GOE 328 AIRFOIL (goe328-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 328 AIRFOIL (goe328-il) Reynolds number: 1,000,000 Max Cl/Cd: 120.66 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe328-il-1000000.txt Download as CSV file: xf-goe328-il-1000000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.4134 0.11040 0.10877 -0.0097 1.0000 0.0167
-9.250 -0.4098 0.10664 0.10501 -0.0123 1.0000 0.0168
-9.000 -0.4068 0.10203 0.10042 -0.0137 1.0000 0.0169
-8.750 -0.3979 0.09906 0.09746 -0.0138 1.0000 0.0170
-8.500 -0.3898 0.09632 0.09472 -0.0147 1.0000 0.0172
-8.250 -0.3820 0.09359 0.09200 -0.0160 1.0000 0.0174
-8.000 -0.3746 0.09083 0.08926 -0.0174 1.0000 0.0176
-7.750 -0.3678 0.08803 0.08648 -0.0191 1.0000 0.0179
-7.500 -0.3620 0.08519 0.08366 -0.0209 1.0000 0.0182
-7.250 -0.3464 0.08143 0.07990 -0.0260 0.9854 0.0190
-7.000 -0.3185 0.07479 0.07318 -0.0405 0.9536 0.0205
-6.750 -0.3025 0.07047 0.06876 -0.0454 0.9285 0.0205
-6.500 -0.2851 0.06629 0.06447 -0.0496 0.9088 0.0205
-6.250 -0.2652 0.06192 0.05997 -0.0539 0.8922 0.0206
-5.500 -0.2139 0.05211 0.04990 -0.0597 0.8495 0.0215
-5.250 -0.1907 0.04945 0.04714 -0.0621 0.8362 0.0220
-5.000 -0.1656 0.04649 0.04406 -0.0647 0.8234 0.0227
-4.750 -0.1288 0.04231 0.03964 -0.0690 0.8118 0.0249
-4.500 -0.0998 0.03895 0.03607 -0.0711 0.8003 0.0250
-4.250 -0.0719 0.03555 0.03247 -0.0728 0.7893 0.0251
-4.000 -0.0474 0.02948 0.02610 -0.0753 0.7796 0.0257
-3.750 -0.0221 0.02794 0.02444 -0.0759 0.7692 0.0260
-3.500 0.0041 0.02655 0.02294 -0.0765 0.7589 0.0264
-3.250 0.0312 0.02511 0.02137 -0.0771 0.7489 0.0270
-3.000 0.0591 0.02353 0.01961 -0.0776 0.7389 0.0278
-2.750 0.0902 0.02203 0.01787 -0.0776 0.7286 0.0303
-2.500 0.1199 0.02097 0.01657 -0.0777 0.7180 0.0307
-2.250 0.1486 0.01950 0.01483 -0.0779 0.7067 0.0308
-1.750 -0.0263 0.01326 0.01048 -0.1032 0.7207 0.0272
-0.500 0.3503 0.01061 0.00456 -0.0796 0.6327 0.0313
-0.250 0.3790 0.01013 0.00401 -0.0797 0.6226 0.0313
0.000 0.4077 0.00970 0.00352 -0.0798 0.6123 0.0312
0.250 0.4362 0.00929 0.00306 -0.0799 0.6011 0.0312
0.500 0.4648 0.00875 0.00246 -0.0800 0.5886 0.0318
0.750 0.4934 0.00851 0.00219 -0.0802 0.5744 0.0327
1.000 0.5219 0.00841 0.00204 -0.0803 0.5580 0.0335
1.250 0.5504 0.00834 0.00192 -0.0804 0.5384 0.0343
1.500 0.5787 0.00834 0.00182 -0.0806 0.5141 0.0350
1.750 0.6069 0.00838 0.00176 -0.0807 0.4882 0.0359
2.000 0.6349 0.00847 0.00176 -0.0807 0.4661 0.0374
2.250 0.6631 0.00852 0.00173 -0.0808 0.4488 0.0389
2.500 0.6914 0.00855 0.00170 -0.0810 0.4351 0.0428
2.750 0.7197 0.00861 0.00174 -0.0811 0.4238 0.0471
3.000 0.7414 0.00670 0.00195 -0.0803 0.4153 1.0000
3.250 0.7696 0.00686 0.00203 -0.0804 0.4059 1.0000
3.500 0.7979 0.00698 0.00211 -0.0805 0.3973 1.0000
3.750 0.8259 0.00713 0.00221 -0.0806 0.3880 1.0000
4.000 0.8540 0.00728 0.00231 -0.0807 0.3781 1.0000
4.250 0.8820 0.00741 0.00241 -0.0808 0.3678 1.0000
4.500 0.9098 0.00759 0.00253 -0.0808 0.3536 1.0000
4.750 0.9375 0.00777 0.00265 -0.0809 0.3400 1.0000
5.000 0.9648 0.00800 0.00279 -0.0809 0.3204 1.0000
5.250 0.9918 0.00827 0.00296 -0.0809 0.3003 1.0000
5.500 1.0190 0.00851 0.00313 -0.0809 0.2844 1.0000
5.750 1.0459 0.00876 0.00332 -0.0809 0.2694 1.0000
6.000 1.0726 0.00905 0.00354 -0.0809 0.2522 1.0000
6.250 1.0991 0.00934 0.00377 -0.0808 0.2362 1.0000
6.500 1.1253 0.00968 0.00403 -0.0807 0.2183 1.0000
6.750 1.1509 0.01008 0.00432 -0.0805 0.1946 1.0000
7.000 1.1678 0.01173 0.00533 -0.0794 0.0830 1.0000
7.250 1.1895 0.01265 0.00601 -0.0787 0.0433 1.0000
7.500 1.2133 0.01323 0.00651 -0.0782 0.0299 1.0000
7.750 1.2373 0.01376 0.00701 -0.0778 0.0238 1.0000
8.000 1.2620 0.01416 0.00742 -0.0774 0.0215 1.0000
8.250 1.2849 0.01478 0.00806 -0.0768 0.0188 1.0000
8.500 1.3093 0.01516 0.00848 -0.0764 0.0178 1.0000
8.750 1.3329 0.01562 0.00896 -0.0759 0.0167 1.0000
9.000 1.3552 0.01620 0.00957 -0.0752 0.0156 1.0000
9.250 1.3748 0.01707 0.01051 -0.0742 0.0146 1.0000
9.500 1.3970 0.01757 0.01106 -0.0735 0.0142 1.0000
9.750 1.4182 0.01815 0.01170 -0.0727 0.0136 1.0000
10.000 1.4385 0.01877 0.01237 -0.0717 0.0131 1.0000
10.250 1.4581 0.01941 0.01304 -0.0708 0.0125 1.0000
10.500 1.4749 0.02024 0.01392 -0.0694 0.0119 1.0000
10.750 1.4810 0.02184 0.01565 -0.0665 0.0113 1.0000
11.000 1.4969 0.02253 0.01640 -0.0650 0.0112 1.0000
11.250 1.5093 0.02331 0.01724 -0.0630 0.0109 1.0000
11.500 1.5178 0.02424 0.01826 -0.0604 0.0107 1.0000
11.750 1.5256 0.02532 0.01942 -0.0581 0.0104 1.0000
12.000 1.5328 0.02656 0.02073 -0.0560 0.0102 1.0000
12.250 1.5395 0.02794 0.02219 -0.0542 0.0100 1.0000
12.500 1.5456 0.02949 0.02382 -0.0526 0.0097 1.0000
12.750 1.5513 0.03118 0.02558 -0.0513 0.0095 1.0000
13.000 1.5555 0.03310 0.02759 -0.0501 0.0093 1.0000
13.250 1.5581 0.03531 0.02988 -0.0491 0.0092 1.0000
13.500 1.5573 0.03797 0.03262 -0.0482 0.0090 1.0000
13.750 1.5521 0.04121 0.03597 -0.0474 0.0088 1.0000
14.000 1.5416 0.04511 0.03999 -0.0466 0.0087 1.0000
14.250 1.5311 0.04911 0.04412 -0.0458 0.0085 1.0000
14.500 1.5337 0.05179 0.04690 -0.0459 0.0085 1.0000
14.750 1.5350 0.05469 0.04991 -0.0460 0.0084 1.0000
15.000 1.5339 0.05791 0.05324 -0.0462 0.0083 1.0000
15.250 1.5318 0.06133 0.05676 -0.0466 0.0082 1.0000
15.500 1.5288 0.06497 0.06052 -0.0471 0.0081 1.0000
15.750 1.5246 0.06887 0.06452 -0.0477 0.0080 1.0000
16.000 1.5197 0.07296 0.06872 -0.0486 0.0079 1.0000
16.250 1.5141 0.07723 0.07310 -0.0495 0.0078 1.0000
16.500 1.5082 0.08165 0.07763 -0.0506 0.0077 1.0000
16.750 1.5017 0.08624 0.08233 -0.0519 0.0076 1.0000
17.000 1.4948 0.09097 0.08717 -0.0533 0.0075 1.0000
17.250 1.4874 0.09585 0.09215 -0.0549 0.0075 1.0000
17.500 1.4796 0.10088 0.09730 -0.0566 0.0074 1.0000
17.750 1.4714 0.10605 0.10258 -0.0585 0.0073 1.0000
18.000 1.4630 0.11129 0.10793 -0.0605 0.0072 1.0000
18.250 1.4542 0.11666 0.11340 -0.0627 0.0072 1.0000
18.500 1.4455 0.12215 0.11900 -0.0651 0.0071 1.0000
18.750 1.4362 0.12784 0.12480 -0.0676 0.0071 1.0000
19.000 1.4274 0.13352 0.13058 -0.0704 0.0070 1.0000
19.250 1.4179 0.13943 0.13660 -0.0734 0.0070 1.0000
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