GOE 703 AIRFOIL (goe703-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 703 AIRFOIL (goe703-il) Reynolds number: 100,000 Max Cl/Cd: 40 at α=9.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe703-il-100000.txt Download as CSV file: xf-goe703-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 703 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
------ -------- --------- --------- -------- -------- --------
-12.750 -0.6190 0.07573 0.06966 -0.0769 1.0000 0.0974
-12.500 -0.6440 0.07119 0.06508 -0.0759 1.0000 0.0968
-12.250 -0.6779 0.06698 0.06077 -0.0736 1.0000 0.0961
-12.000 -0.7147 0.06347 0.05715 -0.0695 1.0000 0.0954
-11.750 -0.7529 0.06078 0.05434 -0.0638 1.0000 0.0950
-11.500 -0.7907 0.05887 0.05234 -0.0568 1.0000 0.0945
-11.250 -0.8290 0.05757 0.05095 -0.0488 1.0000 0.0941
-11.000 -0.8674 0.05658 0.04987 -0.0402 1.0000 0.0938
-10.750 -0.9052 0.05569 0.04886 -0.0314 1.0000 0.0933
-10.500 -0.9377 0.05446 0.04749 -0.0233 1.0000 0.0931
-10.250 -0.9640 0.05302 0.04586 -0.0161 1.0000 0.0929
-10.000 -0.9616 0.05025 0.04273 -0.0143 0.9941 0.0932
-9.750 -0.9444 0.04742 0.03948 -0.0146 0.9847 0.0944
-9.500 -0.9244 0.04499 0.03662 -0.0149 0.9755 0.0959
-9.250 -0.9022 0.04272 0.03380 -0.0152 0.9667 0.0975
-9.000 -0.8685 0.04086 0.03195 -0.0173 0.9579 0.0996
-8.750 -0.8246 0.03917 0.03017 -0.0210 0.9520 0.1024
-8.500 -0.7954 0.03769 0.02847 -0.0218 0.9419 0.1051
-8.250 -0.7501 0.03592 0.02653 -0.0256 0.9364 0.1093
-8.000 -0.7167 0.03493 0.02559 -0.0272 0.9272 0.1138
-7.750 -0.6710 0.03346 0.02401 -0.0308 0.9209 0.1204
-7.500 -0.6175 0.03209 0.02259 -0.0358 0.9171 0.1296
-7.250 -0.5912 0.03126 0.02193 -0.0360 0.9058 0.1380
-7.000 -0.5454 0.03002 0.02075 -0.0396 0.9009 0.1540
-6.750 -0.5185 0.02921 0.01994 -0.0397 0.8920 0.1724
-6.500 -0.4870 0.02825 0.01922 -0.0407 0.8841 0.1956
-6.250 -0.4460 0.02725 0.01826 -0.0434 0.8797 0.2258
-6.000 -0.4395 0.02718 0.01816 -0.0395 0.8667 0.2419
-5.750 -0.3999 0.02632 0.01743 -0.0419 0.8614 0.2664
-5.500 -0.3534 0.02538 0.01658 -0.0455 0.8578 0.2930
-5.250 -0.3498 0.02541 0.01664 -0.0411 0.8441 0.3070
-5.000 -0.3053 0.02447 0.01583 -0.0443 0.8395 0.3361
-4.750 -0.2884 0.02422 0.01570 -0.0424 0.8299 0.3595
-4.500 -0.2584 0.02357 0.01530 -0.0429 0.8223 0.3926
-4.250 -0.2104 0.02245 0.01453 -0.0467 0.8179 0.4468
-4.000 -0.1780 0.02179 0.01449 -0.0475 0.8101 0.5257
-3.750 -0.0250 0.02288 0.01640 -0.0665 0.8093 0.7192
-3.500 0.0129 0.02406 0.01747 -0.0662 0.8010 0.7548
-3.250 0.0752 0.02531 0.01851 -0.0699 0.7957 0.7760
-3.000 0.1075 0.02653 0.01965 -0.0693 0.7860 0.7942
-2.750 0.1545 0.02735 0.02031 -0.0713 0.7787 0.8114
-2.500 0.2053 0.02792 0.02069 -0.0743 0.7730 0.8279
-2.250 0.2529 0.02878 0.02150 -0.0770 0.7630 0.8397
-2.000 0.3086 0.02910 0.02166 -0.0811 0.7561 0.8534
-1.750 0.3493 0.02942 0.02189 -0.0831 0.7486 0.8682
-1.500 0.3820 0.02976 0.02218 -0.0838 0.7399 0.8836
-1.250 0.4411 0.02955 0.02181 -0.0892 0.7335 0.8962
-1.000 0.4807 0.02960 0.02184 -0.0915 0.7245 0.9093
-0.750 0.5241 0.02939 0.02154 -0.0944 0.7168 0.9234
-0.500 0.5788 0.02898 0.02099 -0.0994 0.7104 0.9401
-0.250 0.6291 0.02869 0.02073 -0.1041 0.7009 0.9632
0.000 0.7441 0.02589 0.01776 -0.1211 0.6930 1.0000
0.250 0.7541 0.02612 0.01802 -0.1187 0.6850 1.0000
0.500 0.7692 0.02615 0.01801 -0.1171 0.6775 1.0000
0.750 0.7915 0.02601 0.01775 -0.1165 0.6718 1.0000
1.000 0.7986 0.02641 0.01823 -0.1136 0.6633 1.0000
1.250 0.8156 0.02645 0.01823 -0.1121 0.6562 1.0000
1.500 0.8395 0.02635 0.01801 -0.1117 0.6509 1.0000
1.750 0.8438 0.02690 0.01867 -0.1082 0.6417 1.0000
2.000 0.8624 0.02694 0.01868 -0.1070 0.6351 1.0000
2.250 0.8833 0.02701 0.01867 -0.1060 0.6292 1.0000
2.500 0.8890 0.02756 0.01932 -0.1027 0.6202 1.0000
2.750 0.9096 0.02759 0.01931 -0.1016 0.6139 1.0000
3.000 0.9267 0.02786 0.01955 -0.1000 0.6077 1.0000
3.250 0.9334 0.02844 0.02022 -0.0968 0.5991 1.0000
3.500 0.9558 0.02842 0.02015 -0.0960 0.5930 1.0000
3.750 0.9690 0.02886 0.02061 -0.0937 0.5861 1.0000
4.000 0.9765 0.02945 0.02128 -0.0906 0.5780 1.0000
4.250 1.0015 0.02934 0.02109 -0.0901 0.5721 1.0000
4.500 1.0090 0.02996 0.02180 -0.0869 0.5643 1.0000
4.750 1.0217 0.03022 0.02208 -0.0845 0.5561 1.0000
5.000 1.0571 0.02958 0.02127 -0.0853 0.5499 1.0000
5.250 1.0515 0.03044 0.02230 -0.0800 0.5395 1.0000
5.500 1.0846 0.02964 0.02136 -0.0803 0.5317 1.0000
5.750 1.0867 0.03019 0.02201 -0.0761 0.5221 1.0000
6.000 1.1092 0.02992 0.02169 -0.0749 0.5144 1.0000
6.250 1.1284 0.03000 0.02175 -0.0734 0.5078 1.0000
6.500 1.1292 0.03067 0.02255 -0.0690 0.4994 1.0000
6.750 1.1587 0.03027 0.02205 -0.0691 0.4932 1.0000
7.000 1.1592 0.03099 0.02289 -0.0646 0.4853 1.0000
7.250 1.1726 0.03111 0.02304 -0.0622 0.4778 1.0000
7.500 1.2057 0.03067 0.02248 -0.0627 0.4716 1.0000
7.750 1.1919 0.03173 0.02374 -0.0561 0.4629 1.0000
8.000 1.2202 0.03133 0.02328 -0.0558 0.4561 1.0000
8.250 1.2202 0.03197 0.02400 -0.0513 0.4485 1.0000
8.500 1.2282 0.03219 0.02426 -0.0479 0.4406 1.0000
8.750 1.2540 0.03196 0.02396 -0.0473 0.4332 1.0000
9.000 1.2402 0.03280 0.02494 -0.0406 0.4250 1.0000
9.250 1.2820 0.03205 0.02403 -0.0424 0.4166 1.0000
9.500 1.2527 0.03321 0.02538 -0.0333 0.4085 1.0000
9.750 1.2930 0.03242 0.02440 -0.0348 0.3986 1.0000
10.000 1.2565 0.03356 0.02572 -0.0245 0.3911 1.0000
10.250 1.2910 0.03297 0.02496 -0.0251 0.3802 1.0000
10.500 1.2480 0.03402 0.02617 -0.0138 0.3740 1.0000
10.750 1.2778 0.03355 0.02550 -0.0136 0.3625 1.0000
11.000 1.2380 0.03480 0.02692 -0.0036 0.3557 1.0000
11.250 1.2617 0.03453 0.02647 -0.0025 0.3445 1.0000
11.500 1.2292 0.03593 0.02800 0.0057 0.3367 1.0000
11.750 1.2461 0.03597 0.02790 0.0075 0.3263 1.0000
12.000 1.2226 0.03741 0.02944 0.0138 0.3180 1.0000
12.250 1.2359 0.03774 0.02965 0.0158 0.3085 1.0000
12.500 1.2173 0.03931 0.03131 0.0210 0.3005 1.0000
12.750 1.2307 0.03968 0.03155 0.0229 0.2916 1.0000
13.000 1.2100 0.04157 0.03354 0.0277 0.2843 1.0000
13.250 1.2324 0.04161 0.03342 0.0287 0.2759 1.0000
13.500 1.2057 0.04410 0.03609 0.0334 0.2700 1.0000
13.750 1.2212 0.04441 0.03630 0.0348 0.2625 1.0000
14.000 1.2095 0.04639 0.03836 0.0379 0.2567 1.0000
14.250 1.1975 0.04846 0.04051 0.0407 0.2507 1.0000
14.500 1.2267 0.04807 0.03993 0.0413 0.2436 1.0000
14.750 1.1960 0.05155 0.04365 0.0446 0.2393 1.0000
15.000 1.1908 0.05348 0.04564 0.0465 0.2338 1.0000
15.250 1.2176 0.05318 0.04518 0.0473 0.2274 1.0000
15.500 1.1833 0.05746 0.04972 0.0497 0.2234 1.0000
15.750 1.1787 0.05955 0.05185 0.0511 0.2179 1.0000
16.000 1.2027 0.05933 0.05150 0.0520 0.2115 1.0000
16.250 1.1629 0.06476 0.05720 0.0535 0.2077 1.0000
16.500 1.1743 0.06546 0.05786 0.0544 0.2012 1.0000
16.750 1.1738 0.06752 0.05994 0.0554 0.1955 1.0000
17.000 1.1284 0.07437 0.06704 0.0556 0.1914 1.0000
17.250 0.8381 0.12014 0.11335 0.0425 0.1836 1.0000
17.500 0.9268 0.10713 0.10031 0.0481 0.1823 1.0000
17.750 1.1815 0.07483 0.06717 0.0584 0.1688 1.0000
18.000 1.1142 0.08481 0.07755 0.0572 0.1660 1.0000
18.250 0.6468 0.17371 0.16691 0.0224 0.1517 1.0000
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