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GOE 228 (MVA H.38) AIRFOIL (goe228-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: GOE 228 (MVA H.38) AIRFOIL (goe228-il)
Reynolds number: 50,000
Max Cl/Cd: 5.62 at α=1.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe228-il-50000.txt
Download as CSV file: xf-goe228-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 228 (MVA H.38) AIRFOIL                      
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.2884   0.15315   0.14740  -0.0204   1.0000   0.2168
  -9.750  -0.3055   0.15350   0.14784  -0.0195   1.0000   0.2218
  -9.500  -0.3416   0.15631   0.15079  -0.0188   1.0000   0.2235
  -9.250  -0.3094   0.14921   0.14368  -0.0168   1.0000   0.2279
  -9.000  -0.3112   0.14778   0.14231  -0.0153   1.0000   0.2337
  -8.750  -0.3337   0.14859   0.14322  -0.0143   1.0000   0.2389
  -8.500  -0.3560   0.14863   0.14338  -0.0133   1.0000   0.2408
  -8.250  -0.3282   0.14358   0.13832  -0.0122   0.9991   0.2470
  -8.000  -0.3317   0.14318   0.13793  -0.0175   0.9909   0.2564
  -7.750  -0.2883   0.13671   0.13139  -0.0228   0.9820   0.2624
  -7.500  -0.2789   0.13465   0.12932  -0.0262   0.9719   0.2719
  -7.250  -0.2730   0.13190   0.12659  -0.0292   0.9623   0.2771
  -7.000  -0.2445   0.12851   0.12314  -0.0334   0.9535   0.2891
  -6.750  -0.2896   0.13096   0.12572  -0.0320   0.9419   0.2923
  -6.500  -0.2232   0.12281   0.11744  -0.0364   0.9319   0.3010
  -6.250  -0.2427   0.12314   0.11784  -0.0371   0.9225   0.3094
  -6.000  -0.2555   0.12156   0.11632  -0.0357   0.9111   0.3118
  -5.750  -0.2092   0.11617   0.11082  -0.0396   0.9019   0.3189
  -5.500  -0.2266   0.11576   0.11048  -0.0380   0.8912   0.3262
  -5.250  -0.2527   0.11545   0.11026  -0.0387   0.8806   0.3296
  -5.000  -0.2463   0.07821   0.07225  -0.0973   0.8805   0.1744
  -4.750  -0.1789   0.06830   0.06171  -0.1157   0.8724   0.1729
  -4.500  -0.1252   0.06194   0.05464  -0.1284   0.8618   0.1764
  -4.250  -0.0645   0.05944   0.05176  -0.1363   0.8528   0.1872
  -4.000  -0.0334   0.05785   0.04991  -0.1395   0.8414   0.1956
  -3.750   0.0071   0.05692   0.04876  -0.1431   0.8310   0.2109
  -3.500   0.0488   0.05663   0.04845  -0.1458   0.8211   0.2315
  -3.250   0.0694   0.05703   0.04883  -0.1457   0.8099   0.2511
  -3.000   0.1214   0.05710   0.04884  -0.1490   0.8017   0.2939
  -2.750   0.1258   0.05824   0.05013  -0.1461   0.7896   0.3149
  -2.500   0.1536   0.05907   0.05111  -0.1449   0.7809   0.3577
  -2.250   0.1675   0.06001   0.05212  -0.1426   0.7707   0.3937
  -2.000   0.1855   0.06098   0.05313  -0.1404   0.7617   0.4295
  -1.750   0.2060   0.06184   0.05392  -0.1392   0.7526   0.4625
  -1.500   0.2180   0.06299   0.05509  -0.1364   0.7440   0.4841
  -1.250   0.2322   0.06403   0.05613  -0.1339   0.7355   0.5077
  -1.000   0.2498   0.06520   0.05721  -0.1327   0.7273   0.5365
  -0.750   0.2585   0.06639   0.05842  -0.1301   0.7195   0.5567
  -0.500   0.2866   0.06677   0.05871  -0.1292   0.7129   0.5805
  -0.250   0.2909   0.06847   0.06036  -0.1288   0.7043   0.5931
   0.000   0.3329   0.06835   0.06007  -0.1304   0.6981   0.6138
   0.250   0.3277   0.07076   0.06249  -0.1293   0.6914   0.6226
   0.500   0.3459   0.07196   0.06362  -0.1296   0.6853   0.6362
   0.750   0.3839   0.07236   0.06387  -0.1315   0.6792   0.6542
   1.000   0.3797   0.07514   0.06664  -0.1313   0.6740   0.6625
   1.250   0.3882   0.07712   0.06861  -0.1312   0.6710   0.6726
   1.500   0.4022   0.07918   0.07062  -0.1320   0.6690   0.6843
   1.750   0.4478   0.07965   0.07091  -0.1347   0.6629   0.7028
   2.000   0.4511   0.08258   0.07381  -0.1353   0.6621   0.7136
   2.250   0.4610   0.08501   0.07623  -0.1356   0.6626   0.7259
   2.750   0.3722   0.09841   0.09007  -0.1349   0.7647   0.7237
   3.000   0.3755   0.09911   0.09074  -0.1337   0.7565   0.7359
   3.250   0.4040   0.10124   0.09281  -0.1356   0.7513   0.7565
   3.750   0.4255   0.10439   0.09595  -0.1353   0.7428   0.7957
   4.000   0.4418   0.10575   0.09735  -0.1353   0.7369   0.8258
   4.250   0.4634   0.10731   0.09908  -0.1354   0.7332   0.8847
   4.500   0.4685   0.10849   0.10025  -0.1354   0.7282   1.0000
   4.750   0.4932   0.11082   0.10238  -0.1390   0.7198   1.0000
   5.000   0.5353   0.11486   0.10615  -0.1443   0.7155   1.0000
   5.250   0.5372   0.11635   0.10753  -0.1439   0.7102   1.0000
   5.500   0.5540   0.11840   0.10942  -0.1450   0.7032   1.0000
   5.750   0.5838   0.12171   0.11256  -0.1474   0.6992   1.0000
   6.000   0.6016   0.12474   0.11546  -0.1484   0.6963   1.0000
   6.250   0.6001   0.12527   0.11594  -0.1469   0.6874   1.0000
   6.500   0.6274   0.12837   0.11893  -0.1486   0.6826   1.0000
   6.750   0.6473   0.13166   0.12212  -0.1497   0.6795   1.0000
   7.000   0.6437   0.13198   0.12242  -0.1480   0.6707   1.0000
   7.250   0.6676   0.13493   0.12529  -0.1492   0.6661   1.0000
   7.500   0.6996   0.13946   0.12975  -0.1514   0.6636   1.0000
   7.750   0.6840   0.13874   0.12903  -0.1487   0.6553   1.0000
   8.000   0.7064   0.14153   0.13178  -0.1497   0.6495   1.0000
   8.250   0.7403   0.14644   0.13664  -0.1519   0.6465   1.0000
   8.500   0.7241   0.14544   0.13567  -0.1494   0.6378   1.0000
   8.750   0.7487   0.14856   0.13876  -0.1505   0.6318   1.0000
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