GOE 802 AIRFOIL (goe802-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 802 AIRFOIL (goe802-il) Reynolds number: 200,000 Max Cl/Cd: 79.85 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe802-il-200000.txt Download as CSV file: xf-goe802-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 802 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
------ -------- --------- --------- -------- -------- --------
-9.500 -0.2616 0.11548 0.11201 -0.0346 1.0000 0.0334
-9.250 -0.2803 0.11564 0.11226 -0.0318 1.0000 0.0335
-9.000 -0.2998 0.11576 0.11247 -0.0290 1.0000 0.0336
-8.500 -0.2799 0.10804 0.10477 -0.0300 0.9970 0.0341
-8.250 -0.2587 0.10386 0.10058 -0.0327 0.9945 0.0348
-8.000 -0.2401 0.10023 0.09694 -0.0365 0.9906 0.0358
-7.750 -0.2214 0.09658 0.09329 -0.0412 0.9861 0.0370
-7.500 -0.2024 0.09290 0.08960 -0.0470 0.9814 0.0383
-7.250 -0.1747 0.08894 0.08560 -0.0649 0.9708 0.0396
-7.000 -0.1569 0.08435 0.08101 -0.0688 0.9646 0.0399
-6.750 -0.1380 0.08056 0.07723 -0.0678 0.9618 0.0405
-6.500 -0.1113 0.07682 0.07347 -0.0717 0.9588 0.0415
-6.250 -0.0794 0.07287 0.06949 -0.0785 0.9561 0.0433
-6.000 -0.0538 0.06944 0.06600 -0.0859 0.9466 0.0459
-5.750 -0.0078 0.06367 0.06006 -0.1012 0.9412 0.0475
-5.500 0.0053 0.06100 0.05742 -0.0999 0.9340 0.0482
-5.250 0.0281 0.05820 0.05461 -0.1015 0.9282 0.0494
-5.000 0.0586 0.05502 0.05136 -0.1058 0.9240 0.0515
-4.750 0.1068 0.05131 0.04718 -0.1173 0.9129 0.0562
-4.500 0.1225 0.04774 0.04372 -0.1166 0.9084 0.0572
-4.250 0.1378 0.04587 0.04188 -0.1157 0.8989 0.0587
-4.000 0.1642 0.04358 0.03952 -0.1171 0.8929 0.0617
-3.750 0.2033 0.04032 0.03579 -0.1222 0.8837 0.0678
-3.500 0.2234 0.03791 0.03344 -0.1218 0.8770 0.0693
-3.250 0.2449 0.03621 0.03171 -0.1216 0.8673 0.0719
-3.000 0.2818 0.03393 0.02892 -0.1240 0.8601 0.0809
-2.750 0.3016 0.03183 0.02691 -0.1235 0.8496 0.0831
-2.500 0.3368 0.03214 0.02666 -0.1239 0.8421 0.0946
-2.250 0.3557 0.02846 0.02319 -0.1241 0.8315 0.0978
-2.000 0.3846 0.02742 0.02186 -0.1243 0.8225 0.1118
-1.750 0.4081 0.02576 0.02028 -0.1240 0.8129 0.1172
-1.500 0.4351 0.02452 0.01889 -0.1241 0.8022 0.1315
-1.250 0.4624 0.02339 0.01760 -0.1241 0.7932 0.1480
-0.250 0.5893 0.01791 0.01045 -0.1223 0.7487 0.0796
0.000 0.6171 0.01646 0.00889 -0.1220 0.7361 0.0763
0.250 0.6456 0.01560 0.00777 -0.1215 0.7236 0.0705
0.500 0.6738 0.01534 0.00730 -0.1208 0.7108 0.0675
0.750 0.7014 0.01487 0.00672 -0.1203 0.6982 0.0666
1.000 0.7285 0.01440 0.00621 -0.1199 0.6845 0.0663
1.250 0.7555 0.01408 0.00585 -0.1194 0.6707 0.0665
1.500 0.7824 0.01380 0.00554 -0.1190 0.6569 0.0675
1.750 0.8093 0.01356 0.00530 -0.1188 0.6433 0.0720
2.000 0.8364 0.01351 0.00517 -0.1184 0.6301 0.0757
2.250 0.8635 0.01353 0.00507 -0.1180 0.6176 0.0800
2.500 0.8904 0.01351 0.00503 -0.1177 0.6045 0.0960
2.750 0.9135 0.01192 0.00518 -0.1167 0.5919 1.0000
3.000 0.9400 0.01216 0.00525 -0.1162 0.5790 1.0000
3.250 0.9663 0.01243 0.00535 -0.1158 0.5668 1.0000
3.500 0.9927 0.01271 0.00547 -0.1155 0.5552 1.0000
3.750 1.0185 0.01296 0.00566 -0.1151 0.5425 1.0000
4.000 1.0440 0.01324 0.00584 -0.1146 0.5293 1.0000
4.250 1.0693 0.01351 0.00602 -0.1141 0.5161 1.0000
4.500 1.0946 0.01381 0.00622 -0.1136 0.5037 1.0000
4.750 1.1197 0.01409 0.00642 -0.1131 0.4916 1.0000
5.000 1.1445 0.01436 0.00667 -0.1126 0.4793 1.0000
5.250 1.1696 0.01466 0.00693 -0.1122 0.4688 1.0000
5.500 1.1947 0.01499 0.00718 -0.1117 0.4592 1.0000
5.750 1.2193 0.01527 0.00750 -0.1112 0.4488 1.0000
6.000 1.2442 0.01562 0.00778 -0.1107 0.4400 1.0000
6.250 1.2685 0.01592 0.00812 -0.1102 0.4305 1.0000
6.500 1.2927 0.01625 0.00845 -0.1097 0.4212 1.0000
6.750 1.3165 0.01659 0.00874 -0.1090 0.4117 1.0000
7.000 1.3395 0.01689 0.00912 -0.1083 0.4012 1.0000
7.250 1.3623 0.01725 0.00945 -0.1075 0.3912 1.0000
7.500 1.3845 0.01760 0.00979 -0.1067 0.3807 1.0000
7.750 1.4062 0.01794 0.01020 -0.1058 0.3698 1.0000
8.000 1.4276 0.01835 0.01062 -0.1048 0.3596 1.0000
8.250 1.4481 0.01877 0.01103 -0.1037 0.3489 1.0000
8.500 1.4676 0.01916 0.01149 -0.1025 0.3367 1.0000
8.750 1.4861 0.01960 0.01197 -0.1011 0.3242 1.0000
9.000 1.5034 0.02009 0.01249 -0.0995 0.3111 1.0000
9.250 1.5189 0.02062 0.01303 -0.0977 0.2967 1.0000
9.500 1.5328 0.02119 0.01361 -0.0957 0.2810 1.0000
9.750 1.5438 0.02180 0.01424 -0.0932 0.2649 1.0000
10.000 1.5534 0.02253 0.01498 -0.0905 0.2488 1.0000
10.250 1.5620 0.02339 0.01582 -0.0879 0.2325 1.0000
10.500 1.5697 0.02439 0.01679 -0.0854 0.2171 1.0000
10.750 1.5769 0.02551 0.01788 -0.0830 0.2035 1.0000
11.000 1.5837 0.02674 0.01909 -0.0807 0.1922 1.0000
11.250 1.5885 0.02816 0.02047 -0.0784 0.1824 1.0000
11.500 1.5955 0.02950 0.02187 -0.0764 0.1728 1.0000
11.750 1.6011 0.03099 0.02339 -0.0744 0.1648 1.0000
12.000 1.6057 0.03262 0.02504 -0.0725 0.1573 1.0000
12.250 1.6117 0.03419 0.02669 -0.0709 0.1503 1.0000
12.500 1.6150 0.03601 0.02854 -0.0692 0.1432 1.0000
12.750 1.6202 0.03776 0.03039 -0.0678 0.1365 1.0000
13.000 1.6235 0.03972 0.03241 -0.0665 0.1301 1.0000
13.250 1.6266 0.04175 0.03452 -0.0652 0.1244 1.0000
13.500 1.6305 0.04379 0.03666 -0.0642 0.1181 1.0000
13.750 1.6303 0.04627 0.03919 -0.0632 0.1132 1.0000
14.000 1.6353 0.04832 0.04140 -0.0624 0.1077 1.0000
14.250 1.6337 0.05114 0.04426 -0.0618 0.1024 1.0000
14.500 1.6371 0.05351 0.04678 -0.0613 0.0969 1.0000
14.750 1.6359 0.05650 0.04984 -0.0609 0.0914 1.0000
15.000 1.6355 0.05948 0.05292 -0.0607 0.0858 1.0000
15.250 1.6303 0.06318 0.05667 -0.0607 0.0791 1.0000
15.500 1.6264 0.06679 0.06038 -0.0609 0.0725 1.0000
15.750 1.6171 0.07122 0.06485 -0.0612 0.0666 1.0000
16.000 1.6076 0.07578 0.06948 -0.0618 0.0609 1.0000
16.250 1.5972 0.08057 0.07436 -0.0625 0.0559 1.0000
16.500 1.5846 0.08577 0.07964 -0.0635 0.0509 1.0000
16.750 1.5741 0.09076 0.08473 -0.0645 0.0456 1.0000
17.000 1.5604 0.09634 0.09039 -0.0658 0.0415 1.0000
17.250 1.5492 0.10162 0.09577 -0.0672 0.0372 1.0000
17.500 1.5355 0.10741 0.10164 -0.0689 0.0347 1.0000
17.750 1.5231 0.11307 0.10741 -0.0708 0.0326 1.0000
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