GOE 458 AIRFOIL (goe458-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 458 AIRFOIL (goe458-il) Reynolds number: 50,000 Max Cl/Cd: 42.65 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe458-il-50000-n5.txt Download as CSV file: xf-goe458-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 458 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.500 -0.3190 0.10634 0.10032 -0.0307 1.0000 0.0933
-7.250 -0.3370 0.10653 0.10068 -0.0288 1.0000 0.0943
-7.000 -0.3506 0.10622 0.10051 -0.0288 1.0000 0.0949
-6.750 -0.3571 0.10452 0.09895 -0.0289 1.0000 0.0954
-6.500 -0.3496 0.09954 0.09398 -0.0246 1.0000 0.0973
-6.250 -0.3504 0.09703 0.09153 -0.0227 1.0000 0.0992
-6.000 -0.3531 0.09492 0.08949 -0.0216 1.0000 0.1013
-5.750 -0.3558 0.09285 0.08749 -0.0213 1.0000 0.1038
-5.500 -0.3462 0.09151 0.08617 -0.0313 0.9970 0.1091
-5.250 -0.3249 0.08624 0.08090 -0.0340 0.9910 0.1104
-4.750 -0.2565 0.07288 0.06719 -0.0501 0.9773 0.0533
-4.500 -0.2099 0.06564 0.05973 -0.0625 0.9696 0.0428
-4.250 -0.1861 0.06179 0.05579 -0.0649 0.9625 0.0405
-4.000 -0.1472 0.05670 0.05050 -0.0721 0.9564 0.0394
-3.750 -0.1096 0.05170 0.04525 -0.0786 0.9488 0.0392
-3.500 -0.0639 0.04613 0.03926 -0.0861 0.9434 0.0392
-3.250 -0.0232 0.04126 0.03386 -0.0915 0.9370 0.0386
-3.000 0.0200 0.03671 0.02861 -0.0962 0.9316 0.0380
-2.750 0.0620 0.03313 0.02421 -0.0997 0.9267 0.0382
-2.500 0.0977 0.03062 0.02095 -0.1013 0.9198 0.0399
-2.250 0.1382 0.02862 0.01841 -0.1037 0.9152 0.0459
-2.000 0.1680 0.02735 0.01674 -0.1039 0.9068 0.0512
-1.750 0.2097 0.02604 0.01503 -0.1061 0.9020 0.0648
-1.500 0.2429 0.02511 0.01426 -0.1070 0.8941 0.1181
-1.250 0.2790 0.02526 0.01467 -0.1090 0.8877 0.2901
-1.000 0.3082 0.02499 0.01410 -0.1093 0.8785 0.3159
-0.750 0.3479 0.02455 0.01340 -0.1114 0.8736 0.3453
-0.500 0.3752 0.02431 0.01312 -0.1115 0.8641 0.3814
-0.250 0.4095 0.02357 0.01278 -0.1129 0.8584 0.4794
0.250 0.4685 0.02292 0.01236 -0.1132 0.8413 1.0000
0.500 0.5013 0.02309 0.01223 -0.1141 0.8343 1.0000
0.750 0.5269 0.02342 0.01235 -0.1139 0.8248 1.0000
1.000 0.5616 0.02354 0.01225 -0.1151 0.8192 1.0000
1.250 0.5844 0.02396 0.01254 -0.1144 0.8092 1.0000
1.500 0.6148 0.02418 0.01265 -0.1149 0.8023 1.0000
2.000 0.6665 0.02489 0.01325 -0.1145 0.7855 1.0000
2.250 0.6958 0.02514 0.01347 -0.1148 0.7785 1.0000
2.500 0.7188 0.02561 0.01398 -0.1142 0.7695 1.0000
2.750 0.7500 0.02577 0.01417 -0.1147 0.7634 1.0000
3.000 0.7709 0.02633 0.01478 -0.1138 0.7537 1.0000
3.250 0.8043 0.02639 0.01491 -0.1145 0.7481 1.0000
3.750 0.8495 0.02717 0.01597 -0.1127 0.7269 1.0000
4.000 0.8792 0.02692 0.01585 -0.1121 0.7138 1.0000
4.250 0.9082 0.02657 0.01572 -0.1112 0.6987 1.0000
4.500 0.9364 0.02630 0.01564 -0.1102 0.6836 1.0000
4.750 0.9635 0.02627 0.01583 -0.1094 0.6704 1.0000
5.000 0.9905 0.02632 0.01614 -0.1086 0.6580 1.0000
5.250 1.0173 0.02638 0.01658 -0.1078 0.6449 1.0000
5.500 1.0422 0.02573 0.01614 -0.1053 0.6148 1.0000
5.750 1.0574 0.02479 0.01505 -0.1002 0.5483 1.0000
6.000 1.0633 0.02503 0.01513 -0.0953 0.4684 1.0000
6.250 1.0655 0.02611 0.01526 -0.0903 0.3230 1.0000
6.500 1.0605 0.02851 0.01670 -0.0859 0.2148 1.0000
7.000 1.0515 0.03392 0.02078 -0.0784 0.0427 1.0000
7.250 1.0590 0.03577 0.02288 -0.0759 0.0374 1.0000
7.500 1.0659 0.03769 0.02500 -0.0735 0.0338 1.0000
7.750 1.0723 0.03967 0.02721 -0.0712 0.0307 1.0000
8.000 1.0759 0.04191 0.02966 -0.0689 0.0290 1.0000
8.250 1.0775 0.04439 0.03234 -0.0667 0.0281 1.0000
8.500 1.0816 0.04667 0.03483 -0.0647 0.0276 1.0000
8.750 1.0873 0.04892 0.03732 -0.0627 0.0270 1.0000
9.000 1.0962 0.05104 0.03968 -0.0609 0.0262 1.0000
9.250 1.1111 0.05297 0.04185 -0.0590 0.0248 1.0000
9.500 1.1366 0.05476 0.04386 -0.0574 0.0231 1.0000
9.750 1.1797 0.05697 0.04634 -0.0565 0.0224 1.0000
10.000 1.2143 0.06016 0.05005 -0.0560 0.0225 1.0000
10.250 1.2326 0.06364 0.05396 -0.0548 0.0227 1.0000
10.500 1.2399 0.06719 0.05792 -0.0531 0.0230 1.0000
10.750 1.2400 0.07078 0.06190 -0.0512 0.0233 1.0000
11.000 1.2354 0.07451 0.06599 -0.0494 0.0236 1.0000
11.250 1.2270 0.07843 0.07023 -0.0480 0.0238 1.0000
11.500 1.2160 0.08257 0.07468 -0.0471 0.0240 1.0000
11.750 1.2031 0.08698 0.07938 -0.0467 0.0242 1.0000
12.000 1.1885 0.09176 0.08442 -0.0471 0.0244 1.0000
12.250 1.1725 0.09692 0.08982 -0.0481 0.0246 1.0000
12.500 1.1560 0.10244 0.09557 -0.0499 0.0248 1.0000
12.750 1.1389 0.10846 0.10178 -0.0525 0.0249 1.0000
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