GOE 361 AIRFOIL (goe361-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 361 AIRFOIL (goe361-il) Reynolds number: 500,000 Max Cl/Cd: 101.31 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe361-il-500000-n5.txt Download as CSV file: xf-goe361-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 361 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.2833 0.09791 0.09572 -0.0242 1.0000 0.0084
-8.250 -0.2809 0.09529 0.09314 -0.0243 1.0000 0.0084
-8.000 -0.2796 0.09287 0.09074 -0.0241 1.0000 0.0083
-7.500 -0.2634 0.08448 0.08240 -0.0308 0.9892 0.0091
-7.000 -0.2201 0.07863 0.07654 -0.0395 0.9658 0.0099
-6.750 -0.1919 0.07443 0.07232 -0.0467 0.9544 0.0105
-6.500 -0.1584 0.06932 0.06717 -0.0561 0.9433 0.0109
-6.250 -0.1204 0.06342 0.06119 -0.0673 0.9287 0.0115
-6.000 -0.0859 0.05827 0.05594 -0.0767 0.9112 0.0124
-5.750 -0.0591 0.05604 0.05361 -0.0806 0.8935 0.0131
-5.500 -0.0353 0.05286 0.05033 -0.0849 0.8745 0.0139
-5.250 -0.0105 0.04903 0.04638 -0.0897 0.8555 0.0145
-5.000 0.0226 0.04254 0.03967 -0.0981 0.8362 0.0161
-4.750 0.0440 0.04157 0.03861 -0.0986 0.8145 0.0166
-4.500 0.0691 0.03948 0.03634 -0.1005 0.7897 0.0174
-4.250 0.0974 0.03629 0.03291 -0.1036 0.7626 0.0182
-4.000 0.1378 0.02934 0.02546 -0.1094 0.7398 0.0208
-3.750 0.1609 0.02812 0.02405 -0.1099 0.7134 0.0213
-3.500 0.1856 0.02690 0.02264 -0.1103 0.6907 0.0219
-3.250 0.2127 0.02492 0.02040 -0.1111 0.6717 0.0225
-3.000 0.2407 0.02279 0.01798 -0.1118 0.6544 0.0232
-2.750 0.2688 0.02072 0.01559 -0.1122 0.6363 0.0245
-2.500 0.2969 0.01839 0.01287 -0.1124 0.6204 0.0249
-2.250 0.3243 0.01671 0.01084 -0.1124 0.6059 0.0253
-2.000 0.3514 0.01548 0.00930 -0.1122 0.5928 0.0256
-1.750 0.3784 0.01482 0.00840 -0.1120 0.5789 0.0262
-1.500 0.4052 0.01402 0.00735 -0.1117 0.5653 0.0263
-1.250 0.4320 0.01326 0.00637 -0.1115 0.5517 0.0263
-1.000 0.4588 0.01272 0.00562 -0.1112 0.5370 0.0264
-0.750 0.4855 0.01235 0.00508 -0.1108 0.5214 0.0266
-0.500 0.5121 0.01207 0.00463 -0.1105 0.5050 0.0270
-0.250 0.5383 0.01132 0.00371 -0.1101 0.4888 0.0276
0.000 0.5645 0.01100 0.00328 -0.1098 0.4728 0.0281
0.250 0.5907 0.01080 0.00299 -0.1094 0.4576 0.0285
0.500 0.6170 0.01067 0.00278 -0.1090 0.4436 0.0289
0.750 0.6432 0.01059 0.00264 -0.1087 0.4303 0.0299
1.000 0.6695 0.01053 0.00253 -0.1084 0.4175 0.0306
1.250 0.6957 0.01049 0.00242 -0.1080 0.4047 0.0307
1.500 0.7222 0.01045 0.00234 -0.1077 0.3925 0.0307
1.750 0.7486 0.01045 0.00229 -0.1073 0.3808 0.0308
2.000 0.7749 0.01048 0.00227 -0.1070 0.3699 0.0310
2.250 0.8012 0.01053 0.00228 -0.1067 0.3587 0.0314
2.500 0.8276 0.01060 0.00230 -0.1063 0.3474 0.0322
2.750 0.8539 0.01068 0.00234 -0.1060 0.3364 0.0333
3.000 0.8800 0.01080 0.00241 -0.1057 0.3256 0.0346
3.250 0.9060 0.01094 0.00250 -0.1053 0.3148 0.0359
3.500 0.9321 0.01107 0.00261 -0.1049 0.3045 0.0389
3.750 0.9627 0.00969 0.00302 -0.1062 0.2954 1.0000
4.250 1.0144 0.01010 0.00333 -0.1055 0.2798 1.0000
4.500 1.0400 0.01032 0.00353 -0.1051 0.2731 1.0000
4.750 1.0658 0.01052 0.00372 -0.1047 0.2680 1.0000
5.000 1.0910 0.01078 0.00393 -0.1042 0.2586 1.0000
5.250 1.1157 0.01108 0.00416 -0.1037 0.2446 1.0000
5.500 1.1407 0.01134 0.00441 -0.1033 0.2349 1.0000
5.750 1.1653 0.01164 0.00467 -0.1028 0.2250 1.0000
6.000 1.1897 0.01196 0.00494 -0.1022 0.2129 1.0000
6.250 1.2138 0.01231 0.00524 -0.1017 0.1952 1.0000
6.500 1.2273 0.01389 0.00621 -0.0998 0.0915 1.0000
6.750 1.2424 0.01532 0.00731 -0.0980 0.0246 1.0000
7.000 1.2647 0.01583 0.00785 -0.0972 0.0187 1.0000
7.250 1.2872 0.01632 0.00840 -0.0963 0.0158 1.0000
7.500 1.3095 0.01679 0.00895 -0.0955 0.0141 1.0000
7.750 1.3307 0.01736 0.00956 -0.0945 0.0125 1.0000
8.000 1.3500 0.01813 0.01040 -0.0933 0.0107 1.0000
8.250 1.3706 0.01871 0.01106 -0.0922 0.0101 1.0000
8.500 1.3900 0.01936 0.01180 -0.0910 0.0094 1.0000
8.750 1.4083 0.02008 0.01260 -0.0896 0.0087 1.0000
9.000 1.4256 0.02084 0.01343 -0.0882 0.0082 1.0000
9.250 1.4393 0.02184 0.01450 -0.0863 0.0075 1.0000
9.500 1.4524 0.02280 0.01556 -0.0842 0.0071 1.0000
9.750 1.4659 0.02362 0.01648 -0.0823 0.0067 1.0000
10.000 1.4735 0.02461 0.01757 -0.0794 0.0065 1.0000
10.250 1.4794 0.02566 0.01872 -0.0763 0.0062 1.0000
10.500 1.4846 0.02679 0.01996 -0.0735 0.0059 1.0000
10.750 1.4874 0.02815 0.02141 -0.0707 0.0058 1.0000
11.000 1.4894 0.02966 0.02303 -0.0681 0.0056 1.0000
11.250 1.4913 0.03134 0.02480 -0.0660 0.0055 1.0000
11.500 1.4921 0.03323 0.02679 -0.0641 0.0053 1.0000
11.750 1.4896 0.03562 0.02928 -0.0625 0.0052 1.0000
12.000 1.4843 0.03852 0.03231 -0.0612 0.0051 1.0000
12.250 1.4758 0.04207 0.03599 -0.0604 0.0050 1.0000
12.500 1.4706 0.04553 0.03956 -0.0601 0.0049 1.0000
12.750 1.4672 0.04894 0.04311 -0.0601 0.0048 1.0000
13.000 1.4632 0.05255 0.04685 -0.0603 0.0048 1.0000
13.250 1.4597 0.05621 0.05064 -0.0606 0.0047 1.0000
13.500 1.4561 0.05997 0.05455 -0.0611 0.0046 1.0000
13.750 1.4522 0.06384 0.05855 -0.0617 0.0044 1.0000
14.000 1.4479 0.06787 0.06271 -0.0624 0.0043 1.0000
14.250 1.4442 0.07195 0.06691 -0.0634 0.0042 1.0000
14.500 1.4398 0.07619 0.07128 -0.0644 0.0041 1.0000
14.750 1.4359 0.08051 0.07571 -0.0656 0.0040 1.0000
15.000 1.4310 0.08501 0.08034 -0.0668 0.0039 1.0000
15.250 1.4269 0.08955 0.08500 -0.0683 0.0038 1.0000
15.500 1.4222 0.09426 0.08983 -0.0698 0.0038 1.0000
15.750 1.4178 0.09906 0.09475 -0.0716 0.0037 1.0000
16.000 1.4131 0.10396 0.09977 -0.0735 0.0037 1.0000
16.250 1.4074 0.10909 0.10504 -0.0755 0.0036 1.0000
16.500 1.4021 0.11430 0.11037 -0.0778 0.0036 1.0000
16.750 1.3965 0.11965 0.11585 -0.0802 0.0035 1.0000
17.000 1.3906 0.12514 0.12147 -0.0828 0.0035 1.0000
17.250 1.3848 0.13073 0.12719 -0.0856 0.0035 1.0000
17.500 1.3788 0.13641 0.13299 -0.0886 0.0034 1.0000
17.750 1.3720 0.14240 0.13910 -0.0919 0.0034 1.0000
18.000 1.3642 0.14872 0.14556 -0.0954 0.0034 1.0000
18.250 1.3566 0.15513 0.15210 -0.0992 0.0033 1.0000
18.500 1.3479 0.16195 0.15906 -0.1033 0.0033 1.0000
18.750 1.3388 0.16900 0.16625 -0.1077 0.0033 1.0000
19.000 1.3281 0.17671 0.17411 -0.1126 0.0033 1.0000
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