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

GOE 223 (MVA H.34) AIRFOIL (goe223-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 223 (MVA H.34) AIRFOIL (goe223-il)
Reynolds number: 1,000,000
Max Cl/Cd: 108.48 at α=3.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe223-il-1000000.txt
Download as CSV file: xf-goe223-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 223 (MVA H.34) AIRFOIL                      
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -15.500  -0.5806   0.07567   0.07328  -0.0924   0.9580   0.0162
 -15.250  -0.6014   0.06910   0.06656  -0.0963   0.9487   0.0163
 -15.000  -0.6136   0.06427   0.06159  -0.0990   0.9393   0.0164
 -14.750  -0.6220   0.05981   0.05701  -0.1019   0.9294   0.0165
 -14.500  -0.6281   0.05593   0.05301  -0.1044   0.9193   0.0167
 -14.250  -0.6338   0.05237   0.04931  -0.1066   0.9082   0.0168
 -14.000  -0.6369   0.04900   0.04581  -0.1090   0.8962   0.0170
 -13.750  -0.6392   0.04577   0.04243  -0.1113   0.8847   0.0172
 -13.500  -0.6403   0.04267   0.03917  -0.1135   0.8738   0.0174
 -13.250  -0.6391   0.03976   0.03609  -0.1157   0.8635   0.0177
 -13.000  -0.6358   0.03702   0.03319  -0.1180   0.8549   0.0180
 -12.750  -0.6293   0.03457   0.03057  -0.1203   0.8467   0.0183
 -12.500  -0.6194   0.03241   0.02826  -0.1229   0.8395   0.0185
 -12.250  -0.5503   0.01733   0.01324  -0.1203   0.8233   0.0191
 -12.000  -0.5398   0.01593   0.01179  -0.1220   0.8179   0.0193
 -11.750  -0.5282   0.01471   0.01049  -0.1238   0.8126   0.0195
 -11.500  -0.5155   0.01370   0.00942  -0.1260   0.8077   0.0198
 -11.250  -0.4960   0.01272   0.00837  -0.1292   0.8032   0.0201
 -11.000  -0.4740   0.01197   0.00753  -0.1319   0.7985   0.0204
 -10.750  -0.4526   0.01121   0.00665  -0.1333   0.7938   0.0208
 -10.500  -0.4302   0.01042   0.00577  -0.1344   0.7900   0.0213
 -10.250  -0.4070   0.00972   0.00497  -0.1355   0.7860   0.0218
 -10.000  -0.3827   0.00916   0.00429  -0.1364   0.7819   0.0222
  -9.750  -0.3570   0.00892   0.00390  -0.1375   0.7777   0.0225
  -9.500  -0.3494   0.01875   0.01349  -0.1419   0.7798   0.0231
  -9.250  -0.3230   0.01813   0.01284  -0.1425   0.7755   0.0236
  -9.000  -0.2954   0.01759   0.01229  -0.1432   0.7714   0.0241
  -8.750  -0.2680   0.01706   0.01174  -0.1438   0.7670   0.0245
  -8.500  -0.2405   0.01654   0.01117  -0.1443   0.7627   0.0250
  -8.250  -0.2127   0.01604   0.01061  -0.1448   0.7584   0.0255
  -8.000  -0.1844   0.01555   0.01009  -0.1453   0.7541   0.0260
  -7.750  -0.1556   0.01521   0.00969  -0.1459   0.7492   0.0266
  -7.500  -0.1264   0.01503   0.00941  -0.1465   0.7443   0.0269
  -7.250  -0.1002   0.01398   0.00836  -0.1469   0.7394   0.0276
  -7.000  -0.0723   0.01330   0.00768  -0.1476   0.7334   0.0281
  -6.750  -0.0439   0.01285   0.00719  -0.1482   0.7272   0.0286
  -6.500  -0.0146   0.01244   0.00676  -0.1489   0.7209   0.0292
  -6.250   0.0145   0.01210   0.00638  -0.1495   0.7135   0.0299
  -6.000   0.0437   0.01176   0.00600  -0.1501   0.7060   0.0305
  -5.750   0.0729   0.01145   0.00561  -0.1506   0.6958   0.0309
  -5.500   0.1021   0.01117   0.00527  -0.1512   0.6834   0.0314
  -5.250   0.1310   0.01095   0.00497  -0.1516   0.6684   0.0318
  -5.000   0.1597   0.01081   0.00472  -0.1519   0.6501   0.0321
  -4.750   0.1880   0.01046   0.00421  -0.1524   0.6277   0.0330
  -4.500   0.2158   0.01030   0.00390  -0.1527   0.6000   0.0340
  -4.250   0.2435   0.01026   0.00370  -0.1529   0.5757   0.0348
  -4.000   0.2715   0.01022   0.00355  -0.1532   0.5577   0.0355
  -3.750   0.2999   0.01018   0.00341  -0.1534   0.5446   0.0363
  -3.500   0.3285   0.01015   0.00329  -0.1537   0.5343   0.0372
  -3.250   0.3573   0.01011   0.00319  -0.1540   0.5258   0.0380
  -3.000   0.3863   0.01005   0.00307  -0.1543   0.5191   0.0400
  -2.750   0.4150   0.01001   0.00298  -0.1546   0.5131   0.0433
  -2.500   0.4449   0.00971   0.00283  -0.1553   0.5089   0.0942
  -2.250   0.4751   0.00872   0.00247  -0.1569   0.5046   0.3014
  -2.000   0.5040   0.00869   0.00251  -0.1573   0.5004   0.3389
  -1.750   0.5327   0.00876   0.00257  -0.1575   0.4962   0.3548
  -1.500   0.5622   0.00878   0.00259  -0.1578   0.4933   0.3647
  -1.250   0.5913   0.00883   0.00264  -0.1581   0.4894   0.3746
  -1.000   0.6201   0.00890   0.00269  -0.1584   0.4856   0.3820
  -0.750   0.6485   0.00899   0.00276  -0.1586   0.4818   0.3885
  -0.500   0.6773   0.00907   0.00282  -0.1588   0.4785   0.3930
  -0.250   0.7065   0.00910   0.00285  -0.1591   0.4755   0.3977
   0.000   0.7354   0.00915   0.00291  -0.1594   0.4720   0.4037
   0.250   0.7639   0.00923   0.00297  -0.1596   0.4684   0.4083
   0.500   0.7919   0.00936   0.00305  -0.1597   0.4646   0.4121
   0.750   0.8205   0.00939   0.00310  -0.1600   0.4615   0.4173
   1.000   0.8494   0.00943   0.00316  -0.1603   0.4583   0.4212
   1.250   0.8778   0.00950   0.00322  -0.1605   0.4540   0.4251
   1.500   0.9056   0.00961   0.00329  -0.1606   0.4497   0.4281
   1.750   0.9333   0.00971   0.00337  -0.1607   0.4457   0.4307
   2.000   0.9619   0.00973   0.00342  -0.1610   0.4421   0.4346
   2.250   0.9899   0.00980   0.00350  -0.1611   0.4373   0.4380
   2.500   1.0167   0.00994   0.00360  -0.1611   0.4307   0.4413
   2.750   1.0446   0.01002   0.00368  -0.1612   0.4252   0.4446
   3.000   1.0716   0.01015   0.00378  -0.1612   0.4181   0.4475
   3.250   1.0983   0.01026   0.00389  -0.1612   0.4104   0.4521
   3.500   1.1243   0.01042   0.00403  -0.1611   0.4002   0.4561
   3.750   1.1499   0.01060   0.00417  -0.1608   0.3886   0.4600
   4.000   1.1736   0.01088   0.00437  -0.1603   0.3714   0.4636
   4.250   1.1937   0.01134   0.00467  -0.1592   0.3428   0.4678
   4.500   1.1943   0.01281   0.00565  -0.1549   0.2579   0.4717
   4.750   1.2064   0.01343   0.00614  -0.1524   0.2336   0.4762
   5.000   1.2248   0.01385   0.00652  -0.1510   0.2227   0.4808
   5.250   1.2445   0.01427   0.00691  -0.1499   0.2141   0.4858
   5.500   1.2659   0.01460   0.00725  -0.1491   0.2087   0.4916
   5.750   1.2857   0.01501   0.00765  -0.1481   0.2026   0.4974
   6.000   1.3064   0.01538   0.00802  -0.1472   0.1973   0.5035
   6.250   1.3264   0.01578   0.00843  -0.1463   0.1910   0.5107
   6.500   1.3441   0.01631   0.00893  -0.1450   0.1815   0.5179
   6.750   1.3559   0.01716   0.00968  -0.1430   0.1569   0.5263
   7.000   1.3561   0.01871   0.01101  -0.1396   0.1185   0.5338
   7.250   1.3718   0.01940   0.01174  -0.1383   0.1153   0.5441
   7.500   1.3867   0.02016   0.01252  -0.1369   0.1116   0.5549
   7.750   1.4029   0.02086   0.01327  -0.1358   0.1090   0.5680
   8.000   1.4196   0.02154   0.01402  -0.1347   0.1075   0.5828
   8.250   1.4371   0.02219   0.01475  -0.1338   0.1070   0.5990
   8.500   1.4537   0.02291   0.01554  -0.1329   0.1062   0.6162
   8.750   1.4696   0.02369   0.01640  -0.1319   0.1053   0.6336
   9.000   1.4844   0.02456   0.01734  -0.1308   0.1042   0.6508
   9.250   1.4981   0.02552   0.01838  -0.1297   0.1028   0.6672
   9.500   1.5110   0.02656   0.01947  -0.1285   0.1015   0.6834
   9.750   1.5225   0.02772   0.02071  -0.1273   0.0998   0.6999
  10.000   1.5332   0.02897   0.02203  -0.1260   0.0977   0.7189
  10.250   1.5432   0.03029   0.02348  -0.1248   0.0956   0.7478
  10.500   1.5559   0.03079   0.02442  -0.1234   0.0947   1.0000
  10.750   1.5717   0.03170   0.02535  -0.1227   0.0932   1.0000
  11.000   1.5839   0.03292   0.02659  -0.1218   0.0899   1.0000
  11.250   1.5900   0.03468   0.02833  -0.1204   0.0846   1.0000
  11.500   1.5983   0.03630   0.02989  -0.1193   0.0726   1.0000
  11.750   1.5683   0.04144   0.03484  -0.1159   0.0345   1.0000
  12.000   1.5543   0.04539   0.03878  -0.1138   0.0185   1.0000
  12.250   1.5558   0.04792   0.04136  -0.1127   0.0163   1.0000
  12.500   1.5569   0.05056   0.04405  -0.1117   0.0151   1.0000
  12.750   1.5586   0.05321   0.04676  -0.1108   0.0142   1.0000
  13.000   1.5618   0.05573   0.04934  -0.1101   0.0138   1.0000
  13.250   1.5641   0.05839   0.05207  -0.1095   0.0133   1.0000
  13.500   1.5651   0.06122   0.05496  -0.1088   0.0129   1.0000
  13.750   1.5647   0.06426   0.05807  -0.1082   0.0125   1.0000
  14.000   1.5628   0.06752   0.06140  -0.1077   0.0121   1.0000
  14.250   1.5585   0.07113   0.06509  -0.1072   0.0117   1.0000
  14.500   1.5591   0.07414   0.06818  -0.1069   0.0115   1.0000
  14.750   1.5597   0.07716   0.07126  -0.1066   0.0113   1.0000
  15.000   1.5594   0.08032   0.07449  -0.1063   0.0111   1.0000
  15.250   1.5582   0.08363   0.07787  -0.1061   0.0108   1.0000
  15.500   1.5574   0.08687   0.08118  -0.1060   0.0105   1.0000
  15.750   1.5553   0.09032   0.08469  -0.1059   0.0103   1.0000
  16.000   1.5529   0.09378   0.08823  -0.1059   0.0101   1.0000
  16.250   1.5494   0.09744   0.09195  -0.1059   0.0099   1.0000
  16.500   1.5431   0.10154   0.09613  -0.1061   0.0097   1.0000
  16.750   1.5354   0.10585   0.10053  -0.1064   0.0095   1.0000
<< Back to GOE 223 (MVA H.34) AIRFOIL (goe223-il)

Polar data table (+)

Polar graphs


<< Back to GOE 223 (MVA H.34) AIRFOIL (goe223-il)