GOE 802 AIRFOIL (goe802-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 802 AIRFOIL (goe802-il) Reynolds number: 500,000 Max Cl/Cd: 110.36 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe802-il-500000.txt Download as CSV file: xf-goe802-il-500000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.1433 0.08672 0.08442 -0.0605 0.9561 0.0236
-7.750 -0.1412 0.08383 0.08151 -0.0645 0.9409 0.0242
-7.500 -0.1334 0.08018 0.07783 -0.0715 0.9279 0.0243
-7.250 -0.1225 0.07624 0.07386 -0.0746 0.9196 0.0244
-7.000 -0.1126 0.07360 0.07120 -0.0735 0.9124 0.0246
-6.750 -0.1002 0.07107 0.06865 -0.0737 0.9057 0.0247
-6.500 -0.0856 0.06841 0.06597 -0.0754 0.8978 0.0250
-6.250 -0.0694 0.06565 0.06315 -0.0780 0.8911 0.0254
-6.000 -0.0503 0.06265 0.06013 -0.0815 0.8831 0.0259
-5.750 -0.0294 0.05951 0.05691 -0.0853 0.8763 0.0265
-5.500 -0.0044 0.05598 0.05333 -0.0904 0.8688 0.0276
-5.250 0.0432 0.04861 0.04567 -0.1042 0.8616 0.0287
-5.000 0.0598 0.04616 0.04319 -0.1045 0.8547 0.0290
-4.750 0.0804 0.04403 0.04102 -0.1054 0.8473 0.0293
-4.500 0.1037 0.04184 0.03874 -0.1068 0.8399 0.0297
-4.250 0.1296 0.03942 0.03623 -0.1087 0.8310 0.0304
-4.000 0.1578 0.03677 0.03343 -0.1109 0.8227 0.0314
-3.750 0.2009 0.03085 0.02697 -0.1159 0.8148 0.0339
-3.500 0.2237 0.02914 0.02524 -0.1164 0.8068 0.0343
-3.250 0.2487 0.02773 0.02376 -0.1169 0.7981 0.0349
-3.000 0.2756 0.02615 0.02206 -0.1176 0.7897 0.0357
-2.750 0.3043 0.02433 0.02005 -0.1183 0.7809 0.0374
-2.500 0.3366 0.02144 0.01667 -0.1191 0.7720 0.0406
-2.000 0.3905 0.01933 0.01439 -0.1196 0.7515 0.0430
-1.750 0.4214 0.01816 0.01272 -0.1197 0.7413 0.0479
-1.500 0.4480 0.01698 0.01152 -0.1199 0.7299 0.0492
-1.250 0.4755 0.01634 0.01081 -0.1200 0.7168 0.0518
-1.000 0.5044 0.01555 0.00974 -0.1200 0.7035 0.0580
-0.750 0.5318 0.01489 0.00902 -0.1201 0.6899 0.0608
-0.500 0.5607 0.01613 0.01004 -0.1195 0.6753 0.0669
-0.250 0.5873 0.01385 0.00771 -0.1201 0.6615 0.0736
0.000 0.6148 0.01337 0.00711 -0.1201 0.6465 0.0850
0.500 0.6743 0.01149 0.00456 -0.1186 0.6184 0.0452
0.750 0.7019 0.01117 0.00415 -0.1183 0.6045 0.0450
1.000 0.7295 0.01087 0.00379 -0.1181 0.5913 0.0442
1.250 0.7570 0.01064 0.00349 -0.1179 0.5788 0.0432
1.500 0.7843 0.01052 0.00330 -0.1177 0.5666 0.0430
1.750 0.8115 0.01046 0.00318 -0.1176 0.5544 0.0435
2.000 0.8390 0.01041 0.00311 -0.1174 0.5423 0.0443
2.250 0.8664 0.01041 0.00307 -0.1173 0.5312 0.0455
2.500 0.8935 0.01047 0.00308 -0.1171 0.5203 0.0470
2.750 0.9205 0.01051 0.00307 -0.1170 0.5081 0.0507
3.000 0.9475 0.01059 0.00310 -0.1168 0.4949 0.0548
3.250 0.9721 0.00941 0.00343 -0.1169 0.4822 0.7557
3.500 0.9962 0.00917 0.00348 -0.1157 0.4700 1.0000
3.750 1.0224 0.00940 0.00359 -0.1154 0.4581 1.0000
4.000 1.0490 0.00958 0.00371 -0.1152 0.4457 1.0000
4.250 1.0753 0.00978 0.00384 -0.1150 0.4338 1.0000
4.500 1.1013 0.01001 0.00401 -0.1147 0.4229 1.0000
4.750 1.1272 0.01024 0.00417 -0.1144 0.4125 1.0000
5.000 1.1533 0.01045 0.00435 -0.1141 0.4021 1.0000
5.250 1.1787 0.01070 0.00454 -0.1138 0.3916 1.0000
5.500 1.2039 0.01096 0.00475 -0.1134 0.3810 1.0000
5.750 1.2295 0.01119 0.00495 -0.1131 0.3711 1.0000
6.000 1.2543 0.01147 0.00518 -0.1126 0.3617 1.0000
6.250 1.2796 0.01171 0.00542 -0.1123 0.3529 1.0000
6.500 1.3042 0.01198 0.00567 -0.1119 0.3445 1.0000
6.750 1.3287 0.01226 0.00592 -0.1114 0.3354 1.0000
7.000 1.3533 0.01252 0.00620 -0.1110 0.3276 1.0000
7.250 1.3770 0.01284 0.00648 -0.1104 0.3185 1.0000
7.500 1.4011 0.01311 0.00676 -0.1099 0.3085 1.0000
7.750 1.4240 0.01345 0.00707 -0.1092 0.2961 1.0000
8.000 1.4462 0.01382 0.00740 -0.1084 0.2818 1.0000
8.250 1.4680 0.01421 0.00775 -0.1076 0.2669 1.0000
8.500 1.4890 0.01464 0.00813 -0.1067 0.2504 1.0000
8.750 1.5081 0.01518 0.00859 -0.1055 0.2294 1.0000
9.000 1.5247 0.01587 0.00915 -0.1039 0.2050 1.0000
9.500 1.5518 0.01741 0.01047 -0.0997 0.1689 1.0000
9.750 1.5657 0.01806 0.01110 -0.0977 0.1585 1.0000
10.000 1.5796 0.01874 0.01178 -0.0957 0.1494 1.0000
10.250 1.5918 0.01954 0.01254 -0.0936 0.1404 1.0000
10.500 1.6062 0.02022 0.01324 -0.0919 0.1320 1.0000
10.750 1.6190 0.02103 0.01405 -0.0901 0.1239 1.0000
11.000 1.6306 0.02193 0.01494 -0.0882 0.1152 1.0000
11.250 1.6431 0.02280 0.01582 -0.0865 0.1066 1.0000
11.500 1.6530 0.02388 0.01687 -0.0846 0.0960 1.0000
11.750 1.6609 0.02513 0.01808 -0.0826 0.0842 1.0000
12.000 1.6661 0.02663 0.01951 -0.0805 0.0723 1.0000
12.250 1.6706 0.02824 0.02109 -0.0785 0.0636 1.0000
12.500 1.6750 0.02991 0.02276 -0.0766 0.0566 1.0000
12.750 1.6778 0.03178 0.02463 -0.0747 0.0501 1.0000
13.000 1.6807 0.03371 0.02657 -0.0730 0.0422 1.0000
13.250 1.6739 0.03661 0.02938 -0.0710 0.0244 1.0000
13.500 1.6669 0.03966 0.03244 -0.0692 0.0203 1.0000
13.750 1.6648 0.04237 0.03525 -0.0679 0.0189 1.0000
14.000 1.6618 0.04528 0.03827 -0.0668 0.0180 1.0000
14.250 1.6586 0.04833 0.04143 -0.0660 0.0172 1.0000
14.500 1.6570 0.05133 0.04456 -0.0654 0.0167 1.0000
14.750 1.6540 0.05462 0.04798 -0.0650 0.0163 1.0000
15.000 1.6493 0.05822 0.05170 -0.0647 0.0159 1.0000
15.250 1.6428 0.06216 0.05578 -0.0647 0.0156 1.0000
15.500 1.6349 0.06642 0.06017 -0.0649 0.0153 1.0000
15.750 1.6253 0.07102 0.06489 -0.0654 0.0150 1.0000
16.000 1.6136 0.07599 0.06999 -0.0660 0.0148 1.0000
16.250 1.6007 0.08127 0.07540 -0.0669 0.0146 1.0000
16.500 1.5862 0.08690 0.08116 -0.0680 0.0145 1.0000
16.750 1.5708 0.09274 0.08713 -0.0692 0.0143 1.0000
17.000 1.5547 0.09881 0.09333 -0.0707 0.0142 1.0000
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Polar data table (+)
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