GOE 802 AIRFOIL (goe802-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 802 AIRFOIL (goe802-il) Reynolds number: 500,000 Max Cl/Cd: 104.14 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe802-il-500000-n5.txt Download as CSV file: xf-goe802-il-500000-n5.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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.1738 0.09214 0.08957 -0.0528 0.8919 0.0202
-8.250 -0.1680 0.08892 0.08633 -0.0550 0.8828 0.0202
-8.000 -0.1620 0.08570 0.08308 -0.0574 0.8744 0.0203
-7.750 -0.1560 0.08241 0.07976 -0.0601 0.8656 0.0203
-7.500 -0.1470 0.07863 0.07595 -0.0649 0.8577 0.0204
-7.250 -0.1350 0.07596 0.07326 -0.0653 0.8508 0.0205
-7.000 -0.1214 0.07378 0.07105 -0.0660 0.8444 0.0208
-6.750 -0.1061 0.07133 0.06859 -0.0683 0.8370 0.0212
-6.250 -0.0699 0.06532 0.06250 -0.0760 0.8229 0.0227
-6.000 -0.0397 0.05990 0.05696 -0.0864 0.8156 0.0238
-5.750 -0.0115 0.05518 0.05213 -0.0934 0.8086 0.0239
-5.500 0.0183 0.05032 0.04713 -0.0998 0.8013 0.0240
-5.250 0.0395 0.04708 0.04382 -0.1022 0.7945 0.0241
-5.000 0.0606 0.04503 0.04172 -0.1034 0.7865 0.0243
-4.750 0.0843 0.04291 0.03952 -0.1052 0.7786 0.0246
-4.500 0.1103 0.04057 0.03708 -0.1073 0.7688 0.0251
-4.250 0.1381 0.03803 0.03441 -0.1097 0.7576 0.0257
-4.000 0.1807 0.03245 0.02837 -0.1148 0.7472 0.0281
-3.750 0.2097 0.02924 0.02487 -0.1165 0.7352 0.0281
-3.500 0.2376 0.02661 0.02198 -0.1176 0.7240 0.0282
-3.000 0.2877 0.02353 0.01872 -0.1189 0.7001 0.0267
-2.750 0.3172 0.02103 0.01590 -0.1197 0.6878 0.0259
-2.500 0.3464 0.01900 0.01353 -0.1201 0.6755 0.0257
-2.250 0.3749 0.01763 0.01188 -0.1203 0.6621 0.0262
-2.000 0.4036 0.01613 0.01003 -0.1205 0.6482 0.0258
-1.750 0.4321 0.01499 0.00858 -0.1205 0.6338 0.0257
-1.250 0.4884 0.01355 0.00669 -0.1204 0.6068 0.0261
-1.000 0.5164 0.01304 0.00600 -0.1204 0.5934 0.0263
-0.750 0.5442 0.01263 0.00542 -0.1203 0.5802 0.0265
-0.500 0.5719 0.01229 0.00494 -0.1201 0.5675 0.0268
0.000 0.6275 0.01190 0.00432 -0.1199 0.5450 0.0278
0.250 0.6551 0.01168 0.00402 -0.1198 0.5351 0.0280
0.500 0.6827 0.01152 0.00379 -0.1197 0.5246 0.0281
0.750 0.7102 0.01130 0.00353 -0.1196 0.5145 0.0284
1.000 0.7375 0.01112 0.00332 -0.1196 0.5044 0.0288
1.250 0.7651 0.01101 0.00320 -0.1195 0.4947 0.0293
1.500 0.7926 0.01096 0.00313 -0.1194 0.4861 0.0298
1.750 0.8200 0.01093 0.00309 -0.1194 0.4768 0.0305
2.000 0.8475 0.01093 0.00307 -0.1193 0.4682 0.0312
2.250 0.8747 0.01098 0.00309 -0.1192 0.4585 0.0325
2.500 0.9019 0.01103 0.00311 -0.1191 0.4487 0.0332
2.750 0.9287 0.01109 0.00312 -0.1189 0.4365 0.0342
3.000 0.9552 0.01121 0.00318 -0.1187 0.4226 0.0354
3.500 1.0080 0.01149 0.00335 -0.1183 0.3966 0.0390
4.000 1.0558 0.01021 0.00385 -0.1173 0.3752 1.0000
4.250 1.0821 0.01041 0.00399 -0.1170 0.3657 1.0000
4.500 1.1080 0.01064 0.00415 -0.1167 0.3566 1.0000
4.750 1.1336 0.01089 0.00433 -0.1164 0.3467 1.0000
5.000 1.1591 0.01113 0.00453 -0.1161 0.3359 1.0000
5.250 1.1840 0.01142 0.00474 -0.1157 0.3245 1.0000
5.500 1.2089 0.01170 0.00496 -0.1152 0.3142 1.0000
5.750 1.2343 0.01193 0.00518 -0.1149 0.3069 1.0000
6.000 1.2592 0.01219 0.00541 -0.1145 0.2993 1.0000
6.250 1.2842 0.01243 0.00564 -0.1141 0.2923 1.0000
6.500 1.3087 0.01271 0.00590 -0.1137 0.2840 1.0000
6.750 1.3330 0.01298 0.00616 -0.1132 0.2760 1.0000
7.000 1.3565 0.01331 0.00646 -0.1126 0.2663 1.0000
7.250 1.3798 0.01364 0.00676 -0.1120 0.2539 1.0000
7.500 1.4006 0.01413 0.00715 -0.1110 0.2324 1.0000
7.750 1.4183 0.01485 0.00767 -0.1096 0.2001 1.0000
8.000 1.4345 0.01565 0.00828 -0.1080 0.1735 1.0000
8.250 1.4523 0.01628 0.00884 -0.1066 0.1583 1.0000
8.500 1.4701 0.01687 0.00938 -0.1051 0.1476 1.0000
8.750 1.4874 0.01743 0.00991 -0.1036 0.1377 1.0000
9.000 1.5032 0.01796 0.01044 -0.1018 0.1292 1.0000
9.250 1.5176 0.01860 0.01105 -0.0999 0.1208 1.0000
9.500 1.5334 0.01918 0.01163 -0.0982 0.1131 1.0000
9.750 1.5471 0.01990 0.01232 -0.0963 0.1042 1.0000
10.250 1.5680 0.02183 0.01412 -0.0920 0.0761 1.0000
10.500 1.5769 0.02295 0.01518 -0.0899 0.0658 1.0000
10.750 1.5870 0.02401 0.01624 -0.0879 0.0597 1.0000
11.000 1.5967 0.02514 0.01738 -0.0861 0.0547 1.0000
11.250 1.6071 0.02624 0.01852 -0.0844 0.0503 1.0000
11.500 1.6145 0.02761 0.01990 -0.0825 0.0443 1.0000
12.000 1.6126 0.03188 0.02407 -0.0779 0.0174 1.0000
12.250 1.6166 0.03373 0.02599 -0.0762 0.0153 1.0000
12.500 1.6220 0.03552 0.02787 -0.0749 0.0143 1.0000
12.750 1.6258 0.03750 0.02995 -0.0735 0.0135 1.0000
13.000 1.6281 0.03970 0.03225 -0.0722 0.0128 1.0000
13.250 1.6313 0.04187 0.03452 -0.0711 0.0123 1.0000
13.500 1.6348 0.04407 0.03682 -0.0702 0.0119 1.0000
13.750 1.6369 0.04648 0.03933 -0.0694 0.0114 1.0000
14.000 1.6379 0.04911 0.04207 -0.0687 0.0110 1.0000
14.250 1.6376 0.05198 0.04505 -0.0681 0.0107 1.0000
14.500 1.6358 0.05513 0.04831 -0.0678 0.0104 1.0000
14.750 1.6323 0.05857 0.05187 -0.0675 0.0101 1.0000
15.000 1.6268 0.06239 0.05581 -0.0675 0.0098 1.0000
15.250 1.6225 0.06615 0.05969 -0.0676 0.0097 1.0000
15.500 1.6190 0.06989 0.06354 -0.0678 0.0095 1.0000
15.750 1.6140 0.07387 0.06764 -0.0682 0.0093 1.0000
16.000 1.6078 0.07808 0.07198 -0.0687 0.0092 1.0000
16.250 1.6006 0.08254 0.07656 -0.0694 0.0090 1.0000
16.500 1.5926 0.08716 0.08130 -0.0702 0.0089 1.0000
16.750 1.5836 0.09197 0.08622 -0.0712 0.0087 1.0000
17.000 1.5742 0.09693 0.09131 -0.0723 0.0086 1.0000
17.250 1.5643 0.10205 0.09654 -0.0736 0.0085 1.0000
17.500 1.5542 0.10726 0.10187 -0.0750 0.0083 1.0000
17.750 1.5439 0.11254 0.10726 -0.0766 0.0082 1.0000
18.000 1.5335 0.11791 0.11274 -0.0783 0.0081 1.0000
18.250 1.5231 0.12338 0.11833 -0.0802 0.0080 1.0000
18.500 1.5126 0.12895 0.12400 -0.0823 0.0079 1.0000
18.750 1.5016 0.13466 0.12982 -0.0847 0.0078 1.0000
19.000 1.4907 0.14043 0.13569 -0.0871 0.0077 1.0000
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