GOE 100 (SOPWITH) AIRFOIL (goe100-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 100 (SOPWITH) AIRFOIL (goe100-il) Reynolds number: 200,000 Max Cl/Cd: 61.67 at α=1.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe100-il-200000-n5.txt Download as CSV file: xf-goe100-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 100 (SOPWITH) AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-8.500 -0.2853 0.08947 0.08632 -0.0257 1.0000 0.0185
-8.250 -0.3850 0.10007 0.09672 -0.0235 1.0000 0.0149
-8.000 -0.3850 0.09658 0.09327 -0.0237 1.0000 0.0152
-7.750 -0.3815 0.09345 0.09017 -0.0228 1.0000 0.0158
-7.500 -0.3801 0.09101 0.08777 -0.0218 1.0000 0.0167
-7.250 -0.3832 0.08877 0.08560 -0.0210 1.0000 0.0173
-7.000 -0.3842 0.08627 0.08315 -0.0211 1.0000 0.0182
-6.750 -0.3849 0.08364 0.08058 -0.0215 1.0000 0.0190
-6.500 -0.3858 0.08104 0.07802 -0.0218 1.0000 0.0200
-6.250 -0.3869 0.07841 0.07543 -0.0219 1.0000 0.0207
-6.000 -0.3739 0.07448 0.07149 -0.0259 0.9980 0.0222
-5.750 -0.3280 0.06805 0.06490 -0.0401 0.9927 0.0246
-5.250 -0.2804 0.05611 0.05280 -0.0482 0.9851 0.0133
-5.000 -0.2506 0.05065 0.04719 -0.0535 0.9808 0.0123
-4.750 -0.2161 0.04497 0.04130 -0.0589 0.9777 0.0115
-4.500 -0.1840 0.03931 0.03538 -0.0627 0.9726 0.0109
-4.250 -0.1475 0.03267 0.02833 -0.0665 0.9696 0.0103
-4.000 -0.1104 0.02466 0.01952 -0.0693 0.9676 0.0097
-3.750 -0.0807 0.02064 0.01476 -0.0697 0.9631 0.0098
-3.500 -0.0484 0.01829 0.01187 -0.0705 0.9602 0.0106
-3.250 -0.0145 0.01681 0.01001 -0.0717 0.9578 0.0127
-3.000 0.0213 0.01520 0.00804 -0.0730 0.9558 0.0136
-2.750 0.0527 0.01408 0.00668 -0.0734 0.9499 0.0148
-2.500 0.0881 0.01307 0.00551 -0.0747 0.9447 0.0216
-2.250 0.1227 0.01254 0.00497 -0.0758 0.9394 0.0434
-2.000 0.1539 0.01224 0.00464 -0.0765 0.9325 0.0633
-1.750 0.1877 0.01189 0.00425 -0.0776 0.9251 0.0823
-1.500 0.2215 0.01149 0.00381 -0.0786 0.9149 0.0900
-1.250 0.2518 0.01121 0.00353 -0.0789 0.9034 0.1061
-1.000 0.2816 0.01099 0.00335 -0.0792 0.8937 0.1425
-0.750 0.3115 0.01080 0.00316 -0.0794 0.8834 0.1724
-0.250 0.3676 0.01043 0.00281 -0.0791 0.8554 0.2276
0.000 0.3940 0.01013 0.00272 -0.0788 0.8386 0.3058
0.250 0.4171 0.00852 0.00273 -0.0770 0.8221 0.9523
0.500 0.4528 0.00849 0.00256 -0.0785 0.8027 1.0000
0.750 0.4786 0.00854 0.00248 -0.0778 0.7793 1.0000
1.000 0.5043 0.00861 0.00241 -0.0771 0.7503 1.0000
1.250 0.5295 0.00873 0.00233 -0.0763 0.7089 1.0000
1.500 0.5532 0.00897 0.00225 -0.0751 0.6481 1.0000
1.750 0.5753 0.00938 0.00227 -0.0738 0.5799 1.0000
2.000 0.5976 0.00984 0.00238 -0.0727 0.5230 1.0000
2.250 0.6207 0.01026 0.00257 -0.0718 0.4758 1.0000
2.500 0.6443 0.01066 0.00275 -0.0710 0.4324 1.0000
2.750 0.6680 0.01106 0.00295 -0.0704 0.3913 1.0000
3.000 0.6920 0.01145 0.00320 -0.0697 0.3568 1.0000
3.250 0.7162 0.01182 0.00344 -0.0692 0.3273 1.0000
3.500 0.7384 0.01244 0.00373 -0.0684 0.2714 1.0000
3.750 0.7624 0.01287 0.00402 -0.0679 0.2385 1.0000
4.000 0.7854 0.01343 0.00435 -0.0673 0.1936 1.0000
4.250 0.8056 0.01442 0.00476 -0.0664 0.1151 1.0000
4.500 0.8243 0.01575 0.00558 -0.0651 0.0192 1.0000
4.750 0.8490 0.01621 0.00619 -0.0645 0.0155 1.0000
5.000 0.8733 0.01676 0.00691 -0.0637 0.0138 1.0000
5.250 0.8958 0.01763 0.00806 -0.0627 0.0115 1.0000
5.500 0.9184 0.01848 0.00912 -0.0617 0.0103 1.0000
5.750 0.9410 0.01930 0.01012 -0.0607 0.0099 1.0000
6.000 0.9622 0.02025 0.01125 -0.0595 0.0095 1.0000
6.250 0.9814 0.02136 0.01248 -0.0581 0.0093 1.0000
6.500 0.9998 0.02248 0.01368 -0.0566 0.0085 1.0000
6.750 1.0162 0.02385 0.01510 -0.0550 0.0074 1.0000
7.000 1.0314 0.02567 0.01687 -0.0532 0.0069 1.0000
7.250 1.0502 0.02745 0.01864 -0.0518 0.0069 1.0000
7.500 1.0717 0.02922 0.02042 -0.0507 0.0069 1.0000
7.750 1.0943 0.03082 0.02212 -0.0497 0.0070 1.0000
8.000 1.1154 0.03227 0.02384 -0.0482 0.0075 1.0000
8.250 1.1366 0.03434 0.02616 -0.0468 0.0083 1.0000
8.500 1.1571 0.03739 0.02943 -0.0456 0.0094 1.0000
8.750 1.1839 0.03800 0.03039 -0.0438 0.0151 1.0000
9.000 1.1994 0.04056 0.03325 -0.0419 0.0154 1.0000
9.250 1.2109 0.04314 0.03622 -0.0396 0.0151 1.0000
9.500 1.2184 0.04584 0.03925 -0.0371 0.0146 1.0000
9.750 1.2219 0.04872 0.04243 -0.0345 0.0139 1.0000
10.000 1.2229 0.05188 0.04583 -0.0319 0.0132 1.0000
10.250 1.2285 0.05622 0.05025 -0.0305 0.0122 1.0000
10.500 1.2303 0.06276 0.05691 -0.0295 0.0114 1.0000
10.750 1.2180 0.06888 0.06331 -0.0271 0.0111 1.0000
13.750 0.8234 0.11427 0.11102 -0.0267 0.0165 1.0000
14.000 0.8044 0.12068 0.11750 -0.0305 0.0169 1.0000
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Polar data table (+)
Polar graphs
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