GOE 802 B AIRFOIL (goe802b-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: GOE 802 B AIRFOIL (goe802b-il) Reynolds number: 500,000 Max Cl/Cd: 90.95 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe802b-il-500000-n5.txt Download as CSV file: xf-goe802b-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 802 B 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
------ -------- --------- --------- -------- -------- --------
-9.500 -0.2020 0.09994 0.09754 -0.0475 0.9264 0.0151
-9.250 -0.1959 0.09705 0.09462 -0.0486 0.9145 0.0151
-9.000 -0.1893 0.09411 0.09165 -0.0499 0.9052 0.0153
-8.750 -0.1835 0.09071 0.08823 -0.0519 0.8954 0.0163
-8.500 -0.1737 0.08876 0.08625 -0.0527 0.8876 0.0168
-8.250 -0.1630 0.08655 0.08403 -0.0544 0.8790 0.0190
-8.000 -0.1554 0.08349 0.08093 -0.0571 0.8706 0.0193
-7.750 -0.1422 0.08005 0.07746 -0.0612 0.8630 0.0193
-7.500 -0.1270 0.07650 0.07387 -0.0657 0.8552 0.0194
-7.250 -0.1092 0.07281 0.07013 -0.0707 0.8485 0.0194
-7.000 -0.0874 0.06873 0.06598 -0.0770 0.8413 0.0195
-6.750 -0.0730 0.06576 0.06298 -0.0784 0.8346 0.0198
-6.500 -0.0555 0.06350 0.06069 -0.0801 0.8283 0.0201
-6.250 -0.0347 0.06108 0.05823 -0.0829 0.8212 0.0208
-6.000 -0.0115 0.05826 0.05534 -0.0864 0.8143 0.0219
-5.750 0.0212 0.05444 0.05139 -0.0926 0.8078 0.0233
-5.500 0.0511 0.05091 0.04773 -0.0973 0.8004 0.0234
-5.250 0.0806 0.04756 0.04420 -0.1011 0.7932 0.0235
-5.000 0.1107 0.04434 0.04082 -0.1044 0.7860 0.0236
-4.750 0.1311 0.04135 0.03778 -0.1057 0.7777 0.0238
-4.500 0.1540 0.03932 0.03567 -0.1068 0.7683 0.0241
-4.250 0.1789 0.03744 0.03368 -0.1081 0.7564 0.0245
-4.000 0.2053 0.03558 0.03168 -0.1094 0.7441 0.0252
-3.750 0.2327 0.03372 0.02966 -0.1106 0.7320 0.0263
-3.500 0.2679 0.03182 0.02743 -0.1120 0.7206 0.0281
-3.250 0.2965 0.03007 0.02545 -0.1128 0.7093 0.0283
-3.000 0.3240 0.02835 0.02352 -0.1134 0.6974 0.0283
-2.750 0.3513 0.02664 0.02162 -0.1140 0.6854 0.0283
-2.500 0.3784 0.02503 0.01980 -0.1145 0.6720 0.0283
-2.250 0.4032 0.02320 0.01788 -0.1152 0.6572 0.0275
-2.000 0.4308 0.02187 0.01635 -0.1156 0.6429 0.0271
-1.750 0.4588 0.02069 0.01495 -0.1159 0.6298 0.0270
-1.500 0.4865 0.01965 0.01368 -0.1161 0.6166 0.0269
-1.250 0.5146 0.01867 0.01249 -0.1162 0.6033 0.0275
-1.000 0.5422 0.01777 0.01138 -0.1163 0.5902 0.0275
-0.750 0.5695 0.01696 0.01035 -0.1164 0.5768 0.0271
-0.500 0.5972 0.01612 0.00932 -0.1165 0.5640 0.0270
-0.250 0.6248 0.01527 0.00826 -0.1165 0.5534 0.0271
0.000 0.6523 0.01417 0.00691 -0.1165 0.5429 0.0276
0.250 0.6790 0.01289 0.00534 -0.1166 0.5337 0.0282
0.500 0.7053 0.01221 0.00453 -0.1167 0.5238 0.0288
0.750 0.7323 0.01209 0.00437 -0.1167 0.5146 0.0296
1.000 0.7590 0.01193 0.00416 -0.1167 0.5042 0.0304
1.250 0.7855 0.01174 0.00392 -0.1167 0.4946 0.0308
1.500 0.8121 0.01164 0.00378 -0.1166 0.4843 0.0313
1.750 0.8389 0.01160 0.00371 -0.1166 0.4757 0.0320
2.000 0.8657 0.01159 0.00368 -0.1166 0.4664 0.0328
2.250 0.8923 0.01163 0.00368 -0.1165 0.4578 0.0336
2.500 0.9192 0.01172 0.00377 -0.1164 0.4480 0.0350
2.750 0.9454 0.01184 0.00387 -0.1163 0.4361 0.0368
3.000 0.9711 0.01200 0.00399 -0.1160 0.4212 0.0405
3.250 0.9974 0.01228 0.00428 -0.1158 0.4064 0.0468
3.500 1.0231 0.01246 0.00442 -0.1156 0.3940 0.0603
3.750 1.0484 0.01271 0.00461 -0.1154 0.3828 0.0671
4.000 1.0744 0.01286 0.00475 -0.1152 0.3737 0.0709
4.500 1.1249 0.01331 0.00512 -0.1146 0.3502 0.0799
4.750 1.1498 0.01353 0.00530 -0.1143 0.3378 0.0864
5.000 1.1743 0.01373 0.00547 -0.1140 0.3278 0.0868
5.250 1.1994 0.01385 0.00561 -0.1137 0.3212 0.0869
5.500 1.2244 0.01400 0.00577 -0.1135 0.3141 0.0870
6.000 1.2735 0.01423 0.00605 -0.1129 0.3003 0.0871
6.250 1.2973 0.01441 0.00624 -0.1125 0.2903 0.0873
6.500 1.3213 0.01458 0.00643 -0.1121 0.2811 0.0875
6.750 1.3446 0.01481 0.00666 -0.1116 0.2711 0.0878
7.000 1.3679 0.01504 0.00691 -0.1111 0.2606 0.0881
7.250 1.3898 0.01537 0.00722 -0.1104 0.2470 0.0882
7.500 1.4099 0.01583 0.00759 -0.1094 0.2248 0.0883
7.750 1.4260 0.01657 0.00813 -0.1079 0.1921 0.0884
8.000 1.4419 0.01725 0.00869 -0.1063 0.1675 0.0886
8.250 1.4598 0.01777 0.00919 -0.1050 0.1539 0.0889
8.500 1.4773 0.01829 0.00968 -0.1036 0.1437 0.0891
8.750 1.4941 0.01878 0.01017 -0.1021 0.1345 0.0894
9.000 1.5073 0.01930 0.01069 -0.0999 0.1267 0.0897
9.250 1.5219 0.01986 0.01125 -0.0981 0.1179 0.0898
9.750 1.5500 0.02122 0.01261 -0.0947 0.0987 0.0901
10.000 1.5633 0.02198 0.01335 -0.0929 0.0882 0.0905
10.250 1.5720 0.02306 0.01436 -0.0907 0.0737 0.0912
10.500 1.5812 0.02413 0.01539 -0.0886 0.0651 0.0915
10.750 1.5907 0.02521 0.01648 -0.0867 0.0583 0.0918
11.000 1.6015 0.02622 0.01753 -0.0851 0.0531 0.0922
11.250 1.6090 0.02752 0.01883 -0.0832 0.0476 0.0928
11.500 1.6194 0.02862 0.01999 -0.0817 0.0431 0.0933
11.750 1.6195 0.03059 0.02189 -0.0794 0.0252 0.0935
12.000 1.6156 0.03300 0.02426 -0.0769 0.0170 0.0939
12.250 1.6206 0.03473 0.02608 -0.0754 0.0153 0.0946
12.500 1.6248 0.03659 0.02803 -0.0739 0.0143 0.0955
12.750 1.6279 0.03862 0.03015 -0.0726 0.0133 0.0960
13.000 1.6319 0.04063 0.03226 -0.0714 0.0126 0.0976
13.250 1.6363 0.04265 0.03438 -0.0704 0.0122 0.0994
13.750 1.6411 0.04727 0.03922 -0.0687 0.0112 0.1031
14.000 1.6417 0.04991 0.04197 -0.0680 0.0108 0.1050
14.250 1.6411 0.05278 0.04494 -0.0674 0.0105 0.1083
14.500 1.6391 0.05592 0.04819 -0.0671 0.0102 0.1130
14.750 1.6355 0.05938 0.05176 -0.0668 0.0099 0.1157
15.000 1.6298 0.06320 0.05570 -0.0668 0.0096 0.1176
15.250 1.6238 0.06715 0.05977 -0.0669 0.0094 0.1192
15.500 1.6204 0.07085 0.06359 -0.0672 0.0093 0.1209
15.750 1.6155 0.07482 0.06768 -0.0676 0.0091 0.1223
16.000 1.6095 0.07899 0.07197 -0.0681 0.0090 0.1236
16.250 1.6024 0.08339 0.07650 -0.0688 0.0089 0.1249
16.500 1.5946 0.08797 0.08120 -0.0696 0.0087 0.1271
17.000 1.5767 0.09765 0.09114 -0.0718 0.0085 0.1617
17.250 1.5677 0.10269 0.09645 -0.0732 0.0083 0.3888
17.750 1.5486 0.11224 0.10706 -0.0760 0.0081 1.0000
18.000 1.5384 0.11757 0.11251 -0.0777 0.0080 1.0000
18.250 1.5280 0.12300 0.11804 -0.0796 0.0078 1.0000
|
Polar data table (+)
Polar graphs
<< Back to GOE 802 B AIRFOIL (goe802b-il)