GOE 428 AIRFOIL (goe428-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 428 AIRFOIL (goe428-il) Reynolds number: 500,000 Max Cl/Cd: 102.51 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe428-il-500000-n5.txt Download as CSV file: xf-goe428-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 428 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
------ -------- --------- --------- -------- -------- --------
-9.250 -0.2840 0.10625 0.10405 -0.0301 1.0000 0.0076
-9.000 -0.2809 0.10376 0.10159 -0.0302 1.0000 0.0080
-8.750 -0.2784 0.10127 0.09912 -0.0302 1.0000 0.0089
-8.500 -0.2706 0.09797 0.09585 -0.0320 0.9990 0.0083
-8.250 -0.2536 0.09418 0.09207 -0.0382 0.9934 0.0100
-8.000 -0.2388 0.09048 0.08838 -0.0423 0.9879 0.0100
-7.750 -0.2254 0.08678 0.08468 -0.0459 0.9801 0.0101
-7.500 -0.2109 0.08284 0.08075 -0.0500 0.9707 0.0101
-7.000 -0.1739 0.07405 0.07193 -0.0595 0.9537 0.0090
-6.750 -0.1466 0.06626 0.06409 -0.0712 0.9385 0.0066
-6.500 -0.1165 0.06095 0.05871 -0.0802 0.9178 0.0065
-6.250 -0.0885 0.05591 0.05354 -0.0882 0.8891 0.0064
-6.000 -0.0671 0.05138 0.04885 -0.0937 0.8627 0.0063
-5.750 -0.0468 0.04565 0.04292 -0.0993 0.8398 0.0065
-5.500 -0.0242 0.03915 0.03618 -0.1050 0.8232 0.0066
-5.250 -0.0072 0.01696 0.01248 -0.1139 0.8159 0.0070
-5.000 0.0175 0.01611 0.01135 -0.1136 0.7996 0.0075
-4.750 0.0422 0.01505 0.00998 -0.1132 0.7831 0.0081
-4.500 0.0668 0.01357 0.00809 -0.1127 0.7679 0.0086
-4.250 0.0922 0.01247 0.00665 -0.1122 0.7555 0.0092
-4.000 0.1183 0.01170 0.00562 -0.1118 0.7441 0.0099
-3.750 0.1442 0.01085 0.00453 -0.1113 0.7334 0.0110
-3.500 0.1709 0.01077 0.00441 -0.1110 0.7218 0.0130
-3.250 0.1974 0.01050 0.00402 -0.1106 0.7093 0.0148
-3.000 0.2235 0.01011 0.00348 -0.1102 0.6961 0.0167
-2.750 0.2500 0.00996 0.00325 -0.1098 0.6829 0.0204
-2.500 0.2767 0.00988 0.00308 -0.1095 0.6708 0.0245
-2.250 0.3035 0.00986 0.00295 -0.1092 0.6593 0.0265
-2.000 0.3297 0.00956 0.00256 -0.1088 0.6482 0.0301
-1.750 0.3561 0.00944 0.00234 -0.1085 0.6368 0.0327
-1.250 0.4092 0.00927 0.00199 -0.1078 0.6140 0.0363
-1.000 0.4359 0.00921 0.00184 -0.1075 0.6037 0.0377
-0.750 0.4625 0.00917 0.00171 -0.1072 0.5934 0.0384
-0.500 0.4891 0.00912 0.00157 -0.1069 0.5823 0.0404
-0.250 0.5158 0.00906 0.00148 -0.1066 0.5708 0.0482
0.000 0.5418 0.00896 0.00147 -0.1062 0.5564 0.0967
0.250 0.5676 0.00901 0.00149 -0.1058 0.5371 0.1245
0.500 0.5932 0.00911 0.00150 -0.1054 0.5120 0.1376
0.750 0.6185 0.00924 0.00152 -0.1049 0.4858 0.1482
1.250 0.6694 0.00942 0.00161 -0.1041 0.4462 0.1874
1.500 0.6939 0.00923 0.00175 -0.1037 0.4299 0.3580
2.000 0.7534 0.00826 0.00203 -0.1050 0.4025 1.0000
2.250 0.7789 0.00844 0.00213 -0.1045 0.3917 1.0000
2.500 0.8047 0.00860 0.00223 -0.1042 0.3824 1.0000
2.750 0.8305 0.00876 0.00235 -0.1038 0.3740 1.0000
3.250 0.8814 0.00913 0.00260 -0.1030 0.3544 1.0000
3.500 0.9068 0.00932 0.00275 -0.1025 0.3454 1.0000
3.750 0.9322 0.00951 0.00290 -0.1021 0.3376 1.0000
4.000 0.9578 0.00968 0.00306 -0.1018 0.3317 1.0000
4.250 0.9835 0.00984 0.00324 -0.1014 0.3263 1.0000
4.500 1.0088 0.01002 0.00342 -0.1010 0.3217 1.0000
4.750 1.0343 0.01019 0.00360 -0.1006 0.3157 1.0000
5.000 1.0595 0.01038 0.00380 -0.1002 0.3095 1.0000
5.250 1.0845 0.01058 0.00403 -0.0998 0.3038 1.0000
5.500 1.1087 0.01085 0.00425 -0.0992 0.2869 1.0000
5.750 1.1316 0.01122 0.00451 -0.0985 0.2603 1.0000
6.000 1.1515 0.01185 0.00489 -0.0974 0.2078 1.0000
6.250 1.1597 0.01361 0.00599 -0.0946 0.0967 1.0000
6.500 1.1787 0.01433 0.00660 -0.0933 0.0744 1.0000
6.750 1.1939 0.01538 0.00743 -0.0914 0.0226 1.0000
7.000 1.2140 0.01596 0.00803 -0.0902 0.0139 1.0000
7.250 1.2349 0.01643 0.00858 -0.0891 0.0117 1.0000
7.500 1.2536 0.01707 0.00927 -0.0877 0.0092 1.0000
7.750 1.2725 0.01766 0.00997 -0.0863 0.0082 1.0000
8.000 1.2908 0.01827 0.01066 -0.0849 0.0074 1.0000
8.250 1.3075 0.01894 0.01141 -0.0832 0.0068 1.0000
8.500 1.3219 0.01974 0.01227 -0.0812 0.0062 1.0000
8.750 1.3320 0.02064 0.01326 -0.0785 0.0056 1.0000
9.000 1.3443 0.02132 0.01403 -0.0762 0.0052 1.0000
9.250 1.3527 0.02224 0.01504 -0.0733 0.0048 1.0000
9.500 1.3606 0.02321 0.01610 -0.0705 0.0046 1.0000
9.750 1.3673 0.02428 0.01725 -0.0678 0.0043 1.0000
10.000 1.3726 0.02549 0.01854 -0.0652 0.0042 1.0000
10.250 1.3757 0.02691 0.02010 -0.0625 0.0040 1.0000
10.500 1.3742 0.02879 0.02208 -0.0598 0.0039 1.0000
10.750 1.3707 0.03099 0.02441 -0.0572 0.0037 1.0000
11.000 1.3715 0.03303 0.02657 -0.0553 0.0037 1.0000
11.250 1.3716 0.03526 0.02892 -0.0537 0.0036 1.0000
11.500 1.3707 0.03774 0.03154 -0.0523 0.0035 1.0000
11.750 1.3714 0.04016 0.03407 -0.0512 0.0034 1.0000
12.000 1.3732 0.04256 0.03660 -0.0503 0.0032 1.0000
12.250 1.3707 0.04557 0.03974 -0.0493 0.0032 1.0000
12.500 1.3721 0.04819 0.04248 -0.0489 0.0030 1.0000
12.750 1.3753 0.05069 0.04507 -0.0488 0.0028 1.0000
13.000 1.3761 0.05355 0.04804 -0.0487 0.0027 1.0000
13.250 1.3746 0.05676 0.05137 -0.0486 0.0027 1.0000
13.500 1.3736 0.06002 0.05474 -0.0487 0.0026 1.0000
13.750 1.3716 0.06352 0.05836 -0.0490 0.0025 1.0000
14.000 1.3686 0.06723 0.06219 -0.0494 0.0025 1.0000
14.250 1.3657 0.07106 0.06614 -0.0500 0.0025 1.0000
14.500 1.3616 0.07517 0.07039 -0.0508 0.0024 1.0000
14.750 1.3528 0.08011 0.07548 -0.0516 0.0023 1.0000
15.000 1.3473 0.08473 0.08027 -0.0527 0.0023 1.0000
15.250 1.3406 0.08975 0.08548 -0.0542 0.0023 1.0000
15.500 1.3325 0.09518 0.09110 -0.0561 0.0023 1.0000
15.750 1.3225 0.10111 0.09725 -0.0583 0.0022 1.0000
16.000 1.3112 0.10749 0.10386 -0.0609 0.0022 1.0000
16.250 1.2998 0.11409 0.11065 -0.0639 0.0022 1.0000
16.500 1.2875 0.12106 0.11781 -0.0673 0.0022 1.0000
16.750 1.2737 0.12856 0.12550 -0.0712 0.0022 1.0000
17.000 1.2596 0.13640 0.13352 -0.0755 0.0022 1.0000
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Polar data table (+)
Polar graphs
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