GOE 303 (FRIEDRICHSHAFEN G03) AIRFOIL (goe303-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 303 (FRIEDRICHSHAFEN G03) AIRFOIL (goe303-il) Reynolds number: 200,000 Max Cl/Cd: 83.22 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe303-il-200000.txt Download as CSV file: xf-goe303-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 303 (FRIEDRICHSHAFEN G03) 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
------ -------- --------- --------- -------- -------- --------
-8.500 -0.2962 0.10511 0.10178 -0.0275 1.0000 0.0421
-8.250 -0.3072 0.10389 0.10062 -0.0254 1.0000 0.0429
-8.000 -0.3236 0.10320 0.10001 -0.0230 1.0000 0.0436
-7.750 -0.3107 0.09945 0.09626 -0.0404 0.9901 0.0444
-7.500 -0.2951 0.09421 0.09103 -0.0391 0.9879 0.0450
-7.250 -0.2732 0.09037 0.08718 -0.0393 0.9856 0.0460
-7.000 -0.2487 0.08653 0.08333 -0.0437 0.9806 0.0476
-6.750 -0.2201 0.08218 0.07895 -0.0522 0.9742 0.0509
-6.500 -0.1806 0.07526 0.07191 -0.0720 0.9638 0.0534
-6.250 -0.1598 0.07177 0.06844 -0.0713 0.9609 0.0544
-6.000 -0.1286 0.06815 0.06479 -0.0754 0.9584 0.0563
-5.750 -0.0792 0.06352 0.05992 -0.0910 0.9480 0.0625
-5.500 -0.0476 0.05768 0.05403 -0.0969 0.9452 0.0641
-5.250 -0.0243 0.05498 0.05134 -0.0977 0.9391 0.0657
-5.000 0.0094 0.05179 0.04809 -0.1019 0.9338 0.0687
-4.750 0.0662 0.04595 0.04178 -0.1145 0.9300 0.0760
-4.500 0.0869 0.04347 0.03938 -0.1144 0.9214 0.0776
-4.250 0.1187 0.04112 0.03699 -0.1166 0.9161 0.0813
-4.000 0.1600 0.03755 0.03290 -0.1219 0.9077 0.0901
-3.750 0.1866 0.03499 0.03038 -0.1228 0.9004 0.0921
-3.500 0.2132 0.03315 0.02847 -0.1234 0.8909 0.0956
-3.250 0.2490 0.03071 0.02560 -0.1257 0.8829 0.1061
-3.000 0.2718 0.02907 0.02399 -0.1253 0.8713 0.1096
-2.750 0.3034 0.02753 0.02207 -0.1262 0.8618 0.1221
-2.500 0.3397 0.02163 0.01525 -0.1266 0.8523 0.0774
-2.250 0.3681 0.01972 0.01302 -0.1262 0.8410 0.0708
-2.000 0.3974 0.01832 0.01129 -0.1260 0.8310 0.0706
-1.750 0.4257 0.01718 0.00988 -0.1255 0.8194 0.0707
-1.500 0.4534 0.01621 0.00868 -0.1251 0.8071 0.0706
-1.250 0.4815 0.01546 0.00773 -0.1246 0.7957 0.0715
-1.000 0.5100 0.01486 0.00696 -0.1243 0.7848 0.0732
-0.750 0.5374 0.01429 0.00628 -0.1238 0.7725 0.0763
-0.500 0.5642 0.01388 0.00588 -0.1234 0.7595 0.0814
-0.250 0.5914 0.01357 0.00548 -0.1228 0.7465 0.0871
0.000 0.6184 0.01317 0.00508 -0.1224 0.7340 0.0974
0.250 0.6456 0.01283 0.00477 -0.1220 0.7221 0.1293
0.500 0.6721 0.01256 0.00466 -0.1216 0.7095 0.1929
0.750 0.7009 0.01069 0.00464 -0.1218 0.6971 1.0000
1.000 0.7277 0.01085 0.00457 -0.1213 0.6851 1.0000
1.250 0.7549 0.01102 0.00453 -0.1209 0.6746 1.0000
1.500 0.7812 0.01118 0.00459 -0.1205 0.6634 1.0000
1.750 0.8080 0.01136 0.00465 -0.1201 0.6535 1.0000
2.000 0.8350 0.01154 0.00470 -0.1198 0.6441 1.0000
2.250 0.8613 0.01171 0.00482 -0.1194 0.6340 1.0000
2.500 0.8883 0.01191 0.00491 -0.1191 0.6252 1.0000
2.750 0.9144 0.01208 0.00504 -0.1187 0.6150 1.0000
3.000 0.9407 0.01227 0.00516 -0.1183 0.6053 1.0000
3.250 0.9671 0.01246 0.00526 -0.1179 0.5955 1.0000
3.500 0.9926 0.01263 0.00543 -0.1174 0.5845 1.0000
3.750 1.0185 0.01283 0.00558 -0.1169 0.5742 1.0000
4.000 1.0444 0.01303 0.00571 -0.1165 0.5638 1.0000
4.250 1.0695 0.01322 0.00592 -0.1159 0.5524 1.0000
4.500 1.0947 0.01343 0.00610 -0.1153 0.5412 1.0000
4.750 1.1198 0.01365 0.00626 -0.1148 0.5297 1.0000
5.000 1.1441 0.01386 0.00648 -0.1140 0.5166 1.0000
5.250 1.1680 0.01408 0.00669 -0.1133 0.5023 1.0000
5.500 1.1914 0.01432 0.00691 -0.1124 0.4869 1.0000
5.750 1.2142 0.01459 0.00714 -0.1114 0.4703 1.0000
6.000 1.2364 0.01490 0.00741 -0.1104 0.4526 1.0000
6.250 1.2579 0.01524 0.00772 -0.1092 0.4329 1.0000
6.500 1.2787 0.01563 0.00807 -0.1079 0.4123 1.0000
6.750 1.2987 0.01610 0.00845 -0.1066 0.3922 1.0000
7.000 1.3180 0.01663 0.00886 -0.1051 0.3737 1.0000
7.250 1.3377 0.01716 0.00931 -0.1038 0.3571 1.0000
7.500 1.3574 0.01771 0.00980 -0.1025 0.3431 1.0000
7.750 1.3774 0.01822 0.01032 -0.1013 0.3303 1.0000
8.000 1.3973 0.01875 0.01086 -0.1001 0.3192 1.0000
8.250 1.4166 0.01934 0.01140 -0.0988 0.3096 1.0000
8.500 1.4362 0.01987 0.01196 -0.0976 0.3007 1.0000
8.750 1.4561 0.02047 0.01258 -0.0964 0.2934 1.0000
9.000 1.4752 0.02101 0.01318 -0.0951 0.2858 1.0000
9.250 1.4940 0.02164 0.01382 -0.0938 0.2787 1.0000
9.500 1.5113 0.02218 0.01447 -0.0923 0.2711 1.0000
9.750 1.5278 0.02284 0.01514 -0.0906 0.2635 1.0000
10.000 1.5403 0.02339 0.01579 -0.0883 0.2552 1.0000
10.250 1.5519 0.02406 0.01651 -0.0859 0.2465 1.0000
10.500 1.5616 0.02478 0.01724 -0.0833 0.2371 1.0000
10.750 1.5711 0.02546 0.01809 -0.0807 0.2274 1.0000
11.000 1.5795 0.02634 0.01900 -0.0782 0.2180 1.0000
11.250 1.5866 0.02726 0.02000 -0.0757 0.2072 1.0000
11.500 1.5939 0.02823 0.02110 -0.0734 0.1947 1.0000
11.750 1.6004 0.02936 0.02232 -0.0712 0.1809 1.0000
12.000 1.6053 0.03071 0.02372 -0.0691 0.1649 1.0000
12.250 1.6078 0.03236 0.02538 -0.0670 0.1466 1.0000
12.500 1.6071 0.03441 0.02738 -0.0648 0.1299 1.0000
12.750 1.6043 0.03677 0.02971 -0.0628 0.1173 1.0000
13.000 1.6004 0.03936 0.03230 -0.0609 0.1077 1.0000
13.250 1.5948 0.04225 0.03519 -0.0593 0.0996 1.0000
13.500 1.5918 0.04502 0.03805 -0.0580 0.0919 1.0000
13.750 1.5832 0.04848 0.04153 -0.0568 0.0856 1.0000
14.000 1.5781 0.05174 0.04489 -0.0560 0.0781 1.0000
14.250 1.5696 0.05551 0.04874 -0.0554 0.0710 1.0000
14.500 1.5565 0.05999 0.05324 -0.0551 0.0648 1.0000
14.750 1.5473 0.06423 0.05758 -0.0550 0.0574 1.0000
15.000 1.5328 0.06920 0.06260 -0.0552 0.0527 1.0000
15.250 1.5228 0.07378 0.06727 -0.0555 0.0482 1.0000
15.500 1.5074 0.07911 0.07261 -0.0561 0.0456 1.0000
15.750 1.5007 0.08342 0.07707 -0.0567 0.0426 1.0000
16.000 1.4921 0.08804 0.08178 -0.0574 0.0404 1.0000
16.250 1.4813 0.09300 0.08677 -0.0584 0.0387 1.0000
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Polar data table (+)
Polar graphs
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