GOE 547 AIRFOIL (goe547-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 547 AIRFOIL (goe547-il) Reynolds number: 200,000 Max Cl/Cd: 86.86 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe547-il-200000.txt Download as CSV file: xf-goe547-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 547 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
------ -------- --------- --------- -------- -------- --------
-9.000 -0.3910 0.10158 0.09820 -0.0346 1.0000 0.0597
-8.750 -0.3994 0.09981 0.09648 -0.0327 1.0000 0.0609
-8.500 -0.4099 0.09801 0.09474 -0.0309 1.0000 0.0620
-8.250 -0.3094 0.07999 0.07689 -0.0489 0.9862 0.0694
-8.000 -0.2873 0.07687 0.07374 -0.0500 0.9842 0.0721
-7.750 -0.2823 0.07290 0.06977 -0.0524 0.9789 0.0744
-7.500 -0.2819 0.06767 0.06455 -0.0577 0.9739 0.0777
-7.250 -0.3151 0.05651 0.05319 -0.0789 0.9605 0.0805
-7.000 -0.3100 0.04942 0.04612 -0.0809 0.9560 0.0819
-6.750 -0.2906 0.04756 0.04432 -0.0788 0.9513 0.0833
-6.500 -0.2685 0.04463 0.04136 -0.0802 0.9479 0.0859
-6.250 -0.2591 0.03864 0.03515 -0.0865 0.9414 0.0923
-6.000 -0.2489 0.03261 0.02887 -0.0907 0.9351 0.0981
-5.750 -0.2242 0.02790 0.02366 -0.0960 0.9318 0.1106
-5.500 -0.2504 0.03247 0.02676 -0.0947 0.9344 0.0656
-5.250 -0.2184 0.02873 0.02260 -0.0969 0.9322 0.0632
-5.000 -0.1974 0.02695 0.02046 -0.0960 0.9252 0.0637
-4.750 -0.1662 0.02485 0.01799 -0.0969 0.9214 0.0631
-4.500 -0.1305 0.02310 0.01591 -0.0985 0.9191 0.0630
-4.250 -0.0920 0.02169 0.01421 -0.1005 0.9174 0.0636
-4.000 -0.0708 0.02096 0.01332 -0.0992 0.9097 0.0647
-3.750 -0.0344 0.02028 0.01244 -0.1006 0.9065 0.0668
-3.500 0.0035 0.01892 0.01100 -0.1026 0.9046 0.0684
-3.250 0.0429 0.01777 0.00988 -0.1049 0.9032 0.0713
-3.000 0.0662 0.01729 0.00941 -0.1039 0.8961 0.0745
-2.750 0.1016 0.01667 0.00875 -0.1053 0.8924 0.0794
-2.500 0.1397 0.01577 0.00793 -0.1074 0.8901 0.0900
-2.250 0.1775 0.01473 0.00705 -0.1094 0.8881 0.1264
-2.000 0.1962 0.01409 0.00701 -0.1079 0.8798 0.2653
-1.750 0.2299 0.01356 0.00680 -0.1091 0.8760 0.3623
-1.500 0.2664 0.01306 0.00661 -0.1108 0.8733 0.4645
-1.250 0.2863 0.01291 0.00671 -0.1090 0.8653 0.5417
-1.000 0.3160 0.01250 0.00658 -0.1091 0.8608 0.6314
-0.750 0.3493 0.01189 0.00636 -0.1096 0.8578 0.7387
-0.500 0.4561 0.01131 0.00613 -0.1259 0.8595 1.0000
-0.250 0.4806 0.01138 0.00609 -0.1252 0.8522 1.0000
0.000 0.5093 0.01137 0.00598 -0.1253 0.8458 1.0000
0.250 0.5422 0.01133 0.00583 -0.1262 0.8410 1.0000
0.500 0.5619 0.01147 0.00592 -0.1245 0.8321 1.0000
0.750 0.5956 0.01141 0.00578 -0.1255 0.8276 1.0000
1.000 0.6146 0.01158 0.00591 -0.1236 0.8185 1.0000
1.250 0.6484 0.01146 0.00571 -0.1245 0.8127 1.0000
1.500 0.6691 0.01150 0.00571 -0.1228 0.8019 1.0000
1.750 0.6960 0.01141 0.00557 -0.1222 0.7922 1.0000
2.000 0.7264 0.01126 0.00534 -0.1222 0.7827 1.0000
2.250 0.7474 0.01130 0.00537 -0.1206 0.7716 1.0000
2.500 0.7731 0.01132 0.00536 -0.1198 0.7627 1.0000
2.750 0.8001 0.01132 0.00533 -0.1194 0.7539 1.0000
3.000 0.8222 0.01141 0.00543 -0.1181 0.7441 1.0000
3.250 0.8503 0.01144 0.00544 -0.1179 0.7363 1.0000
3.500 0.8727 0.01154 0.00557 -0.1166 0.7265 1.0000
3.750 0.8970 0.01162 0.00566 -0.1157 0.7172 1.0000
4.000 0.9243 0.01166 0.00568 -0.1153 0.7079 1.0000
4.250 0.9457 0.01176 0.00584 -0.1138 0.6964 1.0000
4.500 0.9686 0.01184 0.00593 -0.1126 0.6838 1.0000
4.750 0.9914 0.01191 0.00601 -0.1113 0.6699 1.0000
5.000 1.0142 0.01202 0.00614 -0.1100 0.6564 1.0000
5.250 1.0358 0.01213 0.00626 -0.1085 0.6402 1.0000
5.500 1.0568 0.01226 0.00639 -0.1068 0.6225 1.0000
5.750 1.0770 0.01241 0.00651 -0.1050 0.6021 1.0000
6.000 1.0936 0.01259 0.00669 -0.1025 0.5769 1.0000
6.250 1.1088 0.01281 0.00688 -0.0997 0.5465 1.0000
6.500 1.1206 0.01311 0.00707 -0.0963 0.5044 1.0000
6.750 1.1276 0.01363 0.00733 -0.0921 0.4494 1.0000
7.000 1.1318 0.01435 0.00775 -0.0876 0.3964 1.0000
7.250 1.1341 0.01517 0.00829 -0.0828 0.3503 1.0000
7.500 1.1375 0.01600 0.00892 -0.0784 0.3102 1.0000
7.750 1.1428 0.01684 0.00959 -0.0745 0.2762 1.0000
8.000 1.1495 0.01768 0.01028 -0.0710 0.2410 1.0000
8.250 1.1555 0.01862 0.01104 -0.0676 0.2032 1.0000
8.500 1.1607 0.01968 0.01187 -0.0642 0.1568 1.0000
8.750 1.1632 0.02100 0.01292 -0.0607 0.1231 1.0000
9.000 1.1670 0.02234 0.01413 -0.0574 0.0947 1.0000
9.250 1.1663 0.02409 0.01560 -0.0536 0.0599 1.0000
9.500 1.1668 0.02579 0.01727 -0.0501 0.0491 1.0000
9.750 1.1677 0.02752 0.01900 -0.0469 0.0435 1.0000
10.000 1.1762 0.02878 0.02035 -0.0447 0.0395 1.0000
10.250 1.1802 0.03043 0.02201 -0.0422 0.0369 1.0000
10.500 1.1843 0.03223 0.02386 -0.0397 0.0352 1.0000
10.750 1.1940 0.03366 0.02539 -0.0378 0.0337 1.0000
11.000 1.2038 0.03517 0.02700 -0.0361 0.0322 1.0000
11.250 1.2141 0.03667 0.02855 -0.0344 0.0308 1.0000
11.500 1.2246 0.03826 0.03015 -0.0330 0.0296 1.0000
11.750 1.2397 0.04023 0.03215 -0.0317 0.0281 1.0000
12.000 1.2541 0.04181 0.03388 -0.0304 0.0272 1.0000
12.250 1.2698 0.04359 0.03583 -0.0293 0.0266 1.0000
12.500 1.2853 0.04561 0.03805 -0.0281 0.0261 1.0000
12.750 1.2981 0.04786 0.04051 -0.0269 0.0256 1.0000
13.000 1.3079 0.05043 0.04332 -0.0256 0.0253 1.0000
13.250 1.3129 0.05331 0.04645 -0.0240 0.0251 1.0000
13.500 1.3137 0.05618 0.04956 -0.0225 0.0248 1.0000
13.750 1.3120 0.05914 0.05274 -0.0211 0.0245 1.0000
14.000 1.3096 0.06212 0.05589 -0.0199 0.0241 1.0000
14.250 1.2987 0.06610 0.06016 -0.0187 0.0241 1.0000
14.500 1.2881 0.06998 0.06428 -0.0179 0.0240 1.0000
14.750 1.2817 0.07343 0.06785 -0.0176 0.0236 1.0000
15.000 1.2603 0.07881 0.07355 -0.0177 0.0239 1.0000
15.250 1.2474 0.08338 0.07830 -0.0183 0.0236 1.0000
15.500 1.2000 0.09317 0.08859 -0.0213 0.0246 1.0000
15.750 1.1714 0.10112 0.09680 -0.0247 0.0249 1.0000
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Polar data table (+)
Polar graphs
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