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GOE 173 (ALBATROS 6020) AIRFOIL (goe173-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 173 (ALBATROS 6020) AIRFOIL (goe173-il)
Reynolds number: 200,000
Max Cl/Cd: 75.71 at α=2.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe173-il-200000-n5.txt
Download as CSV file: xf-goe173-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 173 (ALBATROS 6020) 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.2478   0.10291   0.09963  -0.0280   1.0000   0.0185
  -8.000  -0.2475   0.10100   0.09778  -0.0279   1.0000   0.0187
  -7.750  -0.2500   0.09934   0.09620  -0.0273   1.0000   0.0189
  -7.500  -0.2425   0.09681   0.09372  -0.0301   0.9960   0.0190
  -7.250  -0.2195   0.09284   0.08975  -0.0376   0.9863   0.0191
  -7.000  -0.1956   0.08874   0.08564  -0.0450   0.9751   0.0192
  -6.750  -0.1716   0.08455   0.08145  -0.0515   0.9620   0.0192
  -6.500  -0.1463   0.08026   0.07714  -0.0578   0.9476   0.0193
  -6.250  -0.1189   0.07581   0.07265  -0.0641   0.9323   0.0193
  -6.000  -0.0887   0.07119   0.06798  -0.0709   0.9166   0.0193
  -5.500  -0.0351   0.06152   0.05817  -0.0809   0.8835   0.0200
  -5.250  -0.0148   0.05874   0.05532  -0.0820   0.8661   0.0215
  -4.750   0.0617   0.04928   0.04546  -0.0973   0.8315   0.0190
  -4.500   0.0862   0.04591   0.04194  -0.0999   0.8154   0.0183
  -4.250   0.1176   0.04215   0.03796  -0.1040   0.8002   0.0180
  -4.000   0.1576   0.03739   0.03286  -0.1093   0.7868   0.0189
  -3.750   0.1811   0.03580   0.03114  -0.1105   0.7727   0.0215
  -3.500   0.2160   0.03183   0.02684  -0.1136   0.7607   0.0212
  -3.250   0.2486   0.02858   0.02323  -0.1156   0.7495   0.0216
  -3.000   0.2800   0.02599   0.02030  -0.1169   0.7383   0.0238
  -2.750   0.3140   0.02260   0.01634  -0.1180   0.7276   0.0259
  -2.500   0.3454   0.01993   0.01305  -0.1187   0.7172   0.0280
  -2.250   0.3716   0.01927   0.01229  -0.1189   0.7052   0.0309
  -2.000   0.4007   0.01780   0.01039  -0.1189   0.6932   0.0325
  -1.750   0.4292   0.01681   0.00902  -0.1188   0.6811   0.0349
  -1.500   0.4574   0.01627   0.00814  -0.1185   0.6699   0.0366
  -1.250   0.4853   0.01527   0.00686  -0.1184   0.6596   0.0373
  -1.000   0.5127   0.01447   0.00589  -0.1182   0.6490   0.0383
  -0.750   0.5398   0.01402   0.00538  -0.1181   0.6377   0.0409
  -0.500   0.5670   0.01363   0.00487  -0.1178   0.6268   0.0417
  -0.250   0.5942   0.01329   0.00444  -0.1176   0.6160   0.0419
   0.000   0.6212   0.01302   0.00410  -0.1173   0.6043   0.0424
   0.250   0.6482   0.01282   0.00382  -0.1171   0.5916   0.0432
   0.500   0.6751   0.01269   0.00361  -0.1168   0.5782   0.0443
   0.750   0.7019   0.01262   0.00345  -0.1166   0.5642   0.0457
   1.000   0.7286   0.01261   0.00333  -0.1163   0.5497   0.0474
   1.250   0.7552   0.01261   0.00325  -0.1160   0.5348   0.0508
   1.500   0.7816   0.01264   0.00324  -0.1157   0.5187   0.0596
   1.750   0.8078   0.01267   0.00326  -0.1154   0.5014   0.0876
   2.250   0.8534   0.01134   0.00348  -0.1134   0.4618   1.0000
   2.500   0.8785   0.01161   0.00357  -0.1129   0.4376   1.0000
   2.750   0.9032   0.01193   0.00369  -0.1124   0.4122   1.0000
   3.000   0.9279   0.01227   0.00385  -0.1118   0.3897   1.0000
   3.250   0.9524   0.01261   0.00406  -0.1113   0.3722   1.0000
   3.500   0.9773   0.01295   0.00428  -0.1109   0.3591   1.0000
   3.750   1.0022   0.01328   0.00452  -0.1104   0.3488   1.0000
   4.250   1.0520   0.01393   0.00508  -0.1096   0.3327   1.0000
   4.500   1.0767   0.01428   0.00538  -0.1091   0.3264   1.0000
   4.750   1.1018   0.01459   0.00570  -0.1087   0.3209   1.0000
   5.000   1.1267   0.01492   0.00604  -0.1083   0.3157   1.0000
   5.250   1.1511   0.01530   0.00640  -0.1079   0.3113   1.0000
   5.500   1.1760   0.01562   0.00676  -0.1075   0.3071   1.0000
   5.750   1.2009   0.01595   0.00716  -0.1071   0.3027   1.0000
   6.000   1.2252   0.01632   0.00757  -0.1066   0.2988   1.0000
   6.250   1.2492   0.01673   0.00799  -0.1061   0.2946   1.0000
   6.500   1.2733   0.01701   0.00836  -0.1056   0.2858   1.0000
   6.750   1.2965   0.01736   0.00876  -0.1050   0.2765   1.0000
   7.000   1.3190   0.01773   0.00915  -0.1043   0.2664   1.0000
   7.250   1.3422   0.01802   0.00952  -0.1037   0.2541   1.0000
   7.500   1.3635   0.01841   0.00989  -0.1028   0.2352   1.0000
   7.750   1.3835   0.01893   0.01031  -0.1018   0.2001   1.0000
   8.000   1.3799   0.02175   0.01216  -0.0980   0.0692   1.0000
   8.250   1.3840   0.02380   0.01390  -0.0948   0.0195   1.0000
   8.500   1.3996   0.02468   0.01493  -0.0931   0.0160   1.0000
   8.750   1.4132   0.02565   0.01610  -0.0911   0.0142   1.0000
   9.000   1.4229   0.02672   0.01736  -0.0886   0.0131   1.0000
   9.250   1.4295   0.02800   0.01883  -0.0857   0.0122   1.0000
   9.500   1.4315   0.02965   0.02069  -0.0826   0.0113   1.0000
   9.750   1.4316   0.03150   0.02274  -0.0796   0.0106   1.0000
  10.000   1.4364   0.03307   0.02452  -0.0775   0.0100   1.0000
  10.250   1.4371   0.03511   0.02673  -0.0754   0.0097   1.0000
  10.500   1.4357   0.03752   0.02931  -0.0736   0.0094   1.0000
  10.750   1.4327   0.04030   0.03226  -0.0723   0.0091   1.0000
  11.000   1.4284   0.04342   0.03554  -0.0713   0.0089   1.0000
  11.250   1.4231   0.04684   0.03911  -0.0707   0.0087   1.0000
  11.500   1.4167   0.05051   0.04293  -0.0703   0.0085   1.0000
  11.750   1.4097   0.05440   0.04696  -0.0701   0.0084   1.0000
  12.000   1.4024   0.05841   0.05110  -0.0701   0.0083   1.0000
  12.250   1.3951   0.06248   0.05529  -0.0701   0.0081   1.0000
  12.500   1.3881   0.06659   0.05951  -0.0703   0.0080   1.0000
  12.750   1.3810   0.07072   0.06374  -0.0705   0.0078   1.0000
  13.000   1.3742   0.07483   0.06793  -0.0707   0.0076   1.0000
  13.250   1.3678   0.07878   0.07192  -0.0706   0.0073   1.0000
  13.500   1.3643   0.08218   0.07536  -0.0701   0.0070   1.0000
  13.750   1.3638   0.08581   0.07915  -0.0706   0.0068   1.0000
  14.000   1.3638   0.08918   0.08265  -0.0707   0.0066   1.0000
  14.250   1.3644   0.09236   0.08599  -0.0705   0.0065   1.0000
  14.500   1.3652   0.09553   0.08928  -0.0704   0.0064   1.0000
  14.750   1.3659   0.09876   0.09265  -0.0703   0.0062   1.0000
  15.000   1.3659   0.10220   0.09624  -0.0704   0.0061   1.0000
  15.250   1.3652   0.10586   0.10005  -0.0708   0.0061   1.0000
  15.500   1.3630   0.10990   0.10425  -0.0715   0.0060   1.0000
  15.750   1.3599   0.11419   0.10871  -0.0726   0.0059   1.0000
  16.000   1.3556   0.11880   0.11350  -0.0741   0.0059   1.0000
  16.250   1.3505   0.12372   0.11860  -0.0759   0.0059   1.0000
  16.500   1.3446   0.12894   0.12401  -0.0782   0.0058   1.0000
  16.750   1.3379   0.13450   0.12975  -0.0808   0.0058   1.0000
  17.000   1.3306   0.14033   0.13577  -0.0839   0.0058   1.0000
  17.250   1.3225   0.14650   0.14212  -0.0873   0.0058   1.0000
  17.500   1.3140   0.15298   0.14878  -0.0911   0.0058   1.0000
  17.750   1.3053   0.15973   0.15571  -0.0953   0.0059   1.0000
  18.000   1.2962   0.16683   0.16297  -0.0999   0.0059   1.0000
  18.250   1.2870   0.17425   0.17055  -0.1048   0.0059   1.0000
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