -0.0113   0.0498   0.0455
   4.500   0.9793   0.01667   0.00859  -0.0724   0.0472   1.0000
   4.750   0.9953   0.01702   0.00893  -0.0703   0.0470   1.0000
   5.000   1.0112   0.01737   0.00928  -0.0681   0.0467   1.0000
   5.250   1.0264   0.01778   0.00968  -0.0659   0.0463   1.0000
   5.500   1.0411   0.01821   0.01012  -0.0636   0.0459   1.0000
   5.750   1.0542   0.01872   0.01063  -0.0611   0.0456   1.0000
   6.000   1.0663   0.01929   0.01122  -0.0585   0.0453   1.0000
   6.250   1.0805   0.01975   0.01169  -0.0563   0.0452   1.0000
   6.500   1.0948   0.02022   0.01218  -0.0542   0.0450   1.0000
   6.750   1.1085   0.02073   0.01271  -0.0520   0.0449   1.0000
   7.000   1.1214   0.02129   0.01329  -0.0498   0.0448   1.0000
   7.250   1.1347   0.02185   0.01387  -0.0477   0.0446   1.0000
   7.500   1.1470   0.02247   0.01452  -0.0455   0.0445   1.0000
   7.750   1.1578   0.02319   0.01527  -0.0432   0.0445   1.0000
   8.000   1.1685   0.02394   0.01606  -0.0410   0.0444   1.0000
   8.250   1.1795   0.02470   0.01686  -0.0389   0.0443   1.0000
   8.500   1.1904   0.02551   0.01769  -0.0369   0.0441   1.0000
   8.750   1.2008   0.02636   0.01859  -0.0349   0.0439   1.0000
   9.000   1.2095   0.02735   0.01962  -0.0329   0.0438   1.0000
   9.250   1.2210   0.02819   0.02050  -0.0313   0.0433   1.0000
   9.500   1.2305   0.02919   0.02155  -0.0295   0.0430   1.0000
   9.750   1.2411   0.03016   0.02255  -0.0280   0.0426   1.0000
  10.000   1.2511   0.03119   0.02362  -0.0265   0.0422   1.0000
  10.250   1.2591   0.03241   0.02489  -0.0249   0.0419   1.0000
  10.500   1.2679   0.03361   0.02613  -0.0236   0.0416   1.0000
  10.750   1.2750   0.03501   0.02757  -0.0222   0.0413   1.0000
  11.000   1.2826   0.03642   0.02902  -0.0211   0.0410   1.0000
  11.250   1.2880   0.03807   0.03072  -0.0199   0.0409   1.0000
  11.500   1.2890   0.04020   0.03292  -0.0187   0.0406   1.0000
  11.750   1.2926   0.04218   0.03495  -0.0178   0.0403   1.0000
  12.000   1.3009   0.04377   0.03661  -0.0172   0.0401   1.0000
  12.250   1.3066   0.04566   0.03857  -0.0166   0.0399   1.0000
  12.500   1.3175   0.04708   0.04006  -0.0163   0.0394   1.0000
  12.750   1.3251   0.04886   0.04192  -0.0160   0.0390   1.0000
  13.000   1.3307   0.05090   0.04403  -0.0157   0.0387   1.0000
  13.250   1.3357   0.05305   0.04625  -0.0155   0.0383   1.0000
  13.500   1.3431   0.05497   0.04824  -0.0155   0.0377   1.0000
  13.750   1.3484   0.05714   0.05047  -0.0154   0.0373   1.0000
  14.000   1.3567   0.05900   0.05239  -0.0155   0.0368   1.0000
  14.250   1.3663   0.06075   0.05416  -0.0157   0.0360   1.0000
  14.500   1.3694   0.06327   0.05676  -0.0158   0.0356   1.0000
  14.750   1.3700   0.06610   0.05969  -0.0160   0.0352   1.0000
  15.000   1.3719   0.06880   0.06248  -0.0162   0.0346   1.0000
  15.250   1.3722   0.07175   0.06552  -0.0165   0.0340   1.0000
  15.500   1.3768   0.07418   0.06803  -0.0169   0.0330   1.0000
  15.750   1.3829   0.07642   0.07031  -0.0172   0.0318   1.0000
  16.000   1.3777   0.08018   0.07418  -0.0178   0.0306   1.0000
  16.250   1.3853   0.08228   0.07607  -0.0184   0.0151   1.0000
  16.500   1.3713   0.08738   0.08129  -0.0194   0.0143   1.0000
  16.750   1.3594   0.09227   0.08629  -0.0205   0.0138   1.0000
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