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GOE 411 AIRFOIL (goe411-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 411 AIRFOIL (goe411-il)
Reynolds number: 100,000
Max Cl/Cd: 34.1 at α=4°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe411-il-100000-n5.txt
Download as CSV file: xf-goe411-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 411 AIRFOIL                                 
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -12.500  -0.6708   0.08631   0.08068  -0.0482   1.0000   0.0163
 -12.250  -0.6878   0.08080   0.07506  -0.0506   1.0000   0.0162
 -12.000  -0.7052   0.07584   0.06997  -0.0524   1.0000   0.0160
 -11.750  -0.7217   0.07155   0.06555  -0.0534   1.0000   0.0160
 -11.500  -0.7383   0.06752   0.06136  -0.0535   1.0000   0.0158
 -11.250  -0.7544   0.06404   0.05772  -0.0527   1.0000   0.0158
 -11.000  -0.7701   0.06098   0.05447  -0.0510   1.0000   0.0157
 -10.750  -0.7837   0.05826   0.05158  -0.0485   1.0000   0.0156
 -10.500  -0.7971   0.05580   0.04894  -0.0453   1.0000   0.0156
 -10.250  -0.8103   0.05344   0.04637  -0.0412   1.0000   0.0155
 -10.000  -0.8220   0.05141   0.04415  -0.0366   1.0000   0.0155
  -9.750  -0.8299   0.04945   0.04199  -0.0322   1.0000   0.0155
  -9.500  -0.8335   0.04718   0.03948  -0.0283   1.0000   0.0154
  -9.250  -0.8340   0.04508   0.03713  -0.0246   1.0000   0.0154
  -9.000  -0.8311   0.04299   0.03478  -0.0211   1.0000   0.0154
  -8.750  -0.8261   0.04125   0.03279  -0.0178   1.0000   0.0156
  -8.500  -0.8216   0.04011   0.03137  -0.0141   1.0000   0.0162
  -8.250  -0.8145   0.03851   0.02953  -0.0109   1.0000   0.0167
  -8.000  -0.7931   0.03517   0.02604  -0.0103   1.0000   0.0174
  -7.750  -0.7733   0.03304   0.02374  -0.0091   1.0000   0.0178
  -7.500  -0.7562   0.03130   0.02196  -0.0074   1.0000   0.0181
  -7.250  -0.7438   0.02988   0.02050  -0.0049   1.0000   0.0185
  -7.000  -0.7359   0.02858   0.01918  -0.0016   1.0000   0.0189
  -6.750  -0.7300   0.02747   0.01802   0.0021   1.0000   0.0194
  -6.500  -0.7251   0.02645   0.01691   0.0059   1.0000   0.0202
  -6.250  -0.7193   0.02551   0.01588   0.0096   1.0000   0.0217
  -6.000  -0.7117   0.02469   0.01493   0.0131   1.0000   0.0229
  -5.750  -0.7031   0.02387   0.01395   0.0165   1.0000   0.0242
  -5.500  -0.6926   0.02315   0.01305   0.0195   1.0000   0.0251
  -5.250  -0.6805   0.02252   0.01224   0.0223   1.0000   0.0260
  -5.000  -0.6688   0.02180   0.01136   0.0252   1.0000   0.0282
  -4.750  -0.6565   0.02111   0.01051   0.0279   1.0000   0.0322
  -4.500  -0.6348   0.02029   0.00970   0.0287   0.9972   0.0434
  -4.250  -0.6152   0.01833   0.00889   0.0287   0.9908   0.2319
  -4.000  -0.5907   0.01729   0.00860   0.0285   0.9844   0.3629
  -3.750  -0.5627   0.01680   0.00850   0.0280   0.9780   0.4580
  -3.500  -0.5371   0.01646   0.00842   0.0283   0.9703   0.5335
  -3.250  -0.5077   0.01624   0.00826   0.0279   0.9632   0.5759
  -3.000  -0.4713   0.01609   0.00805   0.0260   0.9577   0.5969
  -2.750  -0.4396   0.01592   0.00784   0.0251   0.9500   0.6177
  -2.500  -0.4057   0.01575   0.00767   0.0238   0.9429   0.6400
  -2.250  -0.3686   0.01562   0.00755   0.0219   0.9367   0.6645
  -2.000  -0.3359   0.01550   0.00751   0.0211   0.9285   0.6947
  -1.750  -0.2946   0.01543   0.00752   0.0187   0.9233   0.7312
  -1.500  -0.2613   0.01541   0.00755   0.0179   0.9142   0.7633
  -1.250  -0.2151   0.01538   0.00752   0.0144   0.9094   0.7875
  -1.000  -0.1797   0.01537   0.00751   0.0131   0.8994   0.8081
  -0.750  -0.1334   0.01536   0.00748   0.0095   0.8931   0.8249
  -0.500  -0.0900   0.01539   0.00751   0.0065   0.8839   0.8399
  -0.250  -0.0467   0.01540   0.00752   0.0036   0.8742   0.8534
   0.000   0.0001   0.01538   0.00749   0.0000   0.8651   0.8651
   0.250   0.0466   0.01540   0.00752  -0.0036   0.8535   0.8741
   0.500   0.0900   0.01539   0.00751  -0.0065   0.8399   0.8839
   0.750   0.1333   0.01536   0.00748  -0.0095   0.8249   0.8931
   1.000   0.1797   0.01536   0.00750  -0.0130   0.8080   0.8995
   1.250   0.2152   0.01538   0.00752  -0.0144   0.7876   0.9094
   1.500   0.2613   0.01540   0.00755  -0.0179   0.7637   0.9141
   1.750   0.2946   0.01543   0.00752  -0.0187   0.7315   0.9233
   2.000   0.3359   0.01550   0.00749  -0.0211   0.6944   0.9285
   2.250   0.3686   0.01561   0.00755  -0.0219   0.6644   0.9367
   2.500   0.4057   0.01575   0.00767  -0.0238   0.6397   0.9430
   2.750   0.4395   0.01591   0.00784  -0.0251   0.6178   0.9500
   3.000   0.4712   0.01608   0.00805  -0.0260   0.5969   0.9577
   3.250   0.5077   0.01623   0.00826  -0.0279   0.5758   0.9632
   3.500   0.5367   0.01646   0.00842  -0.0282   0.5312   0.9704
   3.750   0.5629   0.01679   0.00850  -0.0280   0.4597   0.9780
   4.000   0.5903   0.01731   0.00859  -0.0284   0.3583   0.9846
   4.250   0.6150   0.01834   0.00889  -0.0287   0.2301   0.9909
   4.500   0.6346   0.02033   0.00972  -0.0287   0.0425   0.9973
   4.750   0.6567   0.02107   0.01046  -0.0279   0.0329   1.0000
   5.000   0.6686   0.02180   0.01136  -0.0252   0.0282   1.0000
   5.250   0.6803   0.02253   0.01226  -0.0223   0.0259   1.0000
   5.500   0.6924   0.02316   0.01306  -0.0195   0.0251   1.0000
   5.750   0.7028   0.02389   0.01397  -0.0164   0.0240   1.0000
   6.000   0.7116   0.02468   0.01491  -0.0131   0.0227   1.0000
   6.250   0.7191   0.02551   0.01588  -0.0096   0.0213   1.0000
   6.500   0.7250   0.02644   0.01690  -0.0059   0.0200   1.0000
   6.750   0.7305   0.02742   0.01797  -0.0022   0.0195   1.0000
   7.000   0.7358   0.02857   0.01917   0.0016   0.0189   1.0000
   7.250   0.7440   0.02979   0.02042   0.0048   0.0186   1.0000
   7.500   0.7561   0.03125   0.02191   0.0074   0.0182   1.0000
   7.750   0.7729   0.03296   0.02366   0.0092   0.0178   1.0000
   8.000   0.7925   0.03502   0.02588   0.0104   0.0175   1.0000
   8.250   0.8129   0.03794   0.02895   0.0113   0.0169   1.0000
   8.500   0.8223   0.04021   0.03147   0.0140   0.0162   1.0000
   8.750   0.8268   0.04134   0.03287   0.0177   0.0157   1.0000
   9.000   0.8318   0.04301   0.03479   0.0210   0.0155   1.0000
   9.250   0.8341   0.04504   0.03708   0.0246   0.0154   1.0000
   9.500   0.8334   0.04718   0.03948   0.0283   0.0154   1.0000
   9.750   0.8302   0.04940   0.04194   0.0322   0.0155   1.0000
  10.000   0.8224   0.05140   0.04413   0.0366   0.0155   1.0000
  10.250   0.8100   0.05350   0.04644   0.0412   0.0155   1.0000
  10.500   0.7973   0.05573   0.04886   0.0452   0.0155   1.0000
  10.750   0.7844   0.05820   0.05151   0.0485   0.0156   1.0000
  11.000   0.7696   0.06107   0.05457   0.0510   0.0157   1.0000
  11.250   0.7549   0.06408   0.05775   0.0526   0.0158   1.0000
  11.500   0.7388   0.06752   0.06137   0.0534   0.0158   1.0000
  11.750   0.7217   0.07158   0.06558   0.0533   0.0159   1.0000
  12.000   0.7067   0.07574   0.06986   0.0523   0.0161   1.0000
  12.250   0.6883   0.08094   0.07519   0.0505   0.0162   1.0000
  13.500   0.6217   0.10940   0.10417   0.0344   0.0171   1.0000
  13.750   0.6049   0.11831   0.11314   0.0288   0.0174   1.0000
  14.000   0.5833   0.13203   0.12687   0.0215   0.0190   1.0000
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