GOE 316 (HANSA-BRANDENBURG IV.5) AIRFOIL (goe316-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 316 (HANSA-BRANDENBURG IV.5) AIRFOIL (goe316-il) Reynolds number: 100,000 Max Cl/Cd: 50.86 at α=10.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe316-il-100000.txt Download as CSV file: xf-goe316-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 316 (HANSA-BRANDENBURG IV.5) 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.3873 0.10065 0.09602 -0.0066 1.0000 0.0620
-8.000 -0.3830 0.09760 0.09303 -0.0091 1.0000 0.0639
-7.750 -0.3822 0.09508 0.09057 -0.0136 1.0000 0.0657
-7.500 -0.3755 0.09285 0.08833 -0.0263 1.0000 0.0669
-7.250 -0.3661 0.08841 0.08389 -0.0312 1.0000 0.0676
-7.000 -0.3578 0.08326 0.07886 -0.0237 1.0000 0.0695
-6.750 -0.3471 0.07994 0.07559 -0.0233 1.0000 0.0723
-6.500 -0.3354 0.07659 0.07225 -0.0261 1.0000 0.0757
-6.250 -0.3142 0.07477 0.07015 -0.0385 1.0000 0.0807
-6.000 -0.3067 0.06988 0.06534 -0.0387 1.0000 0.0819
-5.750 -0.3036 0.06643 0.06207 -0.0355 1.0000 0.0834
-5.500 -0.3066 0.06452 0.06025 -0.0328 1.0000 0.0851
-5.250 -0.3139 0.06316 0.05893 -0.0301 1.0000 0.0868
-5.000 -0.3004 0.06070 0.05638 -0.0321 0.9972 0.0916
-4.750 -0.2539 0.05558 0.05104 -0.0409 0.9876 0.0995
-4.500 -0.2043 0.05150 0.04661 -0.0495 0.9774 0.1122
-4.250 -0.1554 0.04795 0.04274 -0.0566 0.9685 0.1262
-4.000 -0.1120 0.04412 0.03874 -0.0619 0.9585 0.1413
-3.750 -0.0758 0.04046 0.03508 -0.0653 0.9463 0.1583
-3.500 -0.0415 0.03783 0.03232 -0.0683 0.9331 0.1882
-3.250 -0.0129 0.03532 0.02980 -0.0696 0.9194 0.2210
-3.000 0.0112 0.03325 0.02776 -0.0696 0.9047 0.2676
-2.750 0.0316 0.03131 0.02589 -0.0682 0.8894 0.3156
-2.500 0.0504 0.02950 0.02414 -0.0661 0.8738 0.3638
-2.250 0.0680 0.02777 0.02249 -0.0633 0.8581 0.4134
-2.000 0.0905 0.02610 0.02076 -0.0617 0.8424 0.4473
-1.750 0.1347 0.02462 0.01862 -0.0656 0.8263 0.4033
-1.500 0.2017 0.02383 0.01597 -0.0690 0.8113 0.1799
-1.250 0.2341 0.02307 0.01460 -0.0672 0.7955 0.1358
-1.000 0.2622 0.02243 0.01355 -0.0657 0.7790 0.1232
-0.750 0.2883 0.02145 0.01240 -0.0645 0.7619 0.1206
-0.500 0.3150 0.02066 0.01137 -0.0632 0.7444 0.1150
-0.250 0.3419 0.02036 0.01076 -0.0617 0.7266 0.1109
0.000 0.3680 0.01974 0.01001 -0.0606 0.7078 0.1099
0.250 0.3941 0.01913 0.00933 -0.0596 0.6866 0.1098
0.500 0.4194 0.01839 0.00860 -0.0585 0.6662 0.1131
0.750 0.4446 0.01790 0.00809 -0.0574 0.6449 0.1183
1.000 0.4704 0.01758 0.00766 -0.0564 0.6220 0.1220
1.250 0.4965 0.01733 0.00721 -0.0555 0.6020 0.1273
1.500 0.5236 0.01722 0.00695 -0.0550 0.5810 0.1389
1.750 0.5512 0.01692 0.00675 -0.0547 0.5633 0.1934
2.000 0.5799 0.01527 0.00662 -0.0541 0.5482 1.0000
2.250 0.6071 0.01564 0.00669 -0.0537 0.5354 1.0000
2.500 0.6342 0.01603 0.00680 -0.0534 0.5252 1.0000
2.750 0.6614 0.01645 0.00713 -0.0534 0.5145 1.0000
3.000 0.6887 0.01689 0.00745 -0.0533 0.5065 1.0000
3.250 0.7160 0.01733 0.00781 -0.0533 0.4986 1.0000
3.500 0.7432 0.01780 0.00819 -0.0532 0.4920 1.0000
3.750 0.7703 0.01827 0.00868 -0.0532 0.4849 1.0000
4.000 0.7977 0.01876 0.00906 -0.0532 0.4800 1.0000
4.250 0.8246 0.01934 0.00973 -0.0533 0.4745 1.0000
4.500 0.8516 0.01990 0.01033 -0.0534 0.4696 1.0000
4.750 0.8788 0.02045 0.01087 -0.0534 0.4656 1.0000
5.000 0.9053 0.02111 0.01161 -0.0534 0.4610 1.0000
5.250 0.9315 0.02178 0.01241 -0.0535 0.4561 1.0000
5.500 0.9582 0.02244 0.01314 -0.0536 0.4524 1.0000
5.750 0.9852 0.02307 0.01375 -0.0535 0.4489 1.0000
6.000 1.0096 0.02383 0.01476 -0.0535 0.4424 1.0000
6.250 1.0360 0.02424 0.01517 -0.0532 0.4360 1.0000
6.500 1.0608 0.02491 0.01600 -0.0530 0.4295 1.0000
6.750 1.0860 0.02553 0.01675 -0.0528 0.4233 1.0000
7.000 1.1125 0.02599 0.01719 -0.0526 0.4175 1.0000
7.250 1.1356 0.02668 0.01814 -0.0522 0.4094 1.0000
7.500 1.1623 0.02696 0.01839 -0.0518 0.4024 1.0000
7.750 1.1853 0.02750 0.01915 -0.0513 0.3932 1.0000
8.000 1.2100 0.02791 0.01963 -0.0509 0.3849 1.0000
8.250 1.2353 0.02814 0.01995 -0.0503 0.3758 1.0000
8.500 1.2575 0.02880 0.02083 -0.0498 0.3668 1.0000
8.750 1.2847 0.02886 0.02084 -0.0493 0.3577 1.0000
9.000 1.3069 0.02905 0.02121 -0.0484 0.3454 1.0000
9.250 1.3288 0.02913 0.02147 -0.0475 0.3319 1.0000
9.500 1.3511 0.02872 0.02108 -0.0464 0.3151 1.0000
9.750 1.3700 0.02816 0.02061 -0.0449 0.2946 1.0000
10.000 1.3853 0.02780 0.02055 -0.0431 0.2716 1.0000
10.250 1.3976 0.02748 0.02058 -0.0410 0.2315 1.0000
10.500 1.3928 0.02910 0.02158 -0.0378 0.1589 1.0000
10.750 1.3796 0.03233 0.02451 -0.0344 0.1251 1.0000
11.000 1.3651 0.03526 0.02735 -0.0310 0.1083 1.0000
11.250 1.3523 0.03851 0.03058 -0.0289 0.0966 1.0000
11.500 1.3402 0.04215 0.03422 -0.0279 0.0884 1.0000
11.750 1.3298 0.04591 0.03797 -0.0275 0.0819 1.0000
12.000 1.3235 0.04938 0.04148 -0.0269 0.0758 1.0000
12.250 1.3189 0.05263 0.04466 -0.0263 0.0708 1.0000
12.500 1.3209 0.05520 0.04723 -0.0248 0.0658 1.0000
12.750 1.3273 0.05736 0.04938 -0.0233 0.0616 1.0000
13.000 1.3492 0.05852 0.05039 -0.0198 0.0573 1.0000
13.250 1.3531 0.06138 0.05351 -0.0191 0.0551 1.0000
13.500 1.3573 0.06426 0.05656 -0.0184 0.0527 1.0000
13.750 1.3629 0.06709 0.05948 -0.0177 0.0505 1.0000
14.250 1.3869 0.07428 0.06688 -0.0149 0.0475 1.0000
14.500 1.3755 0.07869 0.07157 -0.0155 0.0474 1.0000
14.750 1.3619 0.08351 0.07668 -0.0165 0.0472 1.0000
15.000 1.3463 0.08876 0.08220 -0.0180 0.0472 1.0000
15.250 1.3286 0.09446 0.08815 -0.0201 0.0472 1.0000
15.500 1.3097 0.10062 0.09455 -0.0228 0.0472 1.0000
15.750 1.2897 0.10724 0.10137 -0.0260 0.0473 1.0000
16.000 1.2694 0.11434 0.10867 -0.0296 0.0475 1.0000
16.500 1.1998 0.13563 0.13058 -0.0458 0.0496 1.0000
16.750 1.0887 0.17204 0.16718 -0.0712 0.0570 1.0000
17.000 1.0790 0.18144 0.17656 -0.0758 0.0579 1.0000
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Polar data table (+)
Polar graphs
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