GOE 324 (HANSA-BRANDENBURG) AIRFOIL (goe324-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 324 (HANSA-BRANDENBURG) AIRFOIL (goe324-il) Reynolds number: 500,000 Max Cl/Cd: 108.8 at α=8° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe324-il-500000.txt Download as CSV file: xf-goe324-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 324 (HANSA-BRANDENBURG) 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.500 -0.2455 0.08733 0.08382 -0.0116 0.6241 0.0266
-7.250 -0.2379 0.08424 0.08070 -0.0140 0.6204 0.0270
-7.000 -0.2310 0.08105 0.07754 -0.0171 0.6171 0.0274
-6.750 -0.2186 0.07728 0.07377 -0.0219 0.6133 0.0280
-6.500 -0.1949 0.06985 0.06621 -0.0378 0.6104 0.0288
-6.250 -0.1765 0.06493 0.06118 -0.0428 0.6069 0.0289
-6.000 -0.1627 0.06224 0.05845 -0.0430 0.6029 0.0291
-5.750 -0.1461 0.05976 0.05596 -0.0437 0.5991 0.0292
-5.500 -0.1275 0.05724 0.05342 -0.0450 0.5948 0.0295
-5.250 -0.1070 0.05458 0.05071 -0.0468 0.5906 0.0298
-5.000 -0.0847 0.05177 0.04780 -0.0489 0.5866 0.0303
-4.750 -0.0607 0.04880 0.04471 -0.0512 0.5825 0.0310
-4.500 -0.0211 0.04234 0.03770 -0.0567 0.5790 0.0331
-4.250 -0.0011 0.03978 0.03516 -0.0573 0.5742 0.0333
-4.000 0.0212 0.03789 0.03321 -0.0578 0.5696 0.0336
-3.750 0.0451 0.03615 0.03138 -0.0584 0.5651 0.0339
-3.500 0.0706 0.03432 0.02948 -0.0590 0.5603 0.0345
-3.250 0.0972 0.03239 0.02742 -0.0596 0.5555 0.0354
-3.000 0.1296 0.02893 0.02338 -0.0599 0.5515 0.0381
-2.750 0.1547 0.02742 0.02186 -0.0603 0.5467 0.0384
-2.500 0.1811 0.02614 0.02054 -0.0606 0.5414 0.0390
-2.250 0.2083 0.02489 0.01916 -0.0608 0.5362 0.0399
-2.000 0.2392 0.02314 0.01685 -0.0604 0.5316 0.0435
-1.750 0.2661 0.02174 0.01550 -0.0608 0.5265 0.0442
-1.500 0.2937 0.02080 0.01450 -0.0610 0.5214 0.0452
-1.250 0.3240 0.02011 0.01335 -0.0607 0.5168 0.0498
-1.000 0.3513 0.01882 0.01211 -0.0610 0.5121 0.0508
-0.750 0.3797 0.01809 0.01135 -0.0612 0.5070 0.0527
-0.500 0.4091 0.01743 0.01042 -0.0611 0.5021 0.0579
-0.250 0.4371 0.01673 0.00969 -0.0612 0.4975 0.0599
0.750 0.3356 0.02462 0.02047 -0.1038 0.4925 0.0509
1.000 0.5852 0.01326 0.00544 -0.0602 0.4759 0.0433
1.250 0.6138 0.01286 0.00504 -0.0602 0.4708 0.0430
1.500 0.6421 0.01265 0.00473 -0.0601 0.4653 0.0431
1.750 0.6703 0.01212 0.00430 -0.0601 0.4603 0.0442
2.000 0.6988 0.01191 0.00410 -0.0602 0.4557 0.0448
2.250 0.7272 0.01178 0.00396 -0.0602 0.4516 0.0454
2.500 0.7556 0.01173 0.00388 -0.0602 0.4476 0.0465
2.750 0.7845 0.01163 0.00383 -0.0604 0.4438 0.0480
3.000 0.8132 0.01159 0.00380 -0.0605 0.4400 0.0495
3.250 0.8417 0.01156 0.00377 -0.0606 0.4363 0.0536
3.500 0.8699 0.01164 0.00379 -0.0607 0.4322 0.0592
3.750 0.8974 0.00969 0.00400 -0.0609 0.4288 1.0000
4.000 0.9257 0.00980 0.00405 -0.0610 0.4247 1.0000
4.250 0.9538 0.00994 0.00412 -0.0610 0.4202 1.0000
4.500 0.9813 0.01016 0.00424 -0.0610 0.4154 1.0000
4.750 1.0096 0.01024 0.00434 -0.0611 0.4110 1.0000
5.000 1.0376 0.01036 0.00445 -0.0612 0.4063 1.0000
5.250 1.0652 0.01054 0.00458 -0.0613 0.4017 1.0000
5.500 1.0929 0.01072 0.00474 -0.0613 0.3974 1.0000
5.750 1.1209 0.01084 0.00488 -0.0615 0.3929 1.0000
6.000 1.1485 0.01099 0.00503 -0.0615 0.3884 1.0000
6.250 1.1755 0.01122 0.00520 -0.0616 0.3838 1.0000
6.500 1.2032 0.01137 0.00539 -0.0617 0.3793 1.0000
6.750 1.2307 0.01152 0.00556 -0.0618 0.3741 1.0000
7.000 1.2575 0.01173 0.00575 -0.0618 0.3689 1.0000
7.250 1.2846 0.01192 0.00595 -0.0619 0.3632 1.0000
7.500 1.3114 0.01210 0.00615 -0.0620 0.3562 1.0000
7.750 1.3376 0.01236 0.00638 -0.0620 0.3499 1.0000
8.000 1.3643 0.01254 0.00661 -0.0620 0.3428 1.0000
8.250 1.3897 0.01285 0.00689 -0.0620 0.3356 1.0000
8.500 1.4160 0.01307 0.00715 -0.0620 0.3279 1.0000
8.750 1.4406 0.01343 0.00747 -0.0619 0.3196 1.0000
9.000 1.4658 0.01373 0.00780 -0.0618 0.3103 1.0000
9.250 1.4897 0.01412 0.00818 -0.0616 0.3011 1.0000
9.500 1.5127 0.01458 0.00861 -0.0614 0.2916 1.0000
9.750 1.5359 0.01501 0.00905 -0.0611 0.2830 1.0000
10.000 1.5569 0.01558 0.00959 -0.0607 0.2748 1.0000
10.250 1.5788 0.01606 0.01010 -0.0603 0.2670 1.0000
10.500 1.5979 0.01672 0.01073 -0.0597 0.2599 1.0000
10.750 1.6180 0.01727 0.01132 -0.0592 0.2527 1.0000
11.000 1.6336 0.01808 0.01211 -0.0583 0.2456 1.0000
11.250 1.6513 0.01872 0.01279 -0.0575 0.2390 1.0000
11.500 1.6605 0.01973 0.01381 -0.0560 0.2330 1.0000
11.750 1.6730 0.02072 0.01485 -0.0552 0.2278 1.0000
12.000 1.6841 0.02198 0.01616 -0.0547 0.2225 1.0000
12.250 1.6908 0.02376 0.01795 -0.0543 0.2172 1.0000
12.500 1.7037 0.02506 0.01933 -0.0542 0.2125 1.0000
12.750 1.7122 0.02678 0.02110 -0.0540 0.2075 1.0000
13.250 1.7255 0.03054 0.02496 -0.0535 0.1978 1.0000
13.500 1.7299 0.03263 0.02710 -0.0531 0.1928 1.0000
13.750 1.7294 0.03517 0.02966 -0.0527 0.1881 1.0000
14.000 1.7358 0.03707 0.03165 -0.0524 0.1829 1.0000
14.250 1.7336 0.03980 0.03441 -0.0520 0.1770 1.0000
14.500 1.7329 0.04239 0.03706 -0.0516 0.1714 1.0000
14.750 1.7282 0.04542 0.04013 -0.0513 0.1642 1.0000
15.000 1.7222 0.04862 0.04336 -0.0510 0.1565 1.0000
15.250 1.7114 0.05251 0.04725 -0.0509 0.1479 1.0000
15.500 1.7017 0.05642 0.05117 -0.0509 0.1381 1.0000
15.750 1.6895 0.06070 0.05547 -0.0511 0.1283 1.0000
16.000 1.6752 0.06533 0.06010 -0.0514 0.1191 1.0000
16.250 1.6605 0.07012 0.06489 -0.0518 0.1118 1.0000
16.500 1.6476 0.07473 0.06953 -0.0522 0.1060 1.0000
16.750 1.6357 0.07930 0.07413 -0.0528 0.1017 1.0000
17.000 1.6263 0.08359 0.07846 -0.0533 0.0982 1.0000
17.250 1.6143 0.08826 0.08318 -0.0541 0.0950 1.0000
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Polar data table (+)
Polar graphs
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