GOE 428 AIRFOIL (goe428-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 428 AIRFOIL (goe428-il) Reynolds number: 200,000 Max Cl/Cd: 78.16 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe428-il-200000-n5.txt Download as CSV file: xf-goe428-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.2019 0.09741 0.09433 -0.0331 1.0000 0.0188
-9.000 -0.2021 0.09487 0.09184 -0.0325 1.0000 0.0192
-8.750 -0.2021 0.09224 0.08923 -0.0322 0.9997 0.0195
-8.500 -0.1913 0.08816 0.08515 -0.0350 0.9962 0.0200
-8.250 -0.1809 0.08407 0.08107 -0.0378 0.9918 0.0208
-8.000 -0.1696 0.07995 0.07695 -0.0409 0.9873 0.0213
-7.750 -0.1595 0.07592 0.07293 -0.0437 0.9811 0.0218
-7.500 -0.1488 0.07180 0.06881 -0.0468 0.9747 0.0227
-7.250 -0.1376 0.06771 0.06473 -0.0503 0.9675 0.0235
-7.000 -0.1278 0.06443 0.06146 -0.0563 0.9553 0.0260
-6.750 -0.1165 0.06036 0.05739 -0.0607 0.9428 0.0262
-6.250 -0.1633 0.06896 0.06580 -0.0636 0.9513 0.0149
-6.000 -0.1362 0.06419 0.06099 -0.0707 0.9413 0.0148
-5.500 -0.0723 0.05421 0.05084 -0.0860 0.9192 0.0157
-5.250 -0.0429 0.04887 0.04538 -0.0924 0.9089 0.0152
-5.000 -0.0103 0.04359 0.03993 -0.0986 0.8980 0.0150
-4.750 0.0224 0.03816 0.03426 -0.1040 0.8862 0.0149
-4.500 0.0555 0.03230 0.02803 -0.1084 0.8744 0.0149
-4.250 0.0869 0.02560 0.02073 -0.1114 0.8623 0.0153
-4.000 0.1155 0.02119 0.01558 -0.1127 0.8477 0.0170
-3.750 0.1432 0.01940 0.01336 -0.1130 0.8306 0.0183
-3.500 0.1705 0.01764 0.01110 -0.1128 0.8145 0.0199
-3.250 0.1975 0.01633 0.00936 -0.1124 0.8011 0.0226
-3.000 0.2246 0.01546 0.00812 -0.1119 0.7900 0.0260
-2.750 0.2510 0.01424 0.00662 -0.1115 0.7794 0.0289
-2.500 0.2776 0.01383 0.00609 -0.1112 0.7684 0.0341
-2.250 0.3042 0.01330 0.00535 -0.1106 0.7572 0.0377
-2.000 0.3301 0.01273 0.00469 -0.1102 0.7458 0.0432
-1.750 0.3564 0.01238 0.00423 -0.1098 0.7345 0.0465
-1.500 0.3827 0.01215 0.00386 -0.1093 0.7229 0.0503
-1.250 0.4090 0.01189 0.00348 -0.1088 0.7108 0.0537
-1.000 0.4352 0.01167 0.00317 -0.1084 0.6983 0.0585
-0.750 0.4614 0.01149 0.00296 -0.1079 0.6859 0.0708
-0.500 0.4875 0.01136 0.00291 -0.1075 0.6739 0.1161
-0.250 0.5138 0.01134 0.00282 -0.1071 0.6619 0.1421
0.000 0.5398 0.01131 0.00273 -0.1067 0.6496 0.1646
0.250 0.5655 0.01123 0.00267 -0.1062 0.6368 0.1915
0.500 0.5883 0.01062 0.00276 -0.1056 0.6243 0.4497
1.000 0.6524 0.00975 0.00272 -0.1070 0.5973 1.0000
1.500 0.7035 0.01005 0.00277 -0.1060 0.5696 1.0000
1.750 0.7287 0.01022 0.00281 -0.1054 0.5542 1.0000
2.000 0.7536 0.01040 0.00288 -0.1048 0.5357 1.0000
2.250 0.7781 0.01060 0.00295 -0.1041 0.5144 1.0000
2.500 0.8022 0.01083 0.00304 -0.1033 0.4940 1.0000
2.750 0.8264 0.01107 0.00317 -0.1026 0.4736 1.0000
3.000 0.8506 0.01133 0.00332 -0.1020 0.4569 1.0000
3.250 0.8750 0.01158 0.00349 -0.1013 0.4433 1.0000
3.500 0.8995 0.01183 0.00370 -0.1008 0.4317 1.0000
3.750 0.9239 0.01210 0.00391 -0.1002 0.4215 1.0000
4.000 0.9486 0.01235 0.00414 -0.0996 0.4119 1.0000
4.250 0.9732 0.01262 0.00439 -0.0991 0.4031 1.0000
4.500 0.9976 0.01290 0.00468 -0.0985 0.3949 1.0000
4.750 1.0223 0.01317 0.00496 -0.0980 0.3872 1.0000
5.000 1.0465 0.01346 0.00526 -0.0974 0.3800 1.0000
5.250 1.0712 0.01373 0.00560 -0.0969 0.3733 1.0000
5.500 1.0951 0.01404 0.00593 -0.0963 0.3656 1.0000
5.750 1.1193 0.01432 0.00628 -0.0957 0.3576 1.0000
6.000 1.1427 0.01466 0.00664 -0.0951 0.3499 1.0000
6.250 1.1646 0.01498 0.00702 -0.0941 0.3307 1.0000
6.500 1.1848 0.01540 0.00738 -0.0929 0.3060 1.0000
6.750 1.2049 0.01585 0.00777 -0.0918 0.2717 1.0000
7.000 1.2159 0.01705 0.00844 -0.0894 0.1795 1.0000
7.250 1.2168 0.01933 0.01001 -0.0859 0.0796 1.0000
7.500 1.2235 0.02098 0.01140 -0.0829 0.0252 1.0000
7.750 1.2384 0.02187 0.01242 -0.0809 0.0194 1.0000
8.000 1.2509 0.02288 0.01361 -0.0786 0.0163 1.0000
8.250 1.2583 0.02409 0.01504 -0.0755 0.0145 1.0000
8.500 1.2663 0.02516 0.01626 -0.0727 0.0135 1.0000
8.750 1.2751 0.02618 0.01742 -0.0701 0.0123 1.0000
9.000 1.2806 0.02744 0.01882 -0.0672 0.0114 1.0000
9.250 1.2833 0.02894 0.02046 -0.0643 0.0108 1.0000
9.500 1.2846 0.03062 0.02227 -0.0616 0.0104 1.0000
9.750 1.2844 0.03254 0.02430 -0.0591 0.0100 1.0000
10.000 1.2829 0.03472 0.02659 -0.0569 0.0097 1.0000
10.250 1.2807 0.03714 0.02911 -0.0550 0.0094 1.0000
10.500 1.2757 0.04001 0.03207 -0.0531 0.0090 1.0000
10.750 1.2745 0.04273 0.03487 -0.0516 0.0086 1.0000
11.000 1.2802 0.04478 0.03705 -0.0506 0.0082 1.0000
11.250 1.2849 0.04702 0.03948 -0.0496 0.0078 1.0000
11.500 1.2895 0.04941 0.04199 -0.0485 0.0074 1.0000
11.750 1.2955 0.05178 0.04446 -0.0474 0.0073 1.0000
12.000 1.3021 0.05421 0.04702 -0.0463 0.0071 1.0000
12.250 1.3079 0.05677 0.04974 -0.0454 0.0069 1.0000
12.500 1.3132 0.05949 0.05261 -0.0446 0.0067 1.0000
12.750 1.3171 0.06243 0.05571 -0.0440 0.0066 1.0000
13.000 1.3192 0.06563 0.05911 -0.0435 0.0065 1.0000
13.250 1.3193 0.06910 0.06277 -0.0433 0.0064 1.0000
13.500 1.3171 0.07290 0.06677 -0.0434 0.0063 1.0000
13.750 1.3128 0.07701 0.07109 -0.0437 0.0063 1.0000
14.000 1.3066 0.08138 0.07567 -0.0445 0.0062 1.0000
14.250 1.2994 0.08596 0.08042 -0.0456 0.0061 1.0000
14.500 1.2913 0.09078 0.08542 -0.0471 0.0060 1.0000
14.750 1.2817 0.09608 0.09089 -0.0489 0.0059 1.0000
15.000 1.2712 0.10170 0.09669 -0.0512 0.0059 1.0000
15.250 1.2595 0.10777 0.10295 -0.0539 0.0058 1.0000
15.750 1.2333 0.12108 0.11663 -0.0609 0.0058 1.0000
16.000 1.2214 0.12793 0.12366 -0.0648 0.0058 1.0000
16.250 1.2089 0.13523 0.13114 -0.0694 0.0058 1.0000
16.500 1.1981 0.14236 0.13841 -0.0737 0.0058 1.0000
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