GOE 796 AIRFOIL (goe796-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 796 AIRFOIL (goe796-il) Reynolds number: 1,000,000 Max Cl/Cd: 122.7 at α=3.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe796-il-1000000.txt Download as CSV file: xf-goe796-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 796 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.750 -0.6267 0.08376 0.08185 -0.0504 1.0000 0.0186
-12.500 -0.8443 0.03850 0.03596 -0.0870 1.0000 0.0172
-12.250 -0.8665 0.03582 0.03313 -0.0838 0.9983 0.0172
-12.000 -0.8542 0.03237 0.02942 -0.0865 0.9953 0.0172
-11.750 -0.8358 0.02965 0.02647 -0.0887 0.9935 0.0173
-11.500 -0.8170 0.02754 0.02415 -0.0897 0.9902 0.0173
-11.250 -0.7938 0.02575 0.02218 -0.0909 0.9879 0.0174
-11.000 -0.7681 0.02427 0.02054 -0.0922 0.9859 0.0176
-10.750 -0.7413 0.02302 0.01914 -0.0933 0.9839 0.0178
-10.500 -0.7165 0.02201 0.01800 -0.0937 0.9804 0.0180
-10.250 -0.6920 0.02119 0.01707 -0.0937 0.9760 0.0182
-10.000 -0.6670 0.02041 0.01618 -0.0938 0.9723 0.0183
-9.750 -0.6444 0.01965 0.01530 -0.0932 0.9672 0.0184
-9.500 -0.6274 0.01797 0.01341 -0.0920 0.9611 0.0186
-9.250 -0.6067 0.01688 0.01218 -0.0911 0.9560 0.0187
-9.000 -0.5856 0.01593 0.01111 -0.0902 0.9500 0.0188
-8.750 -0.5635 0.01511 0.01018 -0.0893 0.9446 0.0190
-8.500 -0.5403 0.01439 0.00936 -0.0886 0.9389 0.0191
-8.250 -0.5165 0.01376 0.00866 -0.0879 0.9327 0.0193
-8.000 -0.4922 0.01322 0.00802 -0.0873 0.9273 0.0194
-7.750 -0.4669 0.01270 0.00744 -0.0868 0.9208 0.0196
-7.500 -0.4416 0.01224 0.00691 -0.0863 0.9144 0.0197
-7.250 -0.4156 0.01183 0.00642 -0.0860 0.9077 0.0198
-7.000 -0.3895 0.01144 0.00596 -0.0856 0.9003 0.0200
-6.750 -0.3630 0.01108 0.00554 -0.0853 0.8931 0.0201
-6.500 -0.3362 0.01075 0.00515 -0.0851 0.8848 0.0203
-6.250 -0.3093 0.01045 0.00478 -0.0848 0.8761 0.0204
-6.000 -0.2823 0.01018 0.00443 -0.0846 0.8668 0.0206
-5.750 -0.2549 0.00992 0.00412 -0.0844 0.8565 0.0208
-5.500 -0.2275 0.00969 0.00382 -0.0843 0.8461 0.0210
-5.250 -0.2002 0.00949 0.00355 -0.0841 0.8348 0.0212
-5.000 -0.1726 0.00931 0.00329 -0.0839 0.8225 0.0214
-4.750 -0.1449 0.00914 0.00306 -0.0838 0.8098 0.0219
-4.500 -0.1172 0.00900 0.00284 -0.0837 0.7971 0.0224
-4.250 -0.0895 0.00888 0.00265 -0.0836 0.7845 0.0231
-4.000 -0.0618 0.00874 0.00248 -0.0835 0.7733 0.0255
-3.750 -0.0343 0.00851 0.00230 -0.0834 0.7634 0.0401
-3.500 -0.0063 0.00839 0.00218 -0.0834 0.7545 0.0480
-3.250 0.0217 0.00831 0.00207 -0.0834 0.7455 0.0543
-3.000 0.0500 0.00821 0.00196 -0.0834 0.7374 0.0595
-2.750 0.0780 0.00811 0.00187 -0.0834 0.7301 0.0695
-2.500 0.1062 0.00799 0.00183 -0.0835 0.7233 0.0873
-2.250 0.1347 0.00796 0.00179 -0.0836 0.7163 0.0961
-2.000 0.1631 0.00790 0.00174 -0.0837 0.7097 0.1044
-1.750 0.1916 0.00787 0.00169 -0.0838 0.7023 0.1097
-1.500 0.2200 0.00786 0.00165 -0.0838 0.6954 0.1139
-1.250 0.2486 0.00778 0.00160 -0.0840 0.6889 0.1206
-1.000 0.2770 0.00776 0.00156 -0.0840 0.6833 0.1256
-0.750 0.3057 0.00771 0.00153 -0.0842 0.6782 0.1327
-0.500 0.3342 0.00764 0.00150 -0.0843 0.6726 0.1454
-0.250 0.3621 0.00751 0.00148 -0.0844 0.6669 0.1816
0.000 0.3901 0.00732 0.00147 -0.0845 0.6599 0.2423
0.250 0.4175 0.00715 0.00146 -0.0845 0.6516 0.3091
0.500 0.4448 0.00685 0.00147 -0.0845 0.6443 0.4155
0.750 0.4710 0.00646 0.00150 -0.0844 0.6375 0.5639
1.000 0.4960 0.00604 0.00155 -0.0839 0.6314 0.7257
1.250 0.5173 0.00563 0.00163 -0.0822 0.6245 0.8835
1.500 0.5497 0.00563 0.00173 -0.0827 0.6168 0.9725
1.750 0.5899 0.00571 0.00178 -0.0854 0.6070 0.9884
2.000 0.6300 0.00581 0.00182 -0.0881 0.5970 0.9946
2.250 0.6736 0.00592 0.00187 -0.0917 0.5848 0.9994
2.750 0.7272 0.00610 0.00195 -0.0913 0.5591 1.0000
3.000 0.7522 0.00622 0.00201 -0.0907 0.5433 1.0000
3.250 0.7768 0.00636 0.00207 -0.0900 0.5252 1.0000
3.500 0.8012 0.00653 0.00215 -0.0893 0.5033 1.0000
3.750 0.8246 0.00677 0.00227 -0.0885 0.4769 1.0000
4.000 0.8473 0.00706 0.00241 -0.0875 0.4449 1.0000
4.250 0.8697 0.00739 0.00259 -0.0865 0.4131 1.0000
4.500 0.8927 0.00767 0.00276 -0.0856 0.3902 1.0000
4.750 0.9160 0.00796 0.00294 -0.0848 0.3682 1.0000
5.000 0.9393 0.00826 0.00313 -0.0840 0.3473 1.0000
5.250 0.9634 0.00851 0.00331 -0.0833 0.3317 1.0000
5.500 0.9879 0.00874 0.00349 -0.0828 0.3187 1.0000
5.750 1.0125 0.00897 0.00366 -0.0822 0.3070 1.0000
6.000 1.0370 0.00922 0.00385 -0.0817 0.2947 1.0000
6.250 1.0620 0.00942 0.00402 -0.0812 0.2828 1.0000
6.500 1.0867 0.00965 0.00422 -0.0807 0.2697 1.0000
6.750 1.1104 0.00994 0.00443 -0.0801 0.2523 1.0000
7.000 1.1319 0.01039 0.00472 -0.0791 0.2212 1.0000
7.250 1.1498 0.01106 0.00516 -0.0776 0.1813 1.0000
7.500 1.1712 0.01150 0.00552 -0.0766 0.1666 1.0000
7.750 1.1939 0.01182 0.00582 -0.0758 0.1578 1.0000
8.000 1.2157 0.01220 0.00616 -0.0749 0.1487 1.0000
8.250 1.2386 0.01249 0.00644 -0.0741 0.1414 1.0000
8.500 1.2603 0.01285 0.00678 -0.0732 0.1335 1.0000
8.750 1.2819 0.01319 0.00709 -0.0723 0.1241 1.0000
9.000 1.3022 0.01361 0.00746 -0.0711 0.1118 1.0000
9.250 1.3202 0.01412 0.00788 -0.0696 0.0974 1.0000
9.500 1.3364 0.01465 0.00835 -0.0678 0.0852 1.0000
9.750 1.3525 0.01514 0.00881 -0.0659 0.0772 1.0000
10.000 1.3678 0.01569 0.00932 -0.0640 0.0695 1.0000
10.250 1.3833 0.01624 0.00986 -0.0622 0.0628 1.0000
10.500 1.3990 0.01681 0.01042 -0.0604 0.0564 1.0000
10.750 1.4128 0.01750 0.01108 -0.0585 0.0494 1.0000
11.000 1.4271 0.01818 0.01174 -0.0567 0.0426 1.0000
11.250 1.4377 0.01910 0.01260 -0.0545 0.0327 1.0000
11.500 1.4474 0.02012 0.01357 -0.0523 0.0248 1.0000
11.750 1.4585 0.02106 0.01452 -0.0504 0.0212 1.0000
12.000 1.4695 0.02205 0.01553 -0.0485 0.0191 1.0000
12.250 1.4809 0.02304 0.01657 -0.0468 0.0174 1.0000
12.500 1.4927 0.02402 0.01759 -0.0453 0.0163 1.0000
12.750 1.5023 0.02518 0.01880 -0.0436 0.0151 1.0000
13.000 1.5107 0.02650 0.02016 -0.0419 0.0140 1.0000
13.250 1.5226 0.02755 0.02128 -0.0407 0.0134 1.0000
13.500 1.5330 0.02876 0.02255 -0.0394 0.0128 1.0000
13.750 1.5419 0.03013 0.02397 -0.0381 0.0122 1.0000
14.000 1.5490 0.03169 0.02558 -0.0368 0.0116 1.0000
14.250 1.5544 0.03344 0.02739 -0.0355 0.0110 1.0000
14.500 1.5633 0.03493 0.02895 -0.0345 0.0107 1.0000
14.750 1.5708 0.03657 0.03066 -0.0336 0.0102 1.0000
15.000 1.5772 0.03835 0.03250 -0.0327 0.0098 1.0000
15.250 1.5819 0.04033 0.03453 -0.0319 0.0093 1.0000
15.500 1.5840 0.04265 0.03692 -0.0310 0.0089 1.0000
15.750 1.5842 0.04523 0.03959 -0.0303 0.0085 1.0000
16.000 1.5856 0.04774 0.04218 -0.0297 0.0083 1.0000
16.250 1.5859 0.05045 0.04498 -0.0293 0.0080 1.0000
16.500 1.5846 0.05342 0.04804 -0.0290 0.0078 1.0000
16.750 1.5812 0.05672 0.05143 -0.0288 0.0076 1.0000
17.000 1.5758 0.06034 0.05514 -0.0288 0.0074 1.0000
17.250 1.5672 0.06450 0.05940 -0.0291 0.0071 1.0000
17.500 1.5546 0.06936 0.06438 -0.0296 0.0069 1.0000
17.750 1.5388 0.07479 0.06995 -0.0305 0.0068 1.0000
18.000 1.5274 0.07978 0.07506 -0.0316 0.0067 1.0000
18.250 1.5191 0.08444 0.07983 -0.0327 0.0066 1.0000
18.500 1.5091 0.08945 0.08496 -0.0340 0.0065 1.0000
18.750 1.4979 0.09469 0.09031 -0.0356 0.0064 1.0000
19.000 1.4854 0.10027 0.09601 -0.0374 0.0064 1.0000
19.250 1.4721 0.10605 0.10191 -0.0394 0.0063 1.0000
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