GOE 478 AIRFOIL (goe478-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 478 AIRFOIL (goe478-il) Reynolds number: 500,000 Max Cl/Cd: 95.42 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe478-il-500000-n5.txt Download as CSV file: xf-goe478-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 478 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
------ -------- --------- --------- -------- -------- --------
-12.250 -0.6979 0.03757 0.03382 -0.1100 0.9741 0.0270
-12.000 -0.7024 0.03391 0.02986 -0.1117 0.9587 0.0270
-11.750 -0.6903 0.03086 0.02651 -0.1138 0.9468 0.0271
-11.500 -0.6665 0.02844 0.02387 -0.1167 0.9385 0.0273
-11.250 -0.6375 0.02663 0.02190 -0.1194 0.9293 0.0275
-11.000 -0.6077 0.02520 0.02031 -0.1217 0.9188 0.0277
-10.750 -0.5784 0.02406 0.01903 -0.1233 0.9073 0.0279
-10.500 -0.5545 0.02301 0.01781 -0.1238 0.8935 0.0280
-10.250 -0.5334 0.02218 0.01683 -0.1233 0.8798 0.0282
-10.000 -0.5132 0.02139 0.01589 -0.1225 0.8672 0.0284
-9.500 -0.4738 0.01996 0.01416 -0.1204 0.8430 0.0288
-9.250 -0.4532 0.01936 0.01343 -0.1193 0.8324 0.0291
-9.000 -0.4326 0.01877 0.01269 -0.1182 0.8209 0.0294
-8.750 -0.4117 0.01818 0.01195 -0.1171 0.8107 0.0297
-8.500 -0.3902 0.01765 0.01128 -0.1161 0.8009 0.0300
-8.250 -0.3682 0.01711 0.01060 -0.1151 0.7928 0.0303
-8.000 -0.3456 0.01661 0.00998 -0.1142 0.7854 0.0305
-7.750 -0.3226 0.01614 0.00939 -0.1133 0.7794 0.0307
-7.500 -0.2990 0.01570 0.00885 -0.1125 0.7739 0.0309
-7.250 -0.2759 0.01516 0.00826 -0.1117 0.7688 0.0312
-7.000 -0.2522 0.01474 0.00777 -0.1109 0.7642 0.0315
-6.750 -0.2278 0.01436 0.00735 -0.1102 0.7602 0.0318
-6.500 -0.2031 0.01403 0.00699 -0.1096 0.7557 0.0321
-6.250 -0.1783 0.01371 0.00663 -0.1089 0.7511 0.0325
-6.000 -0.1532 0.01342 0.00628 -0.1083 0.7470 0.0329
-5.750 -0.1279 0.01314 0.00595 -0.1078 0.7434 0.0334
-5.500 -0.1024 0.01285 0.00564 -0.1072 0.7399 0.0338
-5.250 -0.0769 0.01258 0.00532 -0.1066 0.7362 0.0343
-5.000 -0.0512 0.01235 0.00505 -0.1061 0.7320 0.0348
-4.750 -0.0256 0.01210 0.00476 -0.1055 0.7283 0.0355
-4.250 0.0262 0.01165 0.00430 -0.1045 0.7214 0.0369
-4.000 0.0521 0.01145 0.00409 -0.1039 0.7165 0.0378
-3.750 0.0781 0.01127 0.00389 -0.1034 0.7120 0.0386
-3.500 0.1043 0.01112 0.00369 -0.1029 0.7080 0.0395
-3.250 0.1305 0.01094 0.00350 -0.1024 0.7046 0.0406
-3.000 0.1567 0.01076 0.00335 -0.1019 0.7005 0.0419
-2.750 0.1830 0.01061 0.00320 -0.1014 0.6957 0.0434
-2.500 0.2092 0.01050 0.00306 -0.1009 0.6905 0.0452
-2.250 0.2353 0.01036 0.00292 -0.1004 0.6860 0.0478
-2.000 0.2616 0.01022 0.00280 -0.0999 0.6810 0.0509
-1.750 0.2875 0.01008 0.00268 -0.0993 0.6751 0.0552
-1.500 0.3131 0.00996 0.00256 -0.0987 0.6688 0.0617
-1.250 0.3387 0.00978 0.00250 -0.0981 0.6613 0.0787
-1.000 0.3639 0.00970 0.00245 -0.0974 0.6517 0.0969
-0.750 0.3896 0.00962 0.00239 -0.0967 0.6408 0.1075
-0.500 0.4145 0.00956 0.00233 -0.0959 0.6270 0.1165
-0.250 0.4382 0.00953 0.00227 -0.0949 0.6058 0.1267
0.250 0.4799 0.00964 0.00226 -0.0917 0.5509 0.1679
0.500 0.5020 0.00973 0.00232 -0.0905 0.5338 0.1911
0.750 0.5255 0.00980 0.00238 -0.0895 0.5219 0.2088
1.000 0.5490 0.00986 0.00243 -0.0885 0.5125 0.2255
1.250 0.5732 0.00988 0.00248 -0.0877 0.5042 0.2456
1.500 0.5964 0.00990 0.00255 -0.0866 0.4963 0.2745
1.750 0.6187 0.00969 0.00263 -0.0856 0.4900 0.3804
2.000 0.6385 0.00937 0.00273 -0.0840 0.4839 0.5329
2.250 0.6531 0.00898 0.00286 -0.0812 0.4780 0.7156
2.500 0.7119 0.00876 0.00320 -0.0874 0.4684 0.9486
2.750 0.7674 0.00903 0.00337 -0.0933 0.4555 0.9789
3.250 0.8463 0.00941 0.00363 -0.0983 0.4383 0.9996
3.500 0.8696 0.00952 0.00372 -0.0973 0.4315 1.0000
3.750 0.8891 0.00967 0.00382 -0.0955 0.4237 1.0000
4.000 0.9093 0.00980 0.00392 -0.0939 0.4170 1.0000
4.250 0.9299 0.00993 0.00403 -0.0923 0.4102 1.0000
4.500 0.9489 0.01010 0.00415 -0.0905 0.4032 1.0000
4.750 0.9698 0.01023 0.00427 -0.0890 0.3962 1.0000
5.000 0.9892 0.01040 0.00441 -0.0872 0.3883 1.0000
5.250 1.0086 0.01057 0.00455 -0.0854 0.3795 1.0000
5.500 1.0259 0.01079 0.00471 -0.0833 0.3681 1.0000
5.750 1.0444 0.01098 0.00487 -0.0814 0.3560 1.0000
6.000 1.0609 0.01121 0.00505 -0.0791 0.3440 1.0000
6.250 1.0750 0.01146 0.00524 -0.0763 0.3303 1.0000
6.500 1.0881 0.01176 0.00546 -0.0734 0.3129 1.0000
6.750 1.0999 0.01215 0.00574 -0.0704 0.2914 1.0000
7.000 1.1105 0.01263 0.00608 -0.0673 0.2677 1.0000
7.250 1.1211 0.01316 0.00649 -0.0642 0.2436 1.0000
7.500 1.1336 0.01367 0.00689 -0.0616 0.2259 1.0000
7.750 1.1474 0.01414 0.00730 -0.0592 0.2117 1.0000
8.000 1.1616 0.01462 0.00773 -0.0570 0.1998 1.0000
8.250 1.1755 0.01514 0.00819 -0.0548 0.1883 1.0000
8.500 1.1902 0.01564 0.00865 -0.0528 0.1778 1.0000
8.750 1.2048 0.01615 0.00913 -0.0508 0.1685 1.0000
9.000 1.2183 0.01674 0.00968 -0.0488 0.1591 1.0000
9.250 1.2330 0.01730 0.01022 -0.0470 0.1506 1.0000
9.500 1.2465 0.01793 0.01082 -0.0451 0.1423 1.0000
9.750 1.2597 0.01860 0.01146 -0.0432 0.1341 1.0000
10.000 1.2737 0.01926 0.01211 -0.0416 0.1275 1.0000
10.250 1.2863 0.02001 0.01284 -0.0398 0.1205 1.0000
10.500 1.2997 0.02074 0.01358 -0.0382 0.1147 1.0000
10.750 1.3118 0.02158 0.01440 -0.0365 0.1084 1.0000
11.000 1.3244 0.02241 0.01524 -0.0350 0.1030 1.0000
11.250 1.3352 0.02340 0.01621 -0.0334 0.0965 1.0000
11.500 1.3471 0.02433 0.01715 -0.0320 0.0914 1.0000
11.750 1.3572 0.02542 0.01823 -0.0305 0.0859 1.0000
12.000 1.3677 0.02650 0.01933 -0.0291 0.0811 1.0000
12.250 1.3771 0.02770 0.02054 -0.0277 0.0768 1.0000
12.500 1.3870 0.02890 0.02176 -0.0265 0.0736 1.0000
12.750 1.3961 0.03018 0.02307 -0.0252 0.0707 1.0000
13.000 1.4041 0.03158 0.02448 -0.0240 0.0683 1.0000
13.250 1.4125 0.03298 0.02593 -0.0229 0.0665 1.0000
13.500 1.4208 0.03442 0.02743 -0.0218 0.0649 1.0000
13.750 1.4282 0.03595 0.02901 -0.0208 0.0633 1.0000
14.000 1.4346 0.03762 0.03071 -0.0198 0.0620 1.0000
14.250 1.4392 0.03948 0.03261 -0.0189 0.0605 1.0000
14.500 1.4439 0.04139 0.03458 -0.0180 0.0593 1.0000
14.750 1.4501 0.04319 0.03645 -0.0173 0.0586 1.0000
15.000 1.4551 0.04515 0.03849 -0.0166 0.0578 1.0000
15.250 1.4598 0.04720 0.04061 -0.0161 0.0570 1.0000
15.500 1.4632 0.04943 0.04291 -0.0156 0.0561 1.0000
15.750 1.4654 0.05184 0.04538 -0.0152 0.0552 1.0000
16.000 1.4656 0.05453 0.04812 -0.0149 0.0540 1.0000
16.250 1.4649 0.05741 0.05106 -0.0147 0.0531 1.0000
16.500 1.4660 0.06014 0.05386 -0.0147 0.0523 1.0000
16.750 1.4698 0.06259 0.05640 -0.0147 0.0514 1.0000
17.000 1.4718 0.06528 0.05917 -0.0148 0.0506 1.0000
17.250 1.4725 0.06814 0.06211 -0.0150 0.0497 1.0000
17.500 1.4723 0.07117 0.06521 -0.0153 0.0488 1.0000
17.750 1.4707 0.07439 0.06849 -0.0156 0.0482 1.0000
18.000 1.4682 0.07774 0.07191 -0.0161 0.0474 1.0000
18.250 1.4645 0.08124 0.07547 -0.0166 0.0469 1.0000
18.500 1.4607 0.08480 0.07911 -0.0172 0.0463 1.0000
18.750 1.4609 0.08786 0.08227 -0.0177 0.0458 1.0000
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