GOE 324 (HANSA-BRANDENBURG) AIRFOIL (goe324-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 324 (HANSA-BRANDENBURG) AIRFOIL (goe324-il) Reynolds number: 100,000 Max Cl/Cd: 49.59 at α=7.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe324-il-100000-n5.txt Download as CSV file: xf-goe324-il-100000-n5.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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.2384 0.10510 0.09952 -0.0137 0.6948 0.0557
-8.250 -0.2375 0.10250 0.09693 -0.0187 0.6902 0.0565
-8.000 -0.2364 0.09949 0.09397 -0.0242 0.6852 0.0569
-7.750 -0.2189 0.09584 0.09028 -0.0208 0.6799 0.0578
-7.500 -0.2081 0.09298 0.08737 -0.0210 0.6757 0.0588
-7.250 -0.1987 0.09013 0.08455 -0.0227 0.6704 0.0601
-7.000 -0.1920 0.08738 0.08182 -0.0251 0.6654 0.0614
-6.750 -0.1822 0.08423 0.07863 -0.0297 0.6610 0.0630
-6.500 -0.1681 0.08047 0.07467 -0.0425 0.6575 0.0647
-6.250 -0.1541 0.07679 0.07101 -0.0436 0.6524 0.0652
-6.000 -0.1404 0.07384 0.06809 -0.0425 0.6470 0.0660
-5.750 -0.1252 0.07108 0.06529 -0.0431 0.6423 0.0672
-5.500 -0.1083 0.06825 0.06237 -0.0450 0.6386 0.0689
-5.250 -0.0868 0.06518 0.05922 -0.0492 0.6333 0.0719
-5.000 -0.0611 0.06147 0.05524 -0.0556 0.6284 0.0748
-4.750 -0.0453 0.05887 0.05267 -0.0548 0.6236 0.0763
-4.500 -0.0256 0.05656 0.05026 -0.0554 0.6197 0.0793
-4.250 0.0051 0.05380 0.04712 -0.0605 0.6142 0.0860
-4.000 0.0239 0.05111 0.04450 -0.0604 0.6090 0.0876
-3.750 0.0459 0.04894 0.04225 -0.0609 0.6046 0.0904
-3.250 0.0974 0.04451 0.03743 -0.0637 0.5952 0.1012
-3.000 0.1217 0.04264 0.03549 -0.0642 0.5899 0.1053
-2.750 0.1486 0.04078 0.03334 -0.0652 0.5856 0.1154
-2.500 0.1877 0.03628 0.02800 -0.0656 0.5826 0.0635
-2.250 0.2146 0.03452 0.02613 -0.0661 0.5767 0.0618
-2.000 0.2456 0.03248 0.02353 -0.0660 0.5720 0.0564
-1.750 0.2724 0.03098 0.02188 -0.0661 0.5679 0.0551
-1.500 0.3004 0.02958 0.02019 -0.0659 0.5644 0.0536
-1.250 0.3292 0.02838 0.01877 -0.0660 0.5584 0.0523
-1.000 0.3583 0.02726 0.01731 -0.0658 0.5536 0.0511
-0.750 0.3871 0.02632 0.01604 -0.0655 0.5497 0.0505
-0.500 0.4153 0.02554 0.01507 -0.0653 0.5462 0.0507
-0.250 0.4430 0.02502 0.01455 -0.0654 0.5407 0.0520
0.000 0.4711 0.02447 0.01390 -0.0653 0.5361 0.0534
0.250 0.4993 0.02388 0.01316 -0.0650 0.5324 0.0539
0.500 0.5273 0.02338 0.01254 -0.0647 0.5286 0.0542
0.750 0.5548 0.02307 0.01224 -0.0647 0.5234 0.0546
1.000 0.5823 0.02273 0.01187 -0.0645 0.5191 0.0553
1.250 0.6097 0.02238 0.01146 -0.0641 0.5156 0.0561
1.500 0.6367 0.02205 0.01112 -0.0638 0.5122 0.0581
1.750 0.6630 0.02203 0.01120 -0.0637 0.5068 0.0610
2.000 0.6900 0.02196 0.01108 -0.0635 0.5025 0.0634
2.250 0.7175 0.02183 0.01086 -0.0632 0.4989 0.0655
2.500 0.7454 0.02174 0.01068 -0.0630 0.4956 0.0688
2.750 0.7719 0.02196 0.01095 -0.0630 0.4900 0.0750
3.000 0.7992 0.02196 0.01097 -0.0629 0.4853 0.0882
3.250 0.8306 0.01992 0.01087 -0.0633 0.4812 1.0000
3.500 0.8566 0.02022 0.01103 -0.0630 0.4757 1.0000
3.750 0.8825 0.02048 0.01120 -0.0628 0.4697 1.0000
4.000 0.9095 0.02059 0.01115 -0.0625 0.4652 1.0000
4.250 0.9356 0.02086 0.01133 -0.0622 0.4606 1.0000
4.500 0.9605 0.02128 0.01176 -0.0621 0.4548 1.0000
4.750 0.9867 0.02151 0.01191 -0.0618 0.4502 1.0000
5.000 1.0139 0.02164 0.01191 -0.0616 0.4466 1.0000
5.250 1.0375 0.02218 0.01253 -0.0614 0.4408 1.0000
5.500 1.0624 0.02254 0.01289 -0.0611 0.4356 1.0000
5.750 1.0888 0.02274 0.01301 -0.0609 0.4314 1.0000
6.000 1.1135 0.02312 0.01340 -0.0606 0.4266 1.0000
6.250 1.1364 0.02364 0.01399 -0.0603 0.4206 1.0000
6.500 1.1617 0.02390 0.01421 -0.0600 0.4157 1.0000
6.750 1.1875 0.02415 0.01442 -0.0597 0.4115 1.0000
7.000 1.2079 0.02486 0.01527 -0.0593 0.4052 1.0000
7.250 1.2318 0.02522 0.01564 -0.0589 0.3999 1.0000
7.500 1.2582 0.02537 0.01571 -0.0586 0.3957 1.0000
7.750 1.2755 0.02623 0.01676 -0.0580 0.3883 1.0000
8.000 1.2983 0.02658 0.01711 -0.0575 0.3824 1.0000
8.250 1.3200 0.02702 0.01758 -0.0570 0.3766 1.0000
8.500 1.3371 0.02776 0.01844 -0.0562 0.3692 1.0000
8.750 1.3604 0.02798 0.01862 -0.0557 0.3636 1.0000
9.000 1.3731 0.02900 0.01979 -0.0547 0.3558 1.0000
9.250 1.3916 0.02949 0.02031 -0.0539 0.3494 1.0000
9.500 1.4045 0.03041 0.02132 -0.0528 0.3424 1.0000
9.750 1.4162 0.03135 0.02233 -0.0517 0.3357 1.0000
10.000 1.4311 0.03198 0.02297 -0.0506 0.3305 1.0000
10.250 1.4312 0.03381 0.02495 -0.0491 0.3238 1.0000
10.500 1.4423 0.03490 0.02608 -0.0483 0.3187 1.0000
10.750 1.4489 0.03649 0.02774 -0.0476 0.3134 1.0000
11.000 1.4491 0.03875 0.03013 -0.0470 0.3073 1.0000
11.250 1.4628 0.03971 0.03109 -0.0463 0.3025 1.0000
11.500 1.4573 0.04268 0.03419 -0.0460 0.2960 1.0000
11.750 1.4601 0.04480 0.03638 -0.0456 0.2902 1.0000
12.000 1.4718 0.04599 0.03756 -0.0450 0.2853 1.0000
12.250 1.4595 0.04993 0.04166 -0.0450 0.2793 1.0000
12.500 1.4664 0.05169 0.04348 -0.0445 0.2746 1.0000
12.750 1.4765 0.05309 0.04489 -0.0440 0.2703 1.0000
13.000 1.4581 0.05793 0.04990 -0.0443 0.2642 1.0000
13.250 1.4651 0.05969 0.05169 -0.0439 0.2595 1.0000
13.500 1.4714 0.06155 0.05359 -0.0436 0.2550 1.0000
13.750 1.4464 0.06747 0.05969 -0.0443 0.2488 1.0000
14.250 1.4669 0.07028 0.06257 -0.0436 0.2407 1.0000
14.500 1.4274 0.07879 0.07130 -0.0454 0.2344 1.0000
14.750 1.4341 0.08080 0.07337 -0.0454 0.2303 1.0000
15.000 1.4639 0.07943 0.07198 -0.0442 0.2273 1.0000
15.250 1.3892 0.09385 0.08669 -0.0484 0.2190 1.0000
15.500 1.4035 0.09473 0.08762 -0.0481 0.2152 1.0000
15.750 1.4385 0.09235 0.08524 -0.0467 0.2125 1.0000
16.000 1.3468 0.11051 0.10365 -0.0529 0.2016 1.0000
16.250 1.3782 0.10847 0.10165 -0.0516 0.1992 1.0000
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Polar data table (+)
Polar graphs
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