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GOE 802 AIRFOIL (goe802-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 802 AIRFOIL (goe802-il)
Reynolds number: 200,000
Max Cl/Cd: 79.85 at α=5.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe802-il-200000.txt
Download as CSV file: xf-goe802-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 802 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
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.2616   0.11548   0.11201  -0.0346   1.0000   0.0334
  -9.250  -0.2803   0.11564   0.11226  -0.0318   1.0000   0.0335
  -9.000  -0.2998   0.11576   0.11247  -0.0290   1.0000   0.0336
  -8.500  -0.2799   0.10804   0.10477  -0.0300   0.9970   0.0341
  -8.250  -0.2587   0.10386   0.10058  -0.0327   0.9945   0.0348
  -8.000  -0.2401   0.10023   0.09694  -0.0365   0.9906   0.0358
  -7.750  -0.2214   0.09658   0.09329  -0.0412   0.9861   0.0370
  -7.500  -0.2024   0.09290   0.08960  -0.0470   0.9814   0.0383
  -7.250  -0.1747   0.08894   0.08560  -0.0649   0.9708   0.0396
  -7.000  -0.1569   0.08435   0.08101  -0.0688   0.9646   0.0399
  -6.750  -0.1380   0.08056   0.07723  -0.0678   0.9618   0.0405
  -6.500  -0.1113   0.07682   0.07347  -0.0717   0.9588   0.0415
  -6.250  -0.0794   0.07287   0.06949  -0.0785   0.9561   0.0433
  -6.000  -0.0538   0.06944   0.06600  -0.0859   0.9466   0.0459
  -5.750  -0.0078   0.06367   0.06006  -0.1012   0.9412   0.0475
  -5.500   0.0053   0.06100   0.05742  -0.0999   0.9340   0.0482
  -5.250   0.0281   0.05820   0.05461  -0.1015   0.9282   0.0494
  -5.000   0.0586   0.05502   0.05136  -0.1058   0.9240   0.0515
  -4.750   0.1068   0.05131   0.04718  -0.1173   0.9129   0.0562
  -4.500   0.1225   0.04774   0.04372  -0.1166   0.9084   0.0572
  -4.250   0.1378   0.04587   0.04188  -0.1157   0.8989   0.0587
  -4.000   0.1642   0.04358   0.03952  -0.1171   0.8929   0.0617
  -3.750   0.2033   0.04032   0.03579  -0.1222   0.8837   0.0678
  -3.500   0.2234   0.03791   0.03344  -0.1218   0.8770   0.0693
  -3.250   0.2449   0.03621   0.03171  -0.1216   0.8673   0.0719
  -3.000   0.2818   0.03393   0.02892  -0.1240   0.8601   0.0809
  -2.750   0.3016   0.03183   0.02691  -0.1235   0.8496   0.0831
  -2.500   0.3368   0.03214   0.02666  -0.1239   0.8421   0.0946
  -2.250   0.3557   0.02846   0.02319  -0.1241   0.8315   0.0978
  -2.000   0.3846   0.02742   0.02186  -0.1243   0.8225   0.1118
  -1.750   0.4081   0.02576   0.02028  -0.1240   0.8129   0.1172
  -1.500   0.4351   0.02452   0.01889  -0.1241   0.8022   0.1315
  -1.250   0.4624   0.02339   0.01760  -0.1241   0.7932   0.1480
  -0.250   0.5893   0.01791   0.01045  -0.1223   0.7487   0.0796
   0.000   0.6171   0.01646   0.00889  -0.1220   0.7361   0.0763
   0.250   0.6456   0.01560   0.00777  -0.1215   0.7236   0.0705
   0.500   0.6738   0.01534   0.00730  -0.1208   0.7108   0.0675
   0.750   0.7014   0.01487   0.00672  -0.1203   0.6982   0.0666
   1.000   0.7285   0.01440   0.00621  -0.1199   0.6845   0.0663
   1.250   0.7555   0.01408   0.00585  -0.1194   0.6707   0.0665
   1.500   0.7824   0.01380   0.00554  -0.1190   0.6569   0.0675
   1.750   0.8093   0.01356   0.00530  -0.1188   0.6433   0.0720
   2.000   0.8364   0.01351   0.00517  -0.1184   0.6301   0.0757
   2.250   0.8635   0.01353   0.00507  -0.1180   0.6176   0.0800
   2.500   0.8904   0.01351   0.00503  -0.1177   0.6045   0.0960
   2.750   0.9135   0.01192   0.00518  -0.1167   0.5919   1.0000
   3.000   0.9400   0.01216   0.00525  -0.1162   0.5790   1.0000
   3.250   0.9663   0.01243   0.00535  -0.1158   0.5668   1.0000
   3.500   0.9927   0.01271   0.00547  -0.1155   0.5552   1.0000
   3.750   1.0185   0.01296   0.00566  -0.1151   0.5425   1.0000
   4.000   1.0440   0.01324   0.00584  -0.1146   0.5293   1.0000
   4.250   1.0693   0.01351   0.00602  -0.1141   0.5161   1.0000
   4.500   1.0946   0.01381   0.00622  -0.1136   0.5037   1.0000
   4.750   1.1197   0.01409   0.00642  -0.1131   0.4916   1.0000
   5.000   1.1445   0.01436   0.00667  -0.1126   0.4793   1.0000
   5.250   1.1696   0.01466   0.00693  -0.1122   0.4688   1.0000
   5.500   1.1947   0.01499   0.00718  -0.1117   0.4592   1.0000
   5.750   1.2193   0.01527   0.00750  -0.1112   0.4488   1.0000
   6.000   1.2442   0.01562   0.00778  -0.1107   0.4400   1.0000
   6.250   1.2685   0.01592   0.00812  -0.1102   0.4305   1.0000
   6.500   1.2927   0.01625   0.00845  -0.1097   0.4212   1.0000
   6.750   1.3165   0.01659   0.00874  -0.1090   0.4117   1.0000
   7.000   1.3395   0.01689   0.00912  -0.1083   0.4012   1.0000
   7.250   1.3623   0.01725   0.00945  -0.1075   0.3912   1.0000
   7.500   1.3845   0.01760   0.00979  -0.1067   0.3807   1.0000
   7.750   1.4062   0.01794   0.01020  -0.1058   0.3698   1.0000
   8.000   1.4276   0.01835   0.01062  -0.1048   0.3596   1.0000
   8.250   1.4481   0.01877   0.01103  -0.1037   0.3489   1.0000
   8.500   1.4676   0.01916   0.01149  -0.1025   0.3367   1.0000
   8.750   1.4861   0.01960   0.01197  -0.1011   0.3242   1.0000
   9.000   1.5034   0.02009   0.01249  -0.0995   0.3111   1.0000
   9.250   1.5189   0.02062   0.01303  -0.0977   0.2967   1.0000
   9.500   1.5328   0.02119   0.01361  -0.0957   0.2810   1.0000
   9.750   1.5438   0.02180   0.01424  -0.0932   0.2649   1.0000
  10.000   1.5534   0.02253   0.01498  -0.0905   0.2488   1.0000
  10.250   1.5620   0.02339   0.01582  -0.0879   0.2325   1.0000
  10.500   1.5697   0.02439   0.01679  -0.0854   0.2171   1.0000
  10.750   1.5769   0.02551   0.01788  -0.0830   0.2035   1.0000
  11.000   1.5837   0.02674   0.01909  -0.0807   0.1922   1.0000
  11.250   1.5885   0.02816   0.02047  -0.0784   0.1824   1.0000
  11.500   1.5955   0.02950   0.02187  -0.0764   0.1728   1.0000
  11.750   1.6011   0.03099   0.02339  -0.0744   0.1648   1.0000
  12.000   1.6057   0.03262   0.02504  -0.0725   0.1573   1.0000
  12.250   1.6117   0.03419   0.02669  -0.0709   0.1503   1.0000
  12.500   1.6150   0.03601   0.02854  -0.0692   0.1432   1.0000
  12.750   1.6202   0.03776   0.03039  -0.0678   0.1365   1.0000
  13.000   1.6235   0.03972   0.03241  -0.0665   0.1301   1.0000
  13.250   1.6266   0.04175   0.03452  -0.0652   0.1244   1.0000
  13.500   1.6305   0.04379   0.03666  -0.0642   0.1181   1.0000
  13.750   1.6303   0.04627   0.03919  -0.0632   0.1132   1.0000
  14.000   1.6353   0.04832   0.04140  -0.0624   0.1077   1.0000
  14.250   1.6337   0.05114   0.04426  -0.0618   0.1024   1.0000
  14.500   1.6371   0.05351   0.04678  -0.0613   0.0969   1.0000
  14.750   1.6359   0.05650   0.04984  -0.0609   0.0914   1.0000
  15.000   1.6355   0.05948   0.05292  -0.0607   0.0858   1.0000
  15.250   1.6303   0.06318   0.05667  -0.0607   0.0791   1.0000
  15.500   1.6264   0.06679   0.06038  -0.0609   0.0725   1.0000
  15.750   1.6171   0.07122   0.06485  -0.0612   0.0666   1.0000
  16.000   1.6076   0.07578   0.06948  -0.0618   0.0609   1.0000
  16.250   1.5972   0.08057   0.07436  -0.0625   0.0559   1.0000
  16.500   1.5846   0.08577   0.07964  -0.0635   0.0509   1.0000
  16.750   1.5741   0.09076   0.08473  -0.0645   0.0456   1.0000
  17.000   1.5604   0.09634   0.09039  -0.0658   0.0415   1.0000
  17.250   1.5492   0.10162   0.09577  -0.0672   0.0372   1.0000
  17.500   1.5355   0.10741   0.10164  -0.0689   0.0347   1.0000
  17.750   1.5231   0.11307   0.10741  -0.0708   0.0326   1.0000
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