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GOE 217 (MVA MK.12) AIRFOIL (goe217-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 217 (MVA MK.12) AIRFOIL (goe217-il)
Reynolds number: 50,000
Max Cl/Cd: 21.12 at α=3.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe217-il-50000-n5.txt
Download as CSV file: xf-goe217-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 217 (MVA MK.12) 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.1962   0.12572   0.11851  -0.0461   1.0000   0.0817
 -11.000  -0.2010   0.12355   0.11647  -0.0453   1.0000   0.0808
 -10.750  -0.2113   0.12175   0.11481  -0.0438   1.0000   0.0800
 -10.500  -0.2011   0.11686   0.10994  -0.0484   0.9918   0.0794
 -10.250  -0.1890   0.11112   0.10419  -0.0541   0.9804   0.0787
 -10.000  -0.2043   0.10041   0.09344  -0.0631   0.9683   0.0760
  -9.750  -0.1944   0.09447   0.08748  -0.0685   0.9559   0.0754
  -9.500  -0.1924   0.08712   0.08008  -0.0751   0.9437   0.0744
  -9.250  -0.2284   0.07440   0.06712  -0.0866   0.9288   0.0723
  -9.000  -0.2709   0.06317   0.05539  -0.0993   0.9073   0.0707
  -8.750  -0.2669   0.05647   0.04823  -0.1101   0.8919   0.0703
  -8.500  -0.2469   0.05260   0.04403  -0.1161   0.8774   0.0703
  -8.250  -0.2244   0.05000   0.04120  -0.1193   0.8630   0.0705
  -8.000  -0.1937   0.04778   0.03876  -0.1219   0.8526   0.0708
  -7.750  -0.1724   0.04631   0.03715  -0.1222   0.8370   0.0712
  -7.500  -0.1468   0.04497   0.03568  -0.1224   0.8244   0.0718
  -7.250  -0.1214   0.04385   0.03443  -0.1223   0.8119   0.0724
  -7.000  -0.0985   0.04291   0.03338  -0.1219   0.7985   0.0734
  -6.750  -0.0714   0.04187   0.03217  -0.1220   0.7877   0.0749
  -6.500  -0.0490   0.04110   0.03128  -0.1217   0.7742   0.0763
  -6.250  -0.0232   0.04040   0.03058  -0.1209   0.7646   0.0778
  -6.000  -0.0018   0.03985   0.03003  -0.1204   0.7516   0.0793
  -5.750   0.0260   0.03909   0.02916  -0.1206   0.7424   0.0808
  -5.500   0.0498   0.03854   0.02855  -0.1209   0.7303   0.0821
  -5.250   0.0793   0.03775   0.02767  -0.1220   0.7211   0.0837
  -5.000   0.1081   0.03687   0.02678  -0.1241   0.7110   0.0858
  -4.750   0.1402   0.03587   0.02572  -0.1268   0.7014   0.0886
  -4.500   0.1789   0.03453   0.02427  -0.1310   0.6942   0.0931
  -4.250   0.2150   0.03325   0.02305  -0.1359   0.6833   0.1012
  -4.000   0.2629   0.03122   0.02186  -0.1439   0.6752   0.1931
  -3.750   0.2979   0.03111   0.02175  -0.1458   0.6675   0.2511
  -3.500   0.3295   0.03132   0.02190  -0.1471   0.6586   0.2840
  -3.250   0.3590   0.03184   0.02234  -0.1468   0.6520   0.3076
  -3.000   0.3875   0.03253   0.02293  -0.1462   0.6457   0.3294
  -2.750   0.4119   0.03338   0.02376  -0.1454   0.6374   0.3468
  -2.500   0.4402   0.03397   0.02422  -0.1451   0.6309   0.3636
  -2.250   0.4715   0.03443   0.02449  -0.1452   0.6259   0.3811
  -2.000   0.4833   0.03606   0.02626  -0.1406   0.6189   0.3897
  -1.750   0.5068   0.03692   0.02710  -0.1396   0.6127   0.4054
  -1.500   0.5323   0.03745   0.02755  -0.1386   0.6076   0.4168
  -1.250   0.5664   0.03725   0.02716  -0.1400   0.6035   0.4256
  -1.000   0.5885   0.03772   0.02764  -0.1395   0.5972   0.4310
  -0.750   0.6240   0.03760   0.02736  -0.1429   0.5909   0.4435
  -0.500   0.6470   0.03798   0.02772  -0.1416   0.5862   0.4482
   0.000   0.7089   0.03826   0.02776  -0.1435   0.5785   0.4674
   0.250   0.7240   0.03926   0.02888  -0.1420   0.5724   0.4729
   0.500   0.7506   0.03974   0.02931  -0.1427   0.5672   0.4832
   0.750   0.7787   0.04001   0.02952  -0.1429   0.5630   0.4917
   1.000   0.8071   0.04021   0.02965  -0.1427   0.5597   0.5000
   1.250   0.8347   0.04089   0.03027  -0.1439   0.5555   0.5116
   1.500   0.8428   0.04240   0.03195  -0.1418   0.5495   0.5167
   1.750   0.8628   0.04326   0.03284  -0.1413   0.5446   0.5253
   2.000   0.8927   0.04364   0.03314  -0.1421   0.5407   0.5357
   2.250   0.9202   0.04383   0.03331  -0.1416   0.5377   0.5433
   2.500   0.9380   0.04513   0.03463  -0.1414   0.5330   0.5525
   2.750   0.9370   0.04762   0.03729  -0.1397   0.5255   0.5583
   3.000   0.9539   0.04852   0.03824  -0.1385   0.5208   0.5643
   3.250   0.9857   0.04868   0.03833  -0.1391   0.5173   0.5735
   3.500   1.0234   0.04846   0.03802  -0.1402   0.5147   0.5819
   3.750   0.9791   0.05394   0.04382  -0.1353   0.5024   0.5830
   4.000   1.0070   0.05397   0.04383  -0.1350   0.4976   0.5900
   4.250   1.0590   0.05261   0.04229  -0.1371   0.4943   0.6004
   4.750   1.0314   0.05848   0.04840  -0.1310   0.4756   0.6063
   5.000   1.0867   0.05632   0.04612  -0.1323   0.4728   0.6152
   5.500   1.0605   0.06372   0.05369  -0.1291   0.4532   0.6222
   5.750   1.1079   0.06142   0.05132  -0.1287   0.4510   0.6294
   6.250   1.0322   0.07599   0.06621  -0.1277   0.4206   0.6318
   6.500   1.0528   0.07669   0.06689  -0.1274   0.4141   0.6378
   6.750   1.0872   0.07524   0.06540  -0.1264   0.4111   0.6440
   7.000   1.1287   0.07303   0.06314  -0.1255   0.4092   0.6514
   7.500   1.1291   0.07900   0.06920  -0.1250   0.3897   0.6590
   8.000   1.0790   0.09188   0.08228  -0.1257   0.3584   0.6621
   8.250   1.1075   0.09113   0.08151  -0.1249   0.3546   0.6686
   8.750   1.1159   0.09642   0.08685  -0.1247   0.3368   0.6769
   9.250   1.1227   0.10210   0.09258  -0.1247   0.3198   0.6852
   9.750   1.1255   0.10867   0.09921  -0.1253   0.3035   0.6926
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