GOE 803 (HACKLINGER) AIRFOIL (goe803h-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 803 (HACKLINGER) AIRFOIL (goe803h-il) Reynolds number: 500,000 Max Cl/Cd: 103.59 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe803h-il-500000-n5.txt Download as CSV file: xf-goe803h-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 803 (HACKLINGER) 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
------ -------- --------- --------- -------- -------- --------
-9.000 -0.2600 0.11058 0.10823 -0.0248 1.0000 0.0150
-8.750 -0.2546 0.10801 0.10568 -0.0252 1.0000 0.0156
-8.500 -0.2500 0.10551 0.10321 -0.0257 1.0000 0.0157
-8.250 -0.2428 0.10280 0.10052 -0.0270 0.9991 0.0158
-8.000 -0.2250 0.09917 0.09689 -0.0315 0.9938 0.0159
-7.500 -0.1928 0.09243 0.09014 -0.0396 0.9569 0.0160
-7.250 -0.1659 0.08796 0.08563 -0.0454 0.9388 0.0161
-6.750 -0.1165 0.08113 0.07866 -0.0547 0.9018 0.0165
-6.500 -0.0994 0.07851 0.07595 -0.0576 0.8842 0.0168
-6.250 -0.0822 0.07591 0.07329 -0.0605 0.8691 0.0172
-6.000 -0.0637 0.07324 0.07056 -0.0637 0.8553 0.0177
-5.750 -0.0421 0.07029 0.06755 -0.0680 0.8418 0.0189
-5.250 0.0134 0.06356 0.06067 -0.0809 0.8149 0.0193
-5.000 0.0457 0.06002 0.05705 -0.0882 0.8021 0.0194
-4.750 0.0785 0.05645 0.05339 -0.0950 0.7900 0.0195
-4.500 0.0964 0.05383 0.05071 -0.0957 0.7775 0.0196
-4.250 0.1214 0.05138 0.04818 -0.0986 0.7643 0.0199
-4.000 0.1504 0.04886 0.04557 -0.1025 0.7513 0.0201
-3.750 0.1825 0.04625 0.04287 -0.1071 0.7394 0.0205
-3.500 0.2174 0.04351 0.04003 -0.1123 0.7295 0.0211
-3.250 0.2738 0.03925 0.03556 -0.1231 0.7199 0.0233
-3.000 0.2994 0.03684 0.03309 -0.1251 0.7109 0.0207
-2.500 0.3784 0.03149 0.02745 -0.1348 0.6899 0.0218
-2.250 0.4281 0.02721 0.02289 -0.1418 0.6782 0.0204
-2.000 0.4697 0.02426 0.01969 -0.1460 0.6647 0.0206
-1.750 0.5091 0.02170 0.01685 -0.1493 0.6515 0.0210
-1.500 0.5490 0.01901 0.01386 -0.1524 0.6404 0.0216
-1.250 0.6038 0.01187 0.00548 -0.1587 0.6329 0.0233
-1.000 0.6340 0.01110 0.00447 -0.1591 0.6227 0.0240
-0.750 0.6627 0.01084 0.00411 -0.1592 0.6121 0.0246
-0.500 0.6912 0.01059 0.00376 -0.1592 0.6009 0.0254
0.000 0.7479 0.01019 0.00312 -0.1591 0.5756 0.0278
0.250 0.7762 0.01003 0.00288 -0.1590 0.5616 0.0289
0.500 0.8039 0.01002 0.00281 -0.1589 0.5457 0.0302
0.750 0.8315 0.01001 0.00271 -0.1587 0.5281 0.0319
1.000 0.8590 0.01002 0.00262 -0.1585 0.5089 0.0341
1.250 0.8859 0.01017 0.00270 -0.1581 0.4857 0.0369
1.500 0.9123 0.01036 0.00273 -0.1578 0.4547 0.0407
1.750 0.9379 0.01067 0.00285 -0.1573 0.4126 0.0439
2.000 0.9632 0.01103 0.00298 -0.1568 0.3692 0.0470
2.250 0.9889 0.01132 0.00310 -0.1564 0.3351 0.0500
2.500 1.0151 0.01156 0.00326 -0.1561 0.3140 0.0544
2.750 1.0415 0.01177 0.00339 -0.1557 0.2980 0.0573
3.000 1.0683 0.01191 0.00348 -0.1555 0.2855 0.0603
3.250 1.0947 0.01210 0.00362 -0.1552 0.2739 0.0628
3.500 1.1212 0.01227 0.00376 -0.1549 0.2636 0.0655
3.750 1.1475 0.01247 0.00391 -0.1545 0.2547 0.0698
4.000 1.1739 0.01263 0.00407 -0.1542 0.2473 0.0781
4.250 1.1989 0.01171 0.00454 -0.1541 0.2412 0.8825
4.750 1.2503 0.01207 0.00487 -0.1530 0.2301 1.0000
5.000 1.2760 0.01233 0.00509 -0.1526 0.2245 1.0000
5.250 1.3018 0.01257 0.00530 -0.1522 0.2176 1.0000
5.500 1.3271 0.01285 0.00554 -0.1517 0.2116 1.0000
5.750 1.3527 0.01308 0.00577 -0.1512 0.2077 1.0000
6.000 1.3783 0.01331 0.00600 -0.1507 0.2033 1.0000
6.250 1.4035 0.01357 0.00626 -0.1502 0.1982 1.0000
6.500 1.4283 0.01386 0.00654 -0.1497 0.1934 1.0000
6.750 1.4535 0.01409 0.00680 -0.1492 0.1879 1.0000
7.000 1.4779 0.01441 0.00709 -0.1486 0.1806 1.0000
7.250 1.5024 0.01470 0.00740 -0.1480 0.1720 1.0000
7.500 1.5249 0.01519 0.00777 -0.1471 0.1507 1.0000
7.750 1.5451 0.01592 0.00831 -0.1460 0.1235 1.0000
8.000 1.5656 0.01659 0.00889 -0.1448 0.1064 1.0000
8.250 1.5862 0.01723 0.00948 -0.1437 0.0922 1.0000
9.000 1.6389 0.01988 0.01181 -0.1390 0.0421 1.0000
9.250 1.6584 0.02048 0.01245 -0.1378 0.0400 1.0000
9.500 1.6771 0.02113 0.01313 -0.1363 0.0376 1.0000
9.750 1.6951 0.02178 0.01384 -0.1348 0.0357 1.0000
10.000 1.7138 0.02233 0.01445 -0.1334 0.0351 1.0000
10.250 1.7316 0.02292 0.01511 -0.1319 0.0344 1.0000
10.500 1.7482 0.02355 0.01582 -0.1302 0.0337 1.0000
10.750 1.7630 0.02422 0.01657 -0.1283 0.0328 1.0000
11.000 1.7747 0.02496 0.01738 -0.1258 0.0318 1.0000
11.250 1.7849 0.02579 0.01827 -0.1231 0.0307 1.0000
11.500 1.7941 0.02674 0.01929 -0.1205 0.0296 1.0000
11.750 1.8015 0.02785 0.02049 -0.1178 0.0283 1.0000
12.000 1.8107 0.02888 0.02160 -0.1155 0.0273 1.0000
12.250 1.8223 0.02977 0.02258 -0.1136 0.0266 1.0000
12.500 1.8329 0.03078 0.02370 -0.1118 0.0255 1.0000
12.750 1.8426 0.03192 0.02493 -0.1100 0.0238 1.0000
13.000 1.8505 0.03328 0.02635 -0.1083 0.0216 1.0000
13.250 1.8569 0.03482 0.02794 -0.1066 0.0190 1.0000
13.500 1.8607 0.03669 0.02982 -0.1049 0.0163 1.0000
13.750 1.8619 0.03888 0.03206 -0.1032 0.0137 1.0000
14.000 1.8619 0.04131 0.03457 -0.1017 0.0112 1.0000
14.250 1.8594 0.04414 0.03747 -0.1004 0.0096 1.0000
14.500 1.8557 0.04720 0.04063 -0.0994 0.0088 1.0000
14.750 1.8506 0.05056 0.04410 -0.0985 0.0082 1.0000
15.000 1.8452 0.05407 0.04772 -0.0979 0.0077 1.0000
15.250 1.8392 0.05773 0.05152 -0.0975 0.0075 1.0000
15.500 1.8317 0.06171 0.05564 -0.0973 0.0073 1.0000
15.750 1.8227 0.06606 0.06013 -0.0974 0.0071 1.0000
16.000 1.8126 0.07071 0.06492 -0.0977 0.0070 1.0000
16.250 1.8013 0.07573 0.07008 -0.0984 0.0069 1.0000
16.500 1.7881 0.08123 0.07573 -0.0995 0.0067 1.0000
16.750 1.7736 0.08707 0.08172 -0.1008 0.0067 1.0000
17.000 1.7578 0.09328 0.08807 -0.1024 0.0066 1.0000
17.250 1.7411 0.09982 0.09477 -0.1044 0.0065 1.0000
17.500 1.7236 0.10667 0.10176 -0.1067 0.0065 1.0000
17.750 1.7057 0.11369 0.10893 -0.1092 0.0064 1.0000
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