GOE 795 smoothed (goe795sm-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 795 smoothed (goe795sm-il) Reynolds number: 200,000 Max Cl/Cd: 69.68 at α=3.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe795sm-il-200000-n5.txt Download as CSV file: xf-goe795sm-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 795 smoothed
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
------ -------- --------- --------- -------- -------- --------
-8.750 -0.4667 0.08479 0.08119 -0.0302 1.0000 0.0161
-8.500 -0.4733 0.08076 0.07722 -0.0314 1.0000 0.0159
-8.250 -0.4831 0.07702 0.07356 -0.0323 1.0000 0.0157
-8.000 -0.4966 0.07293 0.06955 -0.0334 1.0000 0.0156
-7.750 -0.5049 0.06793 0.06458 -0.0358 1.0000 0.0153
-7.500 -0.5128 0.06232 0.05895 -0.0380 1.0000 0.0152
-7.250 -0.5198 0.05609 0.05264 -0.0396 1.0000 0.0150
-7.000 -0.5277 0.04865 0.04501 -0.0403 1.0000 0.0148
-6.750 -0.5389 0.03953 0.03543 -0.0392 1.0000 0.0146
-6.500 -0.5288 0.03153 0.02666 -0.0401 0.9966 0.0149
-6.250 -0.5056 0.02672 0.02111 -0.0412 0.9921 0.0156
-6.000 -0.4795 0.02359 0.01738 -0.0417 0.9876 0.0167
-5.750 -0.4494 0.02165 0.01493 -0.0426 0.9841 0.0180
-5.500 -0.4218 0.02005 0.01307 -0.0432 0.9797 0.0198
-5.250 -0.3923 0.01891 0.01174 -0.0437 0.9752 0.0211
-5.000 -0.3605 0.01781 0.01043 -0.0447 0.9717 0.0230
-4.750 -0.3312 0.01679 0.00920 -0.0450 0.9669 0.0254
-4.500 -0.3017 0.01604 0.00839 -0.0456 0.9618 0.0290
-4.250 -0.2684 0.01548 0.00772 -0.0468 0.9582 0.0334
-4.000 -0.2397 0.01480 0.00694 -0.0470 0.9526 0.0377
-3.750 -0.2088 0.01434 0.00645 -0.0477 0.9474 0.0435
-3.500 -0.1750 0.01380 0.00582 -0.0489 0.9439 0.0489
-3.250 -0.1471 0.01336 0.00536 -0.0490 0.9371 0.0565
-3.000 -0.1145 0.01290 0.00485 -0.0500 0.9323 0.0636
-2.750 -0.0808 0.01254 0.00445 -0.0512 0.9278 0.0740
-2.500 -0.0514 0.01216 0.00409 -0.0515 0.9205 0.0872
-2.250 -0.0169 0.01170 0.00373 -0.0530 0.9161 0.1127
-2.000 0.0109 0.01125 0.00353 -0.0531 0.9076 0.1742
-1.750 0.0450 0.01087 0.00332 -0.0545 0.9022 0.2358
-1.500 0.0731 0.01053 0.00315 -0.0546 0.8931 0.2947
-1.250 0.1037 0.01003 0.00298 -0.0553 0.8857 0.3902
-1.000 0.1282 0.00937 0.00287 -0.0546 0.8760 0.5493
-0.750 0.2440 0.00845 0.00306 -0.0729 0.8810 0.9741
-0.500 0.2967 0.00844 0.00294 -0.0782 0.8715 0.9977
-0.250 0.3322 0.00840 0.00279 -0.0797 0.8577 1.0000
0.000 0.3606 0.00839 0.00267 -0.0797 0.8428 1.0000
0.250 0.3877 0.00840 0.00259 -0.0794 0.8279 1.0000
0.500 0.4138 0.00843 0.00254 -0.0789 0.8131 1.0000
0.750 0.4393 0.00848 0.00252 -0.0783 0.7984 1.0000
1.000 0.4642 0.00854 0.00251 -0.0775 0.7835 1.0000
1.250 0.4888 0.00862 0.00252 -0.0767 0.7686 1.0000
1.500 0.5131 0.00870 0.00255 -0.0758 0.7532 1.0000
1.750 0.5371 0.00879 0.00260 -0.0748 0.7373 1.0000
2.000 0.5610 0.00890 0.00266 -0.0738 0.7209 1.0000
2.250 0.5845 0.00901 0.00272 -0.0727 0.7030 1.0000
2.500 0.6075 0.00914 0.00280 -0.0716 0.6827 1.0000
2.750 0.6299 0.00930 0.00290 -0.0702 0.6574 1.0000
3.000 0.6513 0.00949 0.00298 -0.0687 0.6258 1.0000
3.250 0.6724 0.00971 0.00309 -0.0671 0.5928 1.0000
3.500 0.6933 0.00995 0.00322 -0.0655 0.5592 1.0000
3.750 0.7135 0.01025 0.00338 -0.0639 0.5226 1.0000
4.000 0.7335 0.01057 0.00360 -0.0622 0.4847 1.0000
4.250 0.7529 0.01094 0.00383 -0.0604 0.4451 1.0000
4.500 0.7719 0.01136 0.00410 -0.0586 0.4056 1.0000
4.750 0.7908 0.01181 0.00441 -0.0569 0.3663 1.0000
5.000 0.8093 0.01230 0.00477 -0.0551 0.3243 1.0000
5.250 0.8274 0.01285 0.00515 -0.0533 0.2778 1.0000
5.500 0.8443 0.01351 0.00557 -0.0514 0.2240 1.0000
5.750 0.8606 0.01427 0.00606 -0.0495 0.1708 1.0000
6.000 0.8775 0.01502 0.00659 -0.0476 0.1294 1.0000
6.250 0.8955 0.01569 0.00714 -0.0460 0.0999 1.0000
6.500 0.9136 0.01636 0.00774 -0.0443 0.0759 1.0000
6.750 0.9311 0.01708 0.00836 -0.0426 0.0545 1.0000
7.000 0.9488 0.01781 0.00906 -0.0409 0.0402 1.0000
7.250 0.9655 0.01863 0.00986 -0.0390 0.0308 1.0000
7.500 0.9828 0.01937 0.01066 -0.0372 0.0253 1.0000
7.750 0.9975 0.02037 0.01172 -0.0350 0.0222 1.0000
8.000 1.0135 0.02121 0.01274 -0.0329 0.0206 1.0000
8.250 1.0284 0.02215 0.01379 -0.0308 0.0190 1.0000
8.500 1.0429 0.02310 0.01484 -0.0287 0.0176 1.0000
8.750 1.0543 0.02433 0.01613 -0.0263 0.0160 1.0000
9.000 1.0669 0.02552 0.01743 -0.0240 0.0149 1.0000
9.250 1.0801 0.02669 0.01876 -0.0218 0.0142 1.0000
9.500 1.0921 0.02805 0.02026 -0.0195 0.0136 1.0000
9.750 1.1031 0.02945 0.02182 -0.0171 0.0130 1.0000
10.000 1.1135 0.03093 0.02347 -0.0147 0.0125 1.0000
10.250 1.1225 0.03248 0.02521 -0.0122 0.0119 1.0000
10.500 1.1304 0.03404 0.02692 -0.0098 0.0115 1.0000
10.750 1.1363 0.03558 0.02858 -0.0073 0.0110 1.0000
11.000 1.1385 0.03782 0.03098 -0.0047 0.0106 1.0000
11.250 1.1389 0.04009 0.03349 -0.0021 0.0102 1.0000
11.500 1.1398 0.04196 0.03564 0.0002 0.0097 1.0000
11.750 1.1366 0.04455 0.03850 0.0024 0.0095 1.0000
12.000 1.1300 0.04750 0.04172 0.0044 0.0093 1.0000
12.250 1.1214 0.05072 0.04521 0.0058 0.0092 1.0000
12.500 1.1102 0.05439 0.04914 0.0066 0.0091 1.0000
12.750 1.0954 0.05879 0.05379 0.0065 0.0090 1.0000
13.000 1.0807 0.06350 0.05872 0.0056 0.0090 1.0000
13.250 1.0630 0.06909 0.06454 0.0036 0.0091 1.0000
13.500 1.0434 0.07560 0.07126 0.0005 0.0091 1.0000
13.750 1.0244 0.08268 0.07852 -0.0036 0.0091 1.0000
14.000 1.0023 0.09121 0.08724 -0.0089 0.0091 1.0000
14.250 0.9811 0.10040 0.09657 -0.0147 0.0094 1.0000
14.500 0.9577 0.11097 0.10725 -0.0212 0.0096 1.0000
14.750 0.9279 0.12443 0.12081 -0.0289 0.0098 1.0000
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Polar data table (+)
Polar graphs
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