GOE 767 AIRFOIL (goe767-il) Xfoil prediction polar at RE=200,000 Ncrit=9
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Airfoil: GOE 767 AIRFOIL (goe767-il) Reynolds number: 200,000 Max Cl/Cd: 49.66 at α=8.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe767-il-200000.txt Download as CSV file: xf-goe767-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 767 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.000 -0.8444 0.06548 0.06115 -0.0267 1.0000 0.0578
-11.750 -0.8954 0.05641 0.05184 -0.0329 1.0000 0.0571
-11.500 -0.9382 0.05079 0.04594 -0.0323 1.0000 0.0568
-11.250 -0.9689 0.04599 0.04078 -0.0296 1.0000 0.0567
-11.000 -0.9835 0.04165 0.03601 -0.0273 1.0000 0.0569
-10.750 -0.9870 0.03804 0.03197 -0.0252 1.0000 0.0573
-10.500 -0.9833 0.03504 0.02853 -0.0232 1.0000 0.0578
-10.250 -0.9745 0.03260 0.02566 -0.0213 1.0000 0.0584
-10.000 -0.9568 0.03080 0.02381 -0.0202 1.0000 0.0594
-9.750 -0.9361 0.02983 0.02285 -0.0193 1.0000 0.0605
-9.500 -0.9165 0.02873 0.02166 -0.0181 1.0000 0.0617
-9.250 -0.8973 0.02741 0.02017 -0.0169 1.0000 0.0631
-9.000 -0.8779 0.02598 0.01848 -0.0156 1.0000 0.0645
-8.750 -0.8575 0.02458 0.01688 -0.0144 1.0000 0.0659
-8.500 -0.8348 0.02368 0.01605 -0.0135 1.0000 0.0674
-8.250 -0.8121 0.02294 0.01530 -0.0125 1.0000 0.0694
-8.000 -0.7898 0.02210 0.01430 -0.0114 1.0000 0.0720
-7.750 -0.7672 0.02120 0.01338 -0.0103 1.0000 0.0746
-7.500 -0.7438 0.02067 0.01290 -0.0094 1.0000 0.0776
-7.250 -0.7208 0.01997 0.01200 -0.0082 1.0000 0.0818
-7.000 -0.6977 0.01934 0.01153 -0.0072 1.0000 0.0858
-6.750 -0.6746 0.01876 0.01084 -0.0061 1.0000 0.0923
-6.500 -0.6513 0.01841 0.01058 -0.0050 1.0000 0.0988
-6.250 -0.6284 0.01791 0.01010 -0.0039 1.0000 0.1061
-6.000 -0.6049 0.01773 0.00981 -0.0028 1.0000 0.1137
-5.750 -0.5818 0.01715 0.00937 -0.0018 1.0000 0.1198
-5.500 -0.5581 0.01694 0.00907 -0.0007 1.0000 0.1261
-5.250 -0.5349 0.01638 0.00860 0.0003 1.0000 0.1317
-5.000 -0.5112 0.01612 0.00836 0.0013 1.0000 0.1373
-4.750 -0.4875 0.01580 0.00797 0.0024 1.0000 0.1424
-4.500 -0.4643 0.01531 0.00761 0.0034 1.0000 0.1475
-4.250 -0.4409 0.01508 0.00740 0.0045 1.0000 0.1534
-4.000 -0.4180 0.01471 0.00707 0.0056 1.0000 0.1598
-3.750 -0.3953 0.01444 0.00691 0.0067 1.0000 0.1662
-3.500 -0.3387 0.01398 0.00646 0.0012 0.9716 0.1749
-3.250 -0.2744 0.01336 0.00592 -0.0057 0.8999 0.1842
-3.000 -0.2330 0.01320 0.00538 -0.0073 0.7495 0.1929
-2.750 -0.2112 0.01321 0.00505 -0.0054 0.6676 0.2007
-2.500 -0.1875 0.01315 0.00478 -0.0042 0.6245 0.2105
-2.250 -0.1632 0.01299 0.00454 -0.0032 0.5941 0.2248
-2.000 -0.1393 0.01272 0.00432 -0.0022 0.5691 0.2466
-1.750 -0.1158 0.01236 0.00415 -0.0012 0.5476 0.2937
-1.500 -0.0947 0.01178 0.00401 0.0002 0.5287 0.4046
-1.250 -0.0756 0.01119 0.00398 0.0022 0.5115 0.5469
-1.000 -0.0553 0.01083 0.00405 0.0043 0.4956 0.6683
-0.750 -0.0322 0.01070 0.00413 0.0062 0.4806 0.7524
-0.500 -0.0058 0.01070 0.00424 0.0075 0.4659 0.8181
-0.250 0.0273 0.01083 0.00438 0.0075 0.4502 0.8716
0.000 0.0661 0.01104 0.00453 0.0063 0.4339 0.9094
0.250 0.1046 0.01128 0.00467 0.0049 0.4181 0.9366
0.500 0.1496 0.01156 0.00480 0.0021 0.4024 0.9543
0.750 0.1987 0.01186 0.00494 -0.0016 0.3877 0.9689
1.000 0.2519 0.01215 0.00504 -0.0062 0.3739 0.9825
1.250 0.3158 0.01229 0.00508 -0.0131 0.3591 0.9971
1.500 0.3464 0.01240 0.00510 -0.0138 0.3496 1.0000
1.750 0.3677 0.01246 0.00508 -0.0126 0.3413 1.0000
2.000 0.3893 0.01259 0.00513 -0.0114 0.3331 1.0000
2.250 0.4112 0.01267 0.00516 -0.0102 0.3247 1.0000
2.500 0.4335 0.01289 0.00526 -0.0090 0.3183 1.0000
2.750 0.4562 0.01301 0.00540 -0.0079 0.3114 1.0000
3.000 0.4791 0.01318 0.00551 -0.0068 0.3053 1.0000
3.250 0.5021 0.01346 0.00571 -0.0058 0.2998 1.0000
3.500 0.5254 0.01361 0.00589 -0.0047 0.2935 1.0000
3.750 0.5488 0.01381 0.00603 -0.0037 0.2876 1.0000
4.000 0.5723 0.01411 0.00628 -0.0027 0.2820 1.0000
4.250 0.5960 0.01430 0.00650 -0.0017 0.2758 1.0000
4.500 0.6197 0.01452 0.00667 -0.0007 0.2701 1.0000
4.750 0.6434 0.01483 0.00697 0.0003 0.2640 1.0000
5.000 0.6672 0.01502 0.00718 0.0012 0.2572 1.0000
5.250 0.6909 0.01536 0.00740 0.0022 0.2510 1.0000
5.500 0.7146 0.01559 0.00774 0.0031 0.2441 1.0000
5.750 0.7384 0.01584 0.00794 0.0041 0.2372 1.0000
6.000 0.7619 0.01622 0.00833 0.0050 0.2300 1.0000
6.250 0.7855 0.01646 0.00858 0.0060 0.2223 1.0000
6.500 0.8087 0.01692 0.00899 0.0069 0.2152 1.0000
6.750 0.8322 0.01722 0.00935 0.0079 0.2076 1.0000
7.000 0.8555 0.01774 0.00976 0.0087 0.2012 1.0000
7.250 0.8786 0.01805 0.01020 0.0097 0.1940 1.0000
7.500 0.9021 0.01845 0.01054 0.0106 0.1883 1.0000
7.750 0.9251 0.01898 0.01115 0.0115 0.1825 1.0000
8.000 0.9484 0.01933 0.01154 0.0124 0.1769 1.0000
8.250 0.9717 0.01990 0.01198 0.0132 0.1721 1.0000
8.500 0.9941 0.02023 0.01250 0.0141 0.1665 1.0000
8.750 1.0171 0.02048 0.01273 0.0150 0.1612 1.0000
9.000 1.0394 0.02099 0.01325 0.0159 0.1562 1.0000
9.250 1.0615 0.02139 0.01376 0.0168 0.1512 1.0000
9.500 1.0837 0.02184 0.01416 0.0176 0.1470 1.0000
9.750 1.1049 0.02253 0.01491 0.0185 0.1429 1.0000
10.000 1.1259 0.02307 0.01557 0.0195 0.1385 1.0000
10.250 1.1470 0.02362 0.01608 0.0204 0.1346 1.0000
10.500 1.1667 0.02446 0.01697 0.0214 0.1306 1.0000
10.750 1.1856 0.02511 0.01776 0.0225 0.1264 1.0000
11.000 1.2049 0.02576 0.01837 0.0235 0.1224 1.0000
11.250 1.2222 0.02677 0.01944 0.0246 0.1186 1.0000
11.500 1.2381 0.02757 0.02040 0.0259 0.1145 1.0000
11.750 1.2552 0.02836 0.02114 0.0270 0.1107 1.0000
12.000 1.2682 0.02955 0.02243 0.0284 0.1069 1.0000
12.250 1.2794 0.03048 0.02351 0.0300 0.1029 1.0000
12.500 1.2933 0.03143 0.02438 0.0313 0.0994 1.0000
12.750 1.2984 0.03281 0.02592 0.0333 0.0961 1.0000
13.000 1.2992 0.03404 0.02729 0.0359 0.0932 1.0000
13.250 1.3045 0.03518 0.02843 0.0377 0.0905 1.0000
13.500 1.3109 0.03677 0.02998 0.0390 0.0879 1.0000
13.750 1.3019 0.03898 0.03244 0.0403 0.0860 1.0000
14.000 1.2968 0.04135 0.03498 0.0405 0.0839 1.0000
14.250 1.2973 0.04356 0.03724 0.0403 0.0819 1.0000
14.500 1.3075 0.04511 0.03868 0.0406 0.0798 1.0000
14.750 1.2962 0.04894 0.04271 0.0391 0.0784 1.0000
15.000 1.2813 0.05356 0.04758 0.0365 0.0772 1.0000
15.250 1.2679 0.05828 0.05248 0.0339 0.0759 1.0000
15.500 1.2567 0.06288 0.05722 0.0313 0.0747 1.0000
15.750 1.2519 0.06663 0.06103 0.0295 0.0734 1.0000
16.000 1.2602 0.06851 0.06285 0.0293 0.0721 1.0000
16.250 1.2540 0.07256 0.06696 0.0276 0.0709 1.0000
16.500 1.2198 0.08102 0.07569 0.0221 0.0705 1.0000
16.750 1.1711 0.09254 0.08751 0.0144 0.0703 1.0000
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