GOE 155 (SSW D.1) AIRFOIL (goe155-il) Xfoil prediction polar at RE=50,000 Ncrit=5
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Airfoil: GOE 155 (SSW D.1) AIRFOIL (goe155-il) Reynolds number: 50,000 Max Cl/Cd: 42.36 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe155-il-50000-n5.txt Download as CSV file: xf-goe155-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 155 (SSW D.1) AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.500 -0.2999 0.10021 0.09397 -0.0277 1.0000 0.0825
-7.250 -0.3036 0.09870 0.09257 -0.0278 1.0000 0.0850
-7.000 -0.3118 0.09809 0.09209 -0.0283 1.0000 0.0868
-6.750 -0.3201 0.09788 0.09198 -0.0299 1.0000 0.0877
-6.500 -0.3239 0.09637 0.09056 -0.0307 1.0000 0.0883
-6.250 -0.3239 0.09200 0.08625 -0.0255 1.0000 0.0901
-6.000 -0.3252 0.08965 0.08395 -0.0236 1.0000 0.0923
-5.750 -0.3225 0.08736 0.08170 -0.0239 0.9991 0.0952
-5.500 -0.2814 0.08406 0.07824 -0.0390 0.9893 0.1015
-5.250 -0.2686 0.07925 0.07347 -0.0364 0.9849 0.1072
-4.750 -0.2109 0.07174 0.06578 -0.0481 0.9707 0.1237
-4.500 -0.1744 0.06775 0.06162 -0.0559 0.9646 0.1316
-4.250 -0.1366 0.06478 0.05843 -0.0638 0.9568 0.1437
-3.500 -0.0466 0.05456 0.04789 -0.0744 0.9388 0.1889
-3.250 0.0285 0.04779 0.04011 -0.0869 0.9339 0.0888
-3.000 0.0620 0.04497 0.03701 -0.0896 0.9270 0.0867
-2.750 0.1030 0.04187 0.03363 -0.0937 0.9223 0.0831
-2.500 0.1423 0.03893 0.03007 -0.0967 0.9146 0.0769
-2.250 0.1841 0.03652 0.02720 -0.0998 0.9084 0.0746
-2.000 0.2179 0.03462 0.02491 -0.1013 0.8996 0.0739
-1.750 0.2586 0.03278 0.02256 -0.1038 0.8928 0.0765
-1.500 0.2886 0.03151 0.02107 -0.1044 0.8831 0.0783
-1.250 0.3282 0.02998 0.01910 -0.1062 0.8769 0.0780
-1.000 0.3563 0.02905 0.01786 -0.1061 0.8670 0.0782
-0.750 0.3894 0.02808 0.01663 -0.1067 0.8596 0.0791
-0.500 0.4209 0.02738 0.01565 -0.1069 0.8508 0.0805
-0.250 0.4521 0.02677 0.01481 -0.1071 0.8422 0.0826
0.000 0.4847 0.02618 0.01401 -0.1074 0.8343 0.0867
0.250 0.5117 0.02583 0.01368 -0.1071 0.8241 0.0941
0.500 0.5426 0.02540 0.01318 -0.1072 0.8158 0.1031
0.750 0.5707 0.02511 0.01288 -0.1069 0.8056 0.1145
1.000 0.5979 0.02482 0.01273 -0.1065 0.7948 0.1454
1.250 0.6279 0.02271 0.01234 -0.1065 0.7862 1.0000
1.500 0.6546 0.02284 0.01218 -0.1057 0.7749 1.0000
1.750 0.6800 0.02301 0.01217 -0.1048 0.7624 1.0000
2.000 0.7058 0.02312 0.01212 -0.1039 0.7497 1.0000
2.250 0.7318 0.02311 0.01200 -0.1028 0.7356 1.0000
2.500 0.7574 0.02307 0.01184 -0.1016 0.7203 1.0000
2.750 0.7827 0.02303 0.01171 -0.1003 0.7041 1.0000
3.000 0.8077 0.02302 0.01165 -0.0991 0.6878 1.0000
3.250 0.8325 0.02305 0.01164 -0.0979 0.6714 1.0000
3.500 0.8573 0.02313 0.01168 -0.0968 0.6551 1.0000
3.750 0.8821 0.02322 0.01179 -0.0958 0.6388 1.0000
4.000 0.9063 0.02338 0.01195 -0.0947 0.6217 1.0000
4.250 0.9299 0.02362 0.01222 -0.0937 0.6034 1.0000
4.500 0.9540 0.02382 0.01245 -0.0927 0.5854 1.0000
4.750 0.9785 0.02402 0.01269 -0.0917 0.5678 1.0000
5.000 1.0031 0.02424 0.01292 -0.0907 0.5505 1.0000
5.250 1.0273 0.02454 0.01322 -0.0898 0.5329 1.0000
5.500 1.0508 0.02496 0.01372 -0.0888 0.5148 1.0000
5.750 1.0745 0.02541 0.01421 -0.0879 0.4978 1.0000
6.000 1.0983 0.02593 0.01479 -0.0871 0.4821 1.0000
6.250 1.1221 0.02652 0.01546 -0.0863 0.4673 1.0000
6.500 1.1457 0.02717 0.01625 -0.0855 0.4532 1.0000
6.750 1.1695 0.02786 0.01706 -0.0848 0.4403 1.0000
7.000 1.1933 0.02856 0.01789 -0.0841 0.4279 1.0000
7.250 1.2135 0.02928 0.01877 -0.0829 0.4108 1.0000
7.500 1.2312 0.02996 0.01960 -0.0813 0.3909 1.0000
7.750 1.2480 0.03059 0.02041 -0.0796 0.3710 1.0000
8.000 1.2598 0.03131 0.02130 -0.0774 0.3462 1.0000
8.250 1.2655 0.03211 0.02212 -0.0745 0.3123 1.0000
8.500 1.2690 0.03323 0.02323 -0.0715 0.2738 1.0000
8.750 1.2680 0.03488 0.02470 -0.0684 0.2240 1.0000
9.250 1.2446 0.04119 0.02983 -0.0620 0.0847 1.0000
9.500 1.2369 0.04466 0.03322 -0.0599 0.0730 1.0000
9.750 1.2337 0.04773 0.03645 -0.0583 0.0650 1.0000
10.000 1.2271 0.05125 0.04014 -0.0570 0.0608 1.0000
10.250 1.2219 0.05474 0.04379 -0.0560 0.0579 1.0000
10.500 1.2178 0.05822 0.04748 -0.0552 0.0549 1.0000
10.750 1.2125 0.06192 0.05134 -0.0548 0.0521 1.0000
11.000 1.2061 0.06584 0.05537 -0.0545 0.0497 1.0000
11.250 1.1993 0.06983 0.05940 -0.0542 0.0477 1.0000
11.500 1.1996 0.07299 0.06279 -0.0536 0.0457 1.0000
11.750 1.2020 0.07582 0.06581 -0.0525 0.0441 1.0000
12.000 1.2071 0.07832 0.06846 -0.0511 0.0423 1.0000
12.250 1.2132 0.08074 0.07101 -0.0498 0.0401 1.0000
12.500 1.2307 0.08186 0.07205 -0.0467 0.0371 1.0000
12.750 1.2399 0.08452 0.07511 -0.0455 0.0358 1.0000
13.000 1.2499 0.08739 0.07832 -0.0442 0.0350 1.0000
13.250 1.2529 0.09115 0.08240 -0.0438 0.0344 1.0000
13.500 1.2496 0.09563 0.08718 -0.0442 0.0340 1.0000
13.750 1.2422 0.10065 0.09249 -0.0453 0.0337 1.0000
14.000 1.2318 0.10619 0.09829 -0.0472 0.0335 1.0000
14.250 1.2196 0.11223 0.10459 -0.0497 0.0334 1.0000
14.500 1.2062 0.11882 0.11142 -0.0530 0.0334 1.0000
14.750 1.1917 0.12605 0.11886 -0.0570 0.0335 1.0000
15.000 1.1767 0.13390 0.12689 -0.0617 0.0337 1.0000
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Polar data table (+)
Polar graphs
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