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

GOE 222 (MVA H.33) AIRFOIL (goe222-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 222 (MVA H.33) AIRFOIL (goe222-il)
Reynolds number: 200,000
Max Cl/Cd: 74.88 at α=6.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe222-il-200000.txt
Download as CSV file: xf-goe222-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 222 (MVA H.33) AIRFOIL                      
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -11.500   0.1286   0.09917   0.09542  -0.1334   0.9239   0.1012
 -11.250  -0.1384   0.06967   0.06573  -0.1503   0.9389   0.0639
 -11.000  -0.1822   0.05919   0.05508  -0.1582   0.9253   0.0612
 -10.750  -0.2289   0.05072   0.04636  -0.1655   0.9096   0.0597
 -10.500  -0.2621   0.04373   0.03895  -0.1749   0.8944   0.0585
 -10.250  -0.2527   0.03865   0.03332  -0.1822   0.8900   0.0579
 -10.000  -0.2515   0.03671   0.03113  -0.1817   0.8798   0.0579
  -9.750  -0.2276   0.03439   0.02854  -0.1841   0.8765   0.0586
  -9.500  -0.1986   0.03233   0.02622  -0.1867   0.8743   0.0597
  -9.250  -0.1844   0.03116   0.02486  -0.1861   0.8675   0.0604
  -9.000  -0.1620   0.02980   0.02328  -0.1866   0.8630   0.0610
  -8.750  -0.1327   0.02839   0.02166  -0.1880   0.8605   0.0617
  -8.500  -0.1008   0.02715   0.02021  -0.1896   0.8586   0.0624
  -8.250  -0.0690   0.02575   0.01870  -0.1910   0.8571   0.0637
  -8.000  -0.0583   0.02532   0.01832  -0.1887   0.8500   0.0648
  -7.750  -0.0323   0.02454   0.01755  -0.1889   0.8465   0.0662
  -7.500  -0.0019   0.02373   0.01671  -0.1899   0.8443   0.0676
  -7.250   0.0312   0.02289   0.01583  -0.1912   0.8424   0.0692
  -7.000   0.0669   0.02204   0.01489  -0.1930   0.8407   0.0712
  -6.750   0.0822   0.02178   0.01467  -0.1914   0.8336   0.0731
  -6.500   0.1139   0.02098   0.01388  -0.1928   0.8296   0.0763
  -6.250   0.1511   0.02014   0.01297  -0.1948   0.8268   0.0802
  -6.000   0.1908   0.01917   0.01196  -0.1975   0.8243   0.0861
  -5.750   0.2139   0.01885   0.01164  -0.1972   0.8178   0.0943
  -5.500   0.2472   0.01786   0.01078  -0.1991   0.8133   0.1300
  -5.250   0.2838   0.01698   0.01035  -0.2017   0.8103   0.2554
  -5.000   0.3194   0.01709   0.01037  -0.2029   0.8079   0.2852
  -4.750   0.3446   0.01751   0.01075  -0.2024   0.8036   0.3010
  -4.500   0.3695   0.01786   0.01107  -0.2018   0.7989   0.3130
  -4.250   0.4004   0.01808   0.01114  -0.2023   0.7954   0.3256
  -4.000   0.4328   0.01818   0.01128  -0.2028   0.7927   0.3338
  -3.750   0.4693   0.01818   0.01106  -0.2043   0.7902   0.3443
  -3.500   0.4872   0.01859   0.01162  -0.2025   0.7843   0.3501
  -3.250   0.5157   0.01875   0.01171  -0.2025   0.7798   0.3593
  -3.000   0.5482   0.01873   0.01168  -0.2031   0.7763   0.3675
  -2.750   0.5838   0.01881   0.01167  -0.2043   0.7734   0.3781
  -2.500   0.6031   0.01907   0.01198  -0.2028   0.7674   0.3847
  -2.250   0.6302   0.01916   0.01209  -0.2026   0.7626   0.3913
  -2.000   0.6648   0.01901   0.01177  -0.2039   0.7588   0.3987
  -1.750   0.6997   0.01876   0.01146  -0.2052   0.7554   0.4033
  -1.500   0.7189   0.01889   0.01164  -0.2037   0.7487   0.4067
  -1.250   0.7494   0.01874   0.01142  -0.2042   0.7435   0.4111
  -1.000   0.7863   0.01851   0.01102  -0.2060   0.7394   0.4168
  -0.750   0.8088   0.01852   0.01103  -0.2051   0.7326   0.4205
  -0.500   0.8369   0.01839   0.01091  -0.2051   0.7264   0.4241
  -0.250   0.8723   0.01820   0.01062  -0.2065   0.7218   0.4287
   0.000   0.8947   0.01829   0.01070  -0.2056   0.7145   0.4336
   0.250   0.9237   0.01818   0.01052  -0.2058   0.7079   0.4384
   0.500   0.9591   0.01799   0.01027  -0.2072   0.7029   0.4429
   0.750   0.9773   0.01808   0.01044  -0.2054   0.6939   0.4470
   1.000   1.0093   0.01794   0.01019  -0.2062   0.6874   0.4525
   1.250   1.0335   0.01793   0.01018  -0.2056   0.6792   0.4573
   1.500   1.0601   0.01781   0.01008  -0.2053   0.6710   0.4622
   1.750   1.0850   0.01777   0.01003  -0.2047   0.6621   0.4681
   2.000   1.1109   0.01767   0.00985  -0.2042   0.6526   0.4741
   2.250   1.1320   0.01760   0.00984  -0.2030   0.6420   0.4787
   2.500   1.1596   0.01746   0.00965  -0.2028   0.6331   0.4847
   2.750   1.1774   0.01753   0.00974  -0.2010   0.6209   0.4911
   3.000   1.2003   0.01752   0.00973  -0.2001   0.6106   0.4973
   3.250   1.2238   0.01753   0.00971  -0.1993   0.6005   0.5044
   3.500   1.2438   0.01769   0.00985  -0.1979   0.5895   0.5120
   3.750   1.2678   0.01774   0.00988  -0.1973   0.5802   0.5188
   4.000   1.2884   0.01793   0.01003  -0.1960   0.5700   0.5271
   4.250   1.3106   0.01812   0.01022  -0.1951   0.5610   0.5354
   4.500   1.3336   0.01835   0.01041  -0.1944   0.5530   0.5458
   4.750   1.3576   0.01860   0.01066  -0.1939   0.5459   0.5560
   5.000   1.3779   0.01889   0.01096  -0.1927   0.5385   0.5678
   5.250   1.4072   0.01913   0.01115  -0.1932   0.5320   0.5814
   5.500   1.4221   0.01945   0.01158  -0.1911   0.5247   0.5945
   5.750   1.4475   0.01971   0.01183  -0.1909   0.5180   0.6126
   6.000   1.4687   0.02003   0.01223  -0.1900   0.5116   0.6339
   6.250   1.4882   0.02033   0.01266  -0.1888   0.5054   0.6599
   6.500   1.5164   0.02050   0.01291  -0.1891   0.5002   0.7066
   6.750   1.5290   0.02042   0.01323  -0.1862   0.4956   1.0000
   7.000   1.5471   0.02092   0.01373  -0.1849   0.4902   1.0000
   7.250   1.5708   0.02134   0.01411  -0.1845   0.4851   1.0000
   7.500   1.6008   0.02176   0.01444  -0.1852   0.4803   1.0000
   7.750   1.6124   0.02234   0.01511  -0.1827   0.4751   1.0000
   8.000   1.6307   0.02284   0.01563  -0.1814   0.4699   1.0000
   8.250   1.6605   0.02322   0.01591  -0.1821   0.4646   1.0000
   8.500   1.6695   0.02388   0.01668  -0.1793   0.4591   1.0000
   8.750   1.6824   0.02448   0.01733  -0.1771   0.4533   1.0000
   9.000   1.7075   0.02489   0.01767  -0.1770   0.4477   1.0000
   9.250   1.7174   0.02561   0.01850  -0.1745   0.4422   1.0000
   9.500   1.7269   0.02633   0.01930  -0.1719   0.4362   1.0000
   9.750   1.7492   0.02677   0.01968  -0.1714   0.4302   1.0000
  10.000   1.7529   0.02771   0.02074  -0.1680   0.4238   1.0000
  10.250   1.7596   0.02854   0.02165  -0.1652   0.4168   1.0000
  10.500   1.7762   0.02916   0.02223  -0.1639   0.4099   1.0000
  10.750   1.7724   0.03044   0.02366  -0.1599   0.4021   1.0000
  11.000   1.7882   0.03104   0.02416  -0.1584   0.3941   1.0000
  11.250   1.7767   0.03282   0.02614  -0.1538   0.3850   1.0000
  11.500   1.7829   0.03387   0.02715  -0.1514   0.3759   1.0000
  11.750   1.7743   0.03583   0.02927  -0.1476   0.3656   1.0000
  12.000   1.7732   0.03752   0.03098  -0.1448   0.3553   1.0000
  12.250   1.7719   0.03932   0.03277  -0.1422   0.3446   1.0000
  12.500   1.7676   0.04159   0.03513  -0.1396   0.3329   1.0000
  12.750   1.7664   0.04372   0.03728  -0.1374   0.3219   1.0000
  13.000   1.7660   0.04585   0.03937  -0.1354   0.3118   1.0000
  13.250   1.7654   0.04820   0.04178  -0.1336   0.3013   1.0000
  13.500   1.7662   0.05039   0.04396  -0.1319   0.2926   1.0000
  13.750   1.7665   0.05271   0.04628  -0.1302   0.2840   1.0000
  14.000   1.7687   0.05489   0.04846  -0.1288   0.2767   1.0000
  14.250   1.7705   0.05714   0.05073  -0.1274   0.2697   1.0000
  14.500   1.7748   0.05908   0.05264  -0.1260   0.2638   1.0000
  14.750   1.7762   0.06149   0.05516  -0.1248   0.2576   1.0000
  15.000   1.7791   0.06362   0.05725  -0.1235   0.2515   1.0000
  15.250   1.7808   0.06600   0.05969  -0.1224   0.2458   1.0000
  15.500   1.7813   0.06857   0.06234  -0.1213   0.2401   1.0000
  15.750   1.7859   0.07049   0.06418  -0.1202   0.2342   1.0000
  16.000   1.7823   0.07368   0.06755  -0.1193   0.2288   1.0000
  16.250   1.7801   0.07664   0.07058  -0.1184   0.2231   1.0000
  16.500   1.7840   0.07872   0.07260  -0.1175   0.2177   1.0000
  16.750   1.7785   0.08232   0.07641  -0.1170   0.2128   1.0000
  17.000   1.7753   0.08557   0.07975  -0.1164   0.2075   1.0000
  17.250   1.7757   0.08821   0.08236  -0.1158   0.2021   1.0000
  17.500   1.7677   0.09234   0.08672  -0.1157   0.1970   1.0000
  17.750   1.7612   0.09618   0.09065  -0.1156   0.1910   1.0000
  18.000   1.7539   0.10019   0.09475  -0.1157   0.1849   1.0000
  18.250   1.7431   0.10492   0.09963  -0.1161   0.1775   1.0000
  18.500   1.7314   0.10977   0.10459  -0.1167   0.1693   1.0000
  18.750   1.7157   0.11533   0.11021  -0.1177   0.1591   1.0000
  19.000   1.6966   0.12152   0.11648  -0.1190   0.1436   1.0000
  19.250   1.6718   0.12853   0.12345  -0.1208   0.1234   1.0000
<< Back to GOE 222 (MVA H.33) AIRFOIL (goe222-il)

Polar data table (+)

Polar graphs


<< Back to GOE 222 (MVA H.33) AIRFOIL (goe222-il)