GOE 480 AIRFOIL (goe480-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 480 AIRFOIL (goe480-il) Reynolds number: 1,000,000 Max Cl/Cd: 138.31 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe480-il-1000000.txt Download as CSV file: xf-goe480-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 480 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
------ -------- --------- --------- -------- -------- --------
-12.500 -0.3088 0.12588 0.12409 -0.0399 1.0000 0.0260
-12.250 -0.3010 0.12412 0.12233 -0.0399 1.0000 0.0263
-12.000 -0.2939 0.12229 0.12052 -0.0400 1.0000 0.0268
-11.750 -0.3045 0.11678 0.11502 -0.0428 1.0000 0.0293
-11.250 -0.3063 0.10987 0.10813 -0.0433 1.0000 0.0293
-11.000 -0.2863 0.10747 0.10574 -0.0456 0.9992 0.0299
-10.750 -0.2658 0.10491 0.10316 -0.0487 0.9978 0.0303
-10.500 -0.2477 0.10187 0.10013 -0.0521 0.9946 0.0308
-10.250 -0.2335 0.09886 0.09711 -0.0549 0.9887 0.0323
-9.750 -0.2290 0.08562 0.08385 -0.0673 0.9714 0.0341
-9.500 -0.2000 0.08415 0.08237 -0.0701 0.9629 0.0345
-9.250 -0.1697 0.08089 0.07907 -0.0763 0.9540 0.0350
-8.750 -0.1188 0.06377 0.06174 -0.1064 0.9125 0.0389
-8.500 -0.0973 0.06251 0.06033 -0.1083 0.8810 0.0392
-8.250 -0.0913 0.06124 0.05892 -0.1077 0.8505 0.0395
-8.000 -0.0941 0.05953 0.05712 -0.1069 0.8263 0.0397
-7.750 -0.0892 0.05759 0.05511 -0.1075 0.8102 0.0402
-7.500 -0.0838 0.05520 0.05266 -0.1089 0.7968 0.0411
-7.250 -0.1207 0.03859 0.03571 -0.1214 0.7821 0.0432
-7.000 -0.1634 0.02189 0.01782 -0.1225 0.7723 0.0425
-6.750 -0.1465 0.01972 0.01527 -0.1215 0.7655 0.0431
-6.500 -0.1222 0.01930 0.01466 -0.1209 0.7588 0.0436
-6.250 -0.1062 0.01675 0.01170 -0.1198 0.7525 0.0442
-6.000 -0.0825 0.01573 0.01059 -0.1193 0.7471 0.0447
-5.750 -0.0574 0.01514 0.00993 -0.1189 0.7412 0.0450
-5.500 -0.0321 0.01470 0.00939 -0.1184 0.7356 0.0454
-5.250 -0.0059 0.01428 0.00893 -0.1180 0.7306 0.0458
-5.000 0.0202 0.01387 0.00846 -0.1177 0.7251 0.0462
-4.750 0.0462 0.01353 0.00805 -0.1173 0.7196 0.0467
-4.500 0.0724 0.01305 0.00748 -0.1169 0.7147 0.0472
-4.250 0.0987 0.01254 0.00688 -0.1165 0.7095 0.0476
-4.000 0.1250 0.01210 0.00635 -0.1161 0.7041 0.0480
-3.750 0.1514 0.01172 0.00587 -0.1156 0.6988 0.0484
-3.500 0.1785 0.01138 0.00548 -0.1153 0.6937 0.0489
-3.250 0.2054 0.01109 0.00513 -0.1150 0.6882 0.0492
-3.000 0.2321 0.01091 0.00486 -0.1146 0.6824 0.0495
-2.750 0.2598 0.01075 0.00469 -0.1143 0.6772 0.0498
-2.500 0.2853 0.01001 0.00390 -0.1139 0.6713 0.0507
-2.250 0.3114 0.00970 0.00355 -0.1134 0.6651 0.0513
-2.000 0.3386 0.00944 0.00331 -0.1131 0.6593 0.0519
-1.750 0.3653 0.00925 0.00311 -0.1127 0.6525 0.0524
-1.500 0.3921 0.00910 0.00293 -0.1124 0.6461 0.0529
-1.250 0.4191 0.00894 0.00276 -0.1120 0.6390 0.0535
-1.000 0.4454 0.00883 0.00261 -0.1115 0.6315 0.0542
-0.750 0.4726 0.00869 0.00248 -0.1112 0.6238 0.0549
-0.500 0.4989 0.00862 0.00236 -0.1108 0.6154 0.0556
-0.250 0.5260 0.00853 0.00227 -0.1105 0.6071 0.0563
0.000 0.5524 0.00853 0.00223 -0.1100 0.5978 0.0569
0.250 0.5788 0.00837 0.00205 -0.1096 0.5884 0.0578
0.500 0.6046 0.00828 0.00192 -0.1090 0.5786 0.0591
0.750 0.6308 0.00825 0.00186 -0.1085 0.5680 0.0604
1.000 0.6572 0.00823 0.00183 -0.1081 0.5581 0.0617
1.250 0.6830 0.00826 0.00181 -0.1075 0.5479 0.0631
1.500 0.7096 0.00826 0.00180 -0.1072 0.5387 0.0645
1.750 0.7356 0.00830 0.00181 -0.1067 0.5297 0.0661
2.000 0.7618 0.00830 0.00180 -0.1062 0.5207 0.0705
2.250 0.7877 0.00834 0.00183 -0.1057 0.5119 0.0748
2.500 0.8129 0.00821 0.00191 -0.1051 0.5035 0.1594
2.750 0.8376 0.00812 0.00200 -0.1045 0.4954 0.2433
3.000 0.8554 0.00737 0.00221 -0.1028 0.4873 0.6517
3.250 0.9305 0.00692 0.00244 -0.1133 0.4757 1.0000
3.500 0.9545 0.00706 0.00253 -0.1124 0.4673 1.0000
3.750 0.9791 0.00718 0.00261 -0.1117 0.4594 1.0000
4.000 1.0028 0.00734 0.00271 -0.1107 0.4503 1.0000
4.250 1.0273 0.00746 0.00282 -0.1100 0.4420 1.0000
4.750 1.0747 0.00777 0.00305 -0.1082 0.4228 1.0000
5.000 1.0977 0.00796 0.00318 -0.1072 0.4122 1.0000
5.250 1.1210 0.00813 0.00332 -0.1062 0.4025 1.0000
5.500 1.1444 0.00830 0.00346 -0.1053 0.3925 1.0000
5.750 1.1666 0.00853 0.00362 -0.1042 0.3809 1.0000
6.000 1.1894 0.00872 0.00379 -0.1031 0.3704 1.0000
6.250 1.2121 0.00891 0.00395 -0.1021 0.3611 1.0000
6.500 1.2335 0.00917 0.00415 -0.1009 0.3489 1.0000
6.750 1.2541 0.00945 0.00437 -0.0995 0.3339 1.0000
7.000 1.2742 0.00976 0.00460 -0.0981 0.3181 1.0000
7.250 1.2948 0.01003 0.00482 -0.0968 0.3051 1.0000
7.500 1.3153 0.01030 0.00506 -0.0954 0.2935 1.0000
7.750 1.3343 0.01062 0.00533 -0.0938 0.2801 1.0000
8.000 1.3523 0.01097 0.00561 -0.0920 0.2659 1.0000
8.250 1.3690 0.01133 0.00592 -0.0900 0.2531 1.0000
8.500 1.3831 0.01172 0.00624 -0.0875 0.2394 1.0000
8.750 1.3973 0.01211 0.00658 -0.0851 0.2263 1.0000
9.000 1.4120 0.01251 0.00693 -0.0828 0.2138 1.0000
9.250 1.4259 0.01296 0.00733 -0.0804 0.2007 1.0000
9.500 1.4384 0.01349 0.00779 -0.0779 0.1853 1.0000
9.750 1.4483 0.01417 0.00836 -0.0751 0.1668 1.0000
10.000 1.4543 0.01506 0.00910 -0.0719 0.1407 1.0000
10.250 1.4533 0.01635 0.01018 -0.0679 0.1066 1.0000
10.500 1.4509 0.01783 0.01148 -0.0640 0.0791 1.0000
10.750 1.4583 0.01887 0.01247 -0.0615 0.0682 1.0000
11.000 1.4675 0.01985 0.01343 -0.0595 0.0617 1.0000
11.250 1.4790 0.02074 0.01433 -0.0578 0.0572 1.0000
11.500 1.4886 0.02180 0.01539 -0.0560 0.0530 1.0000
11.750 1.5003 0.02276 0.01638 -0.0546 0.0496 1.0000
12.000 1.5097 0.02392 0.01754 -0.0531 0.0461 1.0000
12.250 1.5203 0.02504 0.01869 -0.0517 0.0431 1.0000
12.500 1.5298 0.02627 0.01994 -0.0504 0.0404 1.0000
12.750 1.5377 0.02767 0.02135 -0.0491 0.0377 1.0000
13.000 1.5472 0.02898 0.02271 -0.0480 0.0356 1.0000
13.250 1.5533 0.03059 0.02433 -0.0467 0.0335 1.0000
13.500 1.5608 0.03212 0.02592 -0.0456 0.0320 1.0000
13.750 1.5680 0.03372 0.02754 -0.0446 0.0303 1.0000
14.000 1.5725 0.03559 0.02946 -0.0436 0.0291 1.0000
14.250 1.5752 0.03766 0.03157 -0.0425 0.0278 1.0000
14.500 1.5810 0.03950 0.03348 -0.0417 0.0269 1.0000
14.750 1.5851 0.04155 0.03559 -0.0410 0.0261 1.0000
15.000 1.5873 0.04382 0.03791 -0.0402 0.0252 1.0000
15.250 1.5863 0.04648 0.04062 -0.0395 0.0244 1.0000
15.500 1.5849 0.04928 0.04349 -0.0389 0.0237 1.0000
15.750 1.5881 0.05162 0.04591 -0.0385 0.0231 1.0000
16.000 1.5906 0.05406 0.04842 -0.0382 0.0224 1.0000
16.250 1.5892 0.05701 0.05144 -0.0379 0.0220 1.0000
16.500 1.5875 0.06006 0.05456 -0.0378 0.0214 1.0000
16.750 1.5827 0.06355 0.05811 -0.0378 0.0209 1.0000
17.000 1.5751 0.06741 0.06204 -0.0378 0.0204 1.0000
17.250 1.5668 0.07144 0.06617 -0.0380 0.0201 1.0000
17.500 1.5653 0.07468 0.06949 -0.0383 0.0198 1.0000
17.750 1.5616 0.07822 0.07312 -0.0386 0.0194 1.0000
18.000 1.5572 0.08188 0.07687 -0.0390 0.0191 1.0000
18.250 1.5518 0.08571 0.08078 -0.0395 0.0188 1.0000
18.500 1.5462 0.08962 0.08477 -0.0401 0.0185 1.0000
18.750 1.5398 0.09374 0.08896 -0.0409 0.0181 1.0000
19.000 1.5305 0.09828 0.09358 -0.0419 0.0179 1.0000
19.250 1.5213 0.10290 0.09829 -0.0431 0.0176 1.0000
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