GOE 328 AIRFOIL (goe328-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 328 AIRFOIL (goe328-il) Reynolds number: 1,000,000 Max Cl/Cd: 111.33 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe328-il-1000000-n5.txt Download as CSV file: xf-goe328-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 328 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.4269 0.10555 0.10391 -0.0087 1.0000 0.0114
-9.250 -0.4213 0.10212 0.10049 -0.0104 1.0000 0.0117
-9.000 -0.4285 0.09509 0.09346 -0.0142 1.0000 0.0130
-8.750 -0.4203 0.09257 0.09096 -0.0157 1.0000 0.0131
-8.500 -0.4071 0.08979 0.08815 -0.0186 0.9590 0.0133
-8.250 -0.4016 0.08737 0.08563 -0.0194 0.9182 0.0134
-8.000 -0.3962 0.08478 0.08296 -0.0207 0.8916 0.0135
-7.750 -0.3888 0.08193 0.08003 -0.0231 0.8710 0.0137
-7.500 -0.3772 0.07857 0.07660 -0.0269 0.8537 0.0140
-7.250 -0.3637 0.07482 0.07278 -0.0313 0.8378 0.0143
-7.000 -0.3483 0.07062 0.06849 -0.0365 0.8231 0.0149
-6.750 -0.3303 0.06039 0.05810 -0.0493 0.8106 0.0163
-6.500 -0.3095 0.05732 0.05495 -0.0527 0.7977 0.0164
-6.250 -0.2875 0.05469 0.05223 -0.0554 0.7856 0.0166
-6.000 -0.2645 0.05204 0.04948 -0.0582 0.7737 0.0168
-5.750 -0.2405 0.04927 0.04660 -0.0609 0.7619 0.0171
-5.500 -0.2156 0.04656 0.04378 -0.0635 0.7498 0.0175
-5.250 -0.1894 0.04313 0.04019 -0.0664 0.7387 0.0180
-5.000 -0.1619 0.03913 0.03601 -0.0693 0.7281 0.0184
-4.500 -0.1024 0.02672 0.02284 -0.0749 0.7077 0.0200
-4.250 -0.0754 0.02194 0.01764 -0.0763 0.6984 0.0205
-4.000 -0.0479 0.02020 0.01570 -0.0768 0.6894 0.0207
-3.750 -0.0201 0.01832 0.01358 -0.0773 0.6817 0.0209
-3.500 0.0080 0.01631 0.01128 -0.0777 0.6732 0.0211
-3.250 0.0364 0.01463 0.00932 -0.0780 0.6650 0.0213
-2.750 0.0932 0.01293 0.00727 -0.0785 0.6463 0.0219
-2.500 0.1217 0.01206 0.00620 -0.0787 0.6360 0.0221
-2.250 0.1502 0.01143 0.00541 -0.0788 0.6248 0.0225
-2.000 0.1788 0.01093 0.00480 -0.0789 0.6131 0.0228
-1.750 0.2073 0.01055 0.00430 -0.0791 0.6002 0.0233
-1.500 0.2358 0.01026 0.00390 -0.0792 0.5842 0.0237
-1.250 0.2641 0.01001 0.00354 -0.0793 0.5652 0.0240
-1.000 0.2925 0.00982 0.00325 -0.0794 0.5466 0.0243
-0.750 0.3209 0.00965 0.00300 -0.0795 0.5282 0.0245
-0.500 0.3492 0.00953 0.00277 -0.0796 0.5051 0.0247
-0.250 0.3774 0.00946 0.00259 -0.0797 0.4811 0.0248
0.000 0.4057 0.00941 0.00245 -0.0798 0.4605 0.0250
0.250 0.4340 0.00936 0.00232 -0.0799 0.4447 0.0251
0.500 0.4625 0.00913 0.00203 -0.0801 0.4322 0.0257
0.750 0.4911 0.00904 0.00189 -0.0803 0.4221 0.0265
1.250 0.5481 0.00897 0.00177 -0.0806 0.4045 0.0276
1.500 0.5766 0.00898 0.00175 -0.0807 0.3961 0.0284
1.750 0.6051 0.00898 0.00174 -0.0809 0.3882 0.0293
2.000 0.6335 0.00901 0.00174 -0.0810 0.3805 0.0301
2.250 0.6619 0.00902 0.00175 -0.0811 0.3733 0.0308
2.500 0.6902 0.00908 0.00178 -0.0812 0.3660 0.0314
2.750 0.7186 0.00910 0.00181 -0.0814 0.3592 0.0322
3.250 0.7751 0.00921 0.00191 -0.0816 0.3430 0.0419
3.500 0.8034 0.00794 0.00222 -0.0826 0.3329 0.7771
4.000 0.8528 0.00772 0.00237 -0.0810 0.3121 1.0000
4.500 0.9077 0.00818 0.00265 -0.0811 0.2785 1.0000
4.750 0.9350 0.00841 0.00280 -0.0811 0.2638 1.0000
5.000 0.9621 0.00866 0.00298 -0.0811 0.2486 1.0000
5.250 0.9893 0.00889 0.00316 -0.0811 0.2359 1.0000
5.500 1.0164 0.00913 0.00334 -0.0811 0.2242 1.0000
5.750 1.0429 0.00944 0.00357 -0.0811 0.2071 1.0000
6.000 1.0694 0.00974 0.00380 -0.0810 0.1906 1.0000
6.250 1.0909 0.01079 0.00442 -0.0804 0.1129 1.0000
6.500 1.1132 0.01169 0.00505 -0.0798 0.0616 1.0000
6.750 1.1381 0.01217 0.00544 -0.0795 0.0453 1.0000
7.000 1.1634 0.01256 0.00580 -0.0793 0.0363 1.0000
7.250 1.1885 0.01296 0.00615 -0.0790 0.0289 1.0000
7.500 1.2134 0.01337 0.00652 -0.0787 0.0220 1.0000
7.750 1.2381 0.01378 0.00691 -0.0784 0.0176 1.0000
8.000 1.2629 0.01415 0.00729 -0.0781 0.0156 1.0000
8.250 1.2873 0.01456 0.00770 -0.0777 0.0140 1.0000
8.500 1.3112 0.01500 0.00816 -0.0773 0.0126 1.0000
8.750 1.3354 0.01539 0.00858 -0.0769 0.0120 1.0000
9.000 1.3591 0.01580 0.00903 -0.0764 0.0112 1.0000
9.250 1.3821 0.01627 0.00951 -0.0759 0.0104 1.0000
9.500 1.4042 0.01681 0.01008 -0.0752 0.0096 1.0000
9.750 1.4262 0.01733 0.01064 -0.0745 0.0092 1.0000
10.000 1.4480 0.01783 0.01118 -0.0738 0.0089 1.0000
10.250 1.4692 0.01835 0.01176 -0.0731 0.0085 1.0000
10.500 1.4896 0.01891 0.01236 -0.0722 0.0081 1.0000
10.750 1.5092 0.01951 0.01300 -0.0712 0.0078 1.0000
11.000 1.5276 0.02016 0.01369 -0.0701 0.0074 1.0000
11.250 1.5440 0.02092 0.01449 -0.0687 0.0070 1.0000
11.500 1.5585 0.02174 0.01538 -0.0670 0.0067 1.0000
11.750 1.5731 0.02244 0.01614 -0.0653 0.0066 1.0000
12.000 1.5835 0.02321 0.01698 -0.0630 0.0064 1.0000
12.250 1.5929 0.02412 0.01796 -0.0607 0.0063 1.0000
12.500 1.6018 0.02515 0.01908 -0.0587 0.0061 1.0000
12.750 1.6102 0.02631 0.02031 -0.0568 0.0060 1.0000
13.000 1.6181 0.02760 0.02168 -0.0551 0.0058 1.0000
13.250 1.6252 0.02904 0.02320 -0.0537 0.0057 1.0000
13.500 1.6314 0.03066 0.02489 -0.0524 0.0056 1.0000
13.750 1.6369 0.03244 0.02676 -0.0513 0.0054 1.0000
14.000 1.6409 0.03447 0.02886 -0.0503 0.0053 1.0000
14.250 1.6435 0.03674 0.03122 -0.0496 0.0052 1.0000
14.500 1.6442 0.03933 0.03391 -0.0490 0.0051 1.0000
14.750 1.6423 0.04230 0.03698 -0.0486 0.0050 1.0000
15.000 1.6375 0.04574 0.04053 -0.0484 0.0049 1.0000
15.250 1.6302 0.04961 0.04453 -0.0484 0.0048 1.0000
15.500 1.6261 0.05316 0.04818 -0.0486 0.0048 1.0000
15.750 1.6209 0.05694 0.05207 -0.0490 0.0047 1.0000
16.000 1.6141 0.06104 0.05629 -0.0496 0.0047 1.0000
16.250 1.6067 0.06537 0.06073 -0.0503 0.0047 1.0000
16.500 1.5987 0.06993 0.06541 -0.0513 0.0046 1.0000
16.750 1.5897 0.07478 0.07037 -0.0526 0.0046 1.0000
17.000 1.5800 0.07980 0.07551 -0.0539 0.0046 1.0000
17.250 1.5697 0.08499 0.08081 -0.0554 0.0046 1.0000
17.500 1.5595 0.09028 0.08621 -0.0570 0.0045 1.0000
17.750 1.5487 0.09565 0.09168 -0.0587 0.0045 1.0000
18.000 1.5378 0.10108 0.09722 -0.0605 0.0044 1.0000
18.250 1.5272 0.10655 0.10280 -0.0624 0.0044 1.0000
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