GOE 315 (HANSA-BRANDENBURG III.5) AIRFOIL (goe315-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 315 (HANSA-BRANDENBURG III.5) AIRFOIL (goe315-il) Reynolds number: 100,000 Max Cl/Cd: 54.35 at α=7.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe315-il-100000.txt Download as CSV file: xf-goe315-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 315 (HANSA-BRANDENBURG III.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
------ -------- --------- --------- -------- -------- --------
-8.500 -0.3690 0.10113 0.09613 -0.0189 1.0000 0.0621
-8.250 -0.3774 0.10018 0.09530 -0.0224 1.0000 0.0628
-8.000 -0.3810 0.09870 0.09387 -0.0284 1.0000 0.0632
-7.750 -0.3779 0.09605 0.09123 -0.0329 1.0000 0.0635
-7.500 -0.3605 0.08843 0.08370 -0.0226 1.0000 0.0657
-7.250 -0.3528 0.08530 0.08060 -0.0219 1.0000 0.0682
-7.000 -0.3478 0.08242 0.07777 -0.0231 1.0000 0.0706
-6.750 -0.3427 0.07957 0.07497 -0.0255 1.0000 0.0733
-6.500 -0.3347 0.07778 0.07311 -0.0330 1.0000 0.0763
-6.250 -0.3263 0.07573 0.07090 -0.0378 1.0000 0.0774
-6.000 -0.3211 0.07023 0.06563 -0.0340 1.0000 0.0787
-5.750 -0.3148 0.06714 0.06262 -0.0318 1.0000 0.0806
-5.500 -0.3087 0.06460 0.06014 -0.0310 1.0000 0.0832
-5.250 -0.3055 0.06247 0.05803 -0.0304 1.0000 0.0864
-5.000 -0.3030 0.06397 0.05911 -0.0325 1.0000 0.0914
-4.750 -0.3076 0.06048 0.05574 -0.0302 1.0000 0.0923
-4.500 -0.2806 0.05544 0.05088 -0.0325 0.9929 0.0968
-4.250 -0.2287 0.05177 0.04680 -0.0417 0.9821 0.1077
-4.000 -0.1925 0.04781 0.04286 -0.0456 0.9724 0.1151
-3.750 -0.1508 0.04431 0.03915 -0.0511 0.9608 0.1261
-3.500 -0.1100 0.04119 0.03586 -0.0557 0.9496 0.1417
-3.250 -0.0649 0.03840 0.03281 -0.0611 0.9406 0.1691
-3.000 -0.0268 0.03576 0.03004 -0.0646 0.9292 0.1993
-2.750 0.0054 0.03285 0.02718 -0.0666 0.9166 0.2334
-2.500 0.0372 0.03097 0.02521 -0.0682 0.9035 0.2899
-2.250 0.0653 0.02820 0.02258 -0.0685 0.8905 0.3335
-2.000 0.0930 0.02614 0.02054 -0.0683 0.8768 0.3788
-1.750 0.1243 0.02445 0.01867 -0.0688 0.8628 0.4045
-1.500 0.1641 0.02313 0.01690 -0.0708 0.8489 0.3835
-1.250 0.2308 0.02353 0.01560 -0.0733 0.8348 0.1686
-1.000 0.2633 0.02250 0.01417 -0.0722 0.8207 0.1303
-0.750 0.2924 0.02171 0.01305 -0.0712 0.8071 0.1159
-0.500 0.3197 0.02097 0.01212 -0.0703 0.7941 0.1133
-0.250 0.3477 0.02046 0.01133 -0.0693 0.7821 0.1083
0.000 0.3752 0.02010 0.01078 -0.0682 0.7699 0.1056
0.250 0.4005 0.01946 0.01009 -0.0671 0.7553 0.1047
0.500 0.4256 0.01896 0.00954 -0.0658 0.7407 0.1047
0.750 0.4502 0.01856 0.00911 -0.0645 0.7267 0.1057
1.000 0.4738 0.01807 0.00871 -0.0633 0.7139 0.1108
1.250 0.4991 0.01787 0.00846 -0.0623 0.7028 0.1177
1.500 0.5257 0.01766 0.00815 -0.0616 0.6924 0.1248
1.750 0.5514 0.01754 0.00803 -0.0608 0.6801 0.1412
2.000 0.6023 0.01544 0.00774 -0.0649 0.6674 1.0000
2.250 0.6271 0.01564 0.00772 -0.0638 0.6562 1.0000
2.500 0.6522 0.01578 0.00769 -0.0628 0.6451 1.0000
2.750 0.6763 0.01598 0.00783 -0.0619 0.6320 1.0000
3.000 0.7006 0.01617 0.00795 -0.0609 0.6192 1.0000
3.250 0.7252 0.01634 0.00806 -0.0599 0.6063 1.0000
3.500 0.7498 0.01650 0.00815 -0.0590 0.5929 1.0000
3.750 0.7744 0.01666 0.00825 -0.0580 0.5786 1.0000
4.000 0.7989 0.01685 0.00838 -0.0570 0.5635 1.0000
4.250 0.8233 0.01709 0.00857 -0.0560 0.5475 1.0000
4.500 0.8473 0.01735 0.00880 -0.0549 0.5301 1.0000
4.750 0.8709 0.01756 0.00893 -0.0537 0.5107 1.0000
5.000 0.8946 0.01772 0.00896 -0.0525 0.4908 1.0000
5.250 0.9170 0.01794 0.00917 -0.0513 0.4696 1.0000
5.500 0.9399 0.01818 0.00943 -0.0502 0.4505 1.0000
5.750 0.9631 0.01842 0.00966 -0.0492 0.4328 1.0000
6.000 0.9860 0.01863 0.00985 -0.0481 0.4154 1.0000
6.250 1.0089 0.01888 0.01008 -0.0471 0.3990 1.0000
6.500 1.0312 0.01914 0.01035 -0.0460 0.3823 1.0000
6.750 1.0531 0.01944 0.01070 -0.0449 0.3650 1.0000
7.000 1.0748 0.01979 0.01109 -0.0438 0.3488 1.0000
7.250 1.0963 0.02017 0.01155 -0.0428 0.3332 1.0000
7.500 1.1172 0.02058 0.01202 -0.0416 0.3170 1.0000
7.750 1.1361 0.02096 0.01243 -0.0402 0.2957 1.0000
8.000 1.1534 0.02140 0.01295 -0.0386 0.2685 1.0000
8.250 1.1676 0.02206 0.01359 -0.0367 0.2276 1.0000
8.500 1.1747 0.02359 0.01469 -0.0341 0.1368 1.0000
8.750 1.1785 0.02567 0.01632 -0.0313 0.1039 1.0000
9.000 1.1849 0.02742 0.01799 -0.0287 0.0942 1.0000
9.250 1.1914 0.02903 0.01963 -0.0262 0.0880 1.0000
9.500 1.1958 0.03077 0.02134 -0.0235 0.0835 1.0000
9.750 1.2039 0.03218 0.02286 -0.0210 0.0803 1.0000
10.000 1.2128 0.03371 0.02445 -0.0188 0.0776 1.0000
10.250 1.2250 0.03546 0.02613 -0.0170 0.0745 1.0000
10.500 1.2465 0.03753 0.02816 -0.0164 0.0713 1.0000
10.750 1.2646 0.03920 0.03001 -0.0153 0.0689 1.0000
11.000 1.2879 0.04127 0.03226 -0.0148 0.0669 1.0000
11.250 1.3079 0.04343 0.03454 -0.0142 0.0647 1.0000
11.500 1.3383 0.04661 0.03766 -0.0152 0.0617 1.0000
11.750 1.3562 0.05013 0.04142 -0.0147 0.0607 1.0000
12.000 1.3610 0.05289 0.04453 -0.0127 0.0603 1.0000
12.250 1.3594 0.05565 0.04763 -0.0103 0.0600 1.0000
12.500 1.3517 0.05842 0.05073 -0.0076 0.0596 1.0000
12.750 1.3403 0.06140 0.05401 -0.0053 0.0593 1.0000
13.000 1.3261 0.06474 0.05764 -0.0037 0.0591 1.0000
13.250 1.3088 0.06848 0.06165 -0.0029 0.0589 1.0000
13.500 1.2908 0.07286 0.06629 -0.0030 0.0590 1.0000
13.750 1.2708 0.07772 0.07139 -0.0040 0.0591 1.0000
14.000 1.2499 0.08322 0.07711 -0.0057 0.0595 1.0000
14.250 1.2262 0.08939 0.08349 -0.0083 0.0597 1.0000
14.500 1.2028 0.09624 0.09050 -0.0115 0.0602 1.0000
14.750 1.1811 0.10361 0.09801 -0.0151 0.0607 1.0000
15.000 1.1595 0.11159 0.10611 -0.0191 0.0611 1.0000
15.250 1.0087 0.15279 0.14758 -0.0496 0.0734 1.0000
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Polar data table (+)
Polar graphs
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