GOE 610-B MOD. AIRFOIL (goe610bm-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
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Airfoil: GOE 610-B MOD. AIRFOIL (goe610bm-il) Reynolds number: 1,000,000 Max Cl/Cd: 130.29 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe610bm-il-1000000.txt Download as CSV file: xf-goe610bm-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 610-B MOD. AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.3261 0.10325 0.10173 -0.0209 1.0000 0.0096
-8.250 -0.3195 0.09983 0.09832 -0.0229 1.0000 0.0097
-8.000 -0.3132 0.09638 0.09489 -0.0250 1.0000 0.0097
-7.750 -0.3053 0.09181 0.09033 -0.0271 0.9876 0.0100
-7.500 -0.2916 0.08885 0.08736 -0.0297 0.9712 0.0103
-7.250 -0.2841 0.08627 0.08475 -0.0309 0.9525 0.0105
-7.000 -0.2758 0.08356 0.08201 -0.0326 0.9370 0.0109
-6.750 -0.2640 0.08047 0.07887 -0.0355 0.9238 0.0114
-6.500 -0.2496 0.07702 0.07537 -0.0391 0.9115 0.0122
-6.250 -0.2242 0.07217 0.07046 -0.0482 0.8989 0.0131
-6.000 -0.2014 0.06795 0.06618 -0.0540 0.8876 0.0132
-5.750 -0.1775 0.06349 0.06167 -0.0597 0.8771 0.0132
-5.500 -0.1516 0.05879 0.05688 -0.0656 0.8665 0.0133
-5.250 -0.1231 0.05108 0.04906 -0.0747 0.8556 0.0136
-5.000 -0.1014 0.04926 0.04717 -0.0762 0.8437 0.0140
-4.750 -0.0748 0.04688 0.04471 -0.0792 0.8316 0.0148
-4.500 -0.0302 0.04206 0.03969 -0.0864 0.8198 0.0176
-4.000 0.0376 0.03082 0.02798 -0.0968 0.7965 0.0159
-3.750 0.0920 0.01591 0.01173 -0.1051 0.7893 0.0185
-3.500 0.1195 0.01624 0.01206 -0.1053 0.7775 0.0191
-3.250 0.1465 0.01672 0.01254 -0.1053 0.7660 0.0201
-2.750 0.2073 0.01453 0.00983 -0.1063 0.7460 0.0232
-2.000 0.2951 0.01267 0.00755 -0.1078 0.7177 0.0294
-1.750 0.3255 0.01158 0.00623 -0.1082 0.7085 0.0293
-1.500 0.3552 0.01084 0.00532 -0.1085 0.6985 0.0297
-1.250 0.3845 0.01052 0.00490 -0.1087 0.6873 0.0311
-1.000 0.4137 0.01014 0.00442 -0.1089 0.6746 0.0317
-0.750 0.4428 0.00983 0.00402 -0.1091 0.6597 0.0321
-0.500 0.4718 0.00953 0.00361 -0.1093 0.6411 0.0323
-0.250 0.5007 0.00925 0.00321 -0.1095 0.6150 0.0324
0.250 0.5581 0.00889 0.00258 -0.1099 0.5609 0.0333
0.500 0.5873 0.00864 0.00220 -0.1103 0.5438 0.0344
0.750 0.6162 0.00855 0.00203 -0.1105 0.5307 0.0363
1.000 0.6450 0.00854 0.00196 -0.1107 0.5204 0.0377
1.250 0.6736 0.00856 0.00193 -0.1109 0.5115 0.0390
1.500 0.7023 0.00856 0.00191 -0.1111 0.5033 0.0402
1.750 0.7309 0.00860 0.00191 -0.1112 0.4946 0.0419
2.000 0.7593 0.00865 0.00191 -0.1114 0.4848 0.0462
2.250 0.7894 0.00764 0.00220 -0.1127 0.4762 0.6474
2.750 0.8403 0.00703 0.00225 -0.1116 0.4620 1.0000
3.000 0.8685 0.00717 0.00233 -0.1117 0.4543 1.0000
3.250 0.8969 0.00726 0.00239 -0.1119 0.4465 1.0000
3.500 0.9251 0.00739 0.00249 -0.1120 0.4397 1.0000
3.750 0.9533 0.00750 0.00257 -0.1121 0.4298 1.0000
4.000 0.9813 0.00764 0.00266 -0.1122 0.4164 1.0000
4.250 1.0091 0.00781 0.00276 -0.1123 0.4010 1.0000
4.500 1.0369 0.00797 0.00289 -0.1124 0.3876 1.0000
4.750 1.0645 0.00817 0.00302 -0.1125 0.3712 1.0000
5.000 1.0914 0.00847 0.00319 -0.1125 0.3425 1.0000
5.250 1.1171 0.00897 0.00345 -0.1125 0.2960 1.0000
5.500 1.1375 0.01041 0.00421 -0.1119 0.1737 1.0000
5.750 1.1602 0.01139 0.00481 -0.1114 0.1094 1.0000
6.000 1.1795 0.01290 0.00574 -0.1105 0.0197 1.0000
6.250 1.2054 0.01324 0.00612 -0.1103 0.0150 1.0000
6.500 1.2310 0.01362 0.00657 -0.1100 0.0136 1.0000
6.750 1.2559 0.01408 0.00708 -0.1096 0.0123 1.0000
7.000 1.2793 0.01474 0.00784 -0.1089 0.0109 1.0000
7.250 1.3034 0.01522 0.00837 -0.1085 0.0103 1.0000
7.500 1.3272 0.01573 0.00894 -0.1079 0.0097 1.0000
7.750 1.3502 0.01632 0.00959 -0.1073 0.0091 1.0000
8.000 1.3724 0.01697 0.01029 -0.1065 0.0086 1.0000
8.250 1.3936 0.01768 0.01106 -0.1056 0.0082 1.0000
8.500 1.4130 0.01853 0.01198 -0.1044 0.0078 1.0000
8.750 1.4269 0.01990 0.01343 -0.1024 0.0073 1.0000
9.000 1.4333 0.02183 0.01550 -0.0993 0.0070 1.0000
9.250 1.4551 0.02220 0.01592 -0.0985 0.0067 1.0000
9.500 1.4720 0.02297 0.01675 -0.0970 0.0064 1.0000
9.750 1.4836 0.02406 0.01791 -0.0946 0.0062 1.0000
10.000 1.4926 0.02523 0.01916 -0.0919 0.0060 1.0000
10.250 1.4969 0.02648 0.02049 -0.0885 0.0059 1.0000
10.500 1.5010 0.02788 0.02197 -0.0853 0.0058 1.0000
10.750 1.5060 0.02936 0.02354 -0.0826 0.0056 1.0000
11.000 1.5109 0.03099 0.02525 -0.0802 0.0055 1.0000
11.250 1.5163 0.03266 0.02699 -0.0780 0.0054 1.0000
11.500 1.5216 0.03441 0.02882 -0.0761 0.0053 1.0000
11.750 1.5266 0.03624 0.03073 -0.0743 0.0051 1.0000
12.000 1.5308 0.03823 0.03280 -0.0727 0.0050 1.0000
12.250 1.5339 0.04039 0.03504 -0.0712 0.0049 1.0000
12.500 1.5355 0.04285 0.03757 -0.0695 0.0048 1.0000
12.750 1.5357 0.04589 0.04070 -0.0671 0.0046 1.0000
13.000 1.5415 0.05035 0.04534 -0.0639 0.0045 1.0000
13.250 1.5422 0.05358 0.04874 -0.0622 0.0045 1.0000
13.500 1.5397 0.05681 0.05212 -0.0607 0.0045 1.0000
13.750 1.5346 0.06036 0.05583 -0.0595 0.0045 1.0000
14.000 1.5254 0.06458 0.06024 -0.0584 0.0045 1.0000
14.250 1.5151 0.06874 0.06457 -0.0578 0.0045 1.0000
14.500 1.5027 0.07326 0.06926 -0.0576 0.0045 1.0000
14.750 1.4907 0.07768 0.07383 -0.0579 0.0045 1.0000
15.000 1.4767 0.08259 0.07891 -0.0586 0.0045 1.0000
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Polar data table (+)
Polar graphs
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