GOE 529 AIRFOIL (goe529-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 529 AIRFOIL (goe529-il) Reynolds number: 1,000,000 Max Cl/Cd: 127.3 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe529-il-1000000-n5.txt Download as CSV file: xf-goe529-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 529 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.250 -0.3126 0.12685 0.12517 -0.0323 1.0000 0.0050
-12.000 -0.3085 0.12363 0.12196 -0.0332 1.0000 0.0051
-10.000 -0.4883 0.01896 0.01534 -0.1175 0.8323 0.0093
-9.750 -0.4682 0.01732 0.01342 -0.1171 0.8189 0.0096
-9.500 -0.4463 0.01610 0.01200 -0.1166 0.8063 0.0104
-9.250 -0.4230 0.01524 0.01095 -0.1162 0.7932 0.0111
-9.000 -0.3991 0.01454 0.01009 -0.1158 0.7792 0.0118
-8.750 -0.3747 0.01394 0.00930 -0.1153 0.7640 0.0125
-8.500 -0.3491 0.01365 0.00894 -0.1149 0.7474 0.0136
-8.250 -0.3230 0.01348 0.00869 -0.1145 0.7303 0.0146
-8.000 -0.2973 0.01323 0.00830 -0.1141 0.7124 0.0156
-7.750 -0.2719 0.01288 0.00779 -0.1137 0.6951 0.0162
-7.250 -0.2188 0.01274 0.00750 -0.1131 0.6661 0.0176
-7.000 -0.1918 0.01274 0.00744 -0.1128 0.6546 0.0182
-6.750 -0.1648 0.01270 0.00733 -0.1126 0.6448 0.0190
-6.500 -0.1379 0.01261 0.00716 -0.1123 0.6357 0.0198
-6.250 -0.1110 0.01239 0.00684 -0.1121 0.6288 0.0204
-6.000 -0.0840 0.01222 0.00658 -0.1119 0.6227 0.0208
-5.500 -0.0305 0.01154 0.00570 -0.1114 0.6144 0.0218
-5.250 -0.0036 0.01122 0.00532 -0.1112 0.6104 0.0225
-5.000 0.0237 0.01107 0.00513 -0.1111 0.6066 0.0231
-4.750 0.0509 0.01091 0.00491 -0.1109 0.6030 0.0237
-4.500 0.0784 0.01072 0.00468 -0.1108 0.5999 0.0243
-4.250 0.1058 0.01045 0.00435 -0.1106 0.5963 0.0248
-4.000 0.1331 0.01021 0.00403 -0.1104 0.5929 0.0254
-3.750 0.1604 0.01003 0.00380 -0.1102 0.5896 0.0260
-3.500 0.1877 0.00982 0.00352 -0.1100 0.5864 0.0264
-3.250 0.2152 0.00958 0.00323 -0.1099 0.5832 0.0267
-3.000 0.2427 0.00940 0.00300 -0.1097 0.5795 0.0270
-2.750 0.2700 0.00922 0.00278 -0.1095 0.5759 0.0272
-2.500 0.2973 0.00908 0.00258 -0.1093 0.5725 0.0274
-2.250 0.3250 0.00892 0.00240 -0.1092 0.5692 0.0276
-2.000 0.3526 0.00879 0.00224 -0.1091 0.5651 0.0278
-1.750 0.3799 0.00864 0.00205 -0.1089 0.5606 0.0280
-1.500 0.4070 0.00847 0.00182 -0.1086 0.5567 0.0292
-1.250 0.4347 0.00834 0.00168 -0.1085 0.5527 0.0304
-1.000 0.4622 0.00826 0.00157 -0.1084 0.5465 0.0313
-0.750 0.4895 0.00821 0.00149 -0.1082 0.5392 0.0325
-0.500 0.5169 0.00817 0.00143 -0.1080 0.5305 0.0336
-0.250 0.5441 0.00815 0.00137 -0.1078 0.5203 0.0346
0.000 0.5711 0.00816 0.00133 -0.1076 0.5083 0.0359
0.500 0.6240 0.00825 0.00131 -0.1070 0.4737 0.0470
0.750 0.6501 0.00829 0.00135 -0.1067 0.4581 0.0701
1.000 0.6764 0.00836 0.00140 -0.1064 0.4446 0.0816
1.250 0.7027 0.00844 0.00145 -0.1061 0.4319 0.0939
1.500 0.7289 0.00849 0.00152 -0.1058 0.4208 0.1203
1.750 0.7555 0.00854 0.00159 -0.1056 0.4125 0.1433
2.000 0.7820 0.00858 0.00167 -0.1054 0.4060 0.1671
2.250 0.8086 0.00860 0.00174 -0.1052 0.3992 0.2030
2.500 0.8344 0.00855 0.00186 -0.1049 0.3928 0.2908
3.000 0.8989 0.00741 0.00221 -0.1074 0.3793 1.0000
3.250 0.9250 0.00752 0.00229 -0.1071 0.3736 1.0000
3.500 0.9508 0.00765 0.00239 -0.1067 0.3669 1.0000
3.750 0.9765 0.00779 0.00249 -0.1063 0.3606 1.0000
4.000 1.0023 0.00792 0.00260 -0.1060 0.3533 1.0000
4.250 1.0277 0.00808 0.00272 -0.1056 0.3459 1.0000
4.500 1.0528 0.00827 0.00286 -0.1051 0.3353 1.0000
4.750 1.0775 0.00848 0.00301 -0.1046 0.3222 1.0000
5.000 1.1019 0.00871 0.00318 -0.1040 0.3085 1.0000
5.250 1.1264 0.00893 0.00335 -0.1035 0.2967 1.0000
5.500 1.1487 0.00931 0.00361 -0.1026 0.2739 1.0000
5.750 1.1699 0.00975 0.00391 -0.1016 0.2476 1.0000
6.000 1.1918 0.01015 0.00420 -0.1007 0.2276 1.0000
6.250 1.2118 0.01066 0.00455 -0.0995 0.2021 1.0000
6.500 1.2309 0.01121 0.00496 -0.0981 0.1719 1.0000
6.750 1.2432 0.01222 0.00565 -0.0957 0.1188 1.0000
7.000 1.2640 0.01261 0.00600 -0.0947 0.1101 1.0000
7.250 1.2857 0.01293 0.00631 -0.0937 0.1029 1.0000
7.500 1.3052 0.01337 0.00671 -0.0925 0.0923 1.0000
7.750 1.3172 0.01423 0.00736 -0.0900 0.0561 1.0000
8.000 1.3329 0.01483 0.00790 -0.0881 0.0413 1.0000
8.250 1.3396 0.01575 0.00868 -0.0847 0.0166 1.0000
8.500 1.3539 0.01620 0.00916 -0.0825 0.0132 1.0000
8.750 1.3690 0.01664 0.00963 -0.0805 0.0119 1.0000
9.000 1.3828 0.01715 0.01017 -0.0784 0.0107 1.0000
9.250 1.3958 0.01772 0.01077 -0.0762 0.0096 1.0000
9.500 1.4099 0.01824 0.01134 -0.0743 0.0091 1.0000
9.750 1.4233 0.01883 0.01196 -0.0724 0.0084 1.0000
10.000 1.4356 0.01949 0.01266 -0.0704 0.0078 1.0000
10.250 1.4467 0.02026 0.01347 -0.0685 0.0073 1.0000
10.500 1.4558 0.02119 0.01445 -0.0663 0.0067 1.0000
10.750 1.4670 0.02203 0.01534 -0.0646 0.0065 1.0000
11.000 1.4776 0.02296 0.01632 -0.0629 0.0062 1.0000
11.250 1.4869 0.02402 0.01744 -0.0613 0.0060 1.0000
11.500 1.4959 0.02517 0.01864 -0.0597 0.0058 1.0000
11.750 1.5039 0.02644 0.01996 -0.0582 0.0055 1.0000
12.000 1.5108 0.02787 0.02146 -0.0568 0.0052 1.0000
12.250 1.5161 0.02949 0.02313 -0.0554 0.0050 1.0000
12.500 1.5200 0.03132 0.02504 -0.0542 0.0047 1.0000
12.750 1.5255 0.03308 0.02687 -0.0531 0.0047 1.0000
13.000 1.5316 0.03485 0.02871 -0.0523 0.0045 1.0000
13.250 1.5353 0.03692 0.03085 -0.0515 0.0044 1.0000
13.500 1.5385 0.03911 0.03312 -0.0508 0.0042 1.0000
13.750 1.5417 0.04135 0.03544 -0.0502 0.0041 1.0000
14.000 1.5421 0.04396 0.03813 -0.0497 0.0040 1.0000
14.250 1.5430 0.04657 0.04083 -0.0493 0.0039 1.0000
14.500 1.5447 0.04916 0.04349 -0.0490 0.0038 1.0000
14.750 1.5436 0.05211 0.04653 -0.0488 0.0037 1.0000
15.000 1.5422 0.05519 0.04968 -0.0487 0.0036 1.0000
15.250 1.5396 0.05848 0.05307 -0.0488 0.0036 1.0000
15.500 1.5379 0.06175 0.05640 -0.0490 0.0035 1.0000
15.750 1.5344 0.06532 0.06006 -0.0493 0.0034 1.0000
16.000 1.5253 0.06979 0.06464 -0.0499 0.0033 1.0000
16.250 1.5199 0.07387 0.06881 -0.0506 0.0032 1.0000
16.500 1.5120 0.07842 0.07346 -0.0515 0.0032 1.0000
16.750 1.5060 0.08281 0.07795 -0.0525 0.0031 1.0000
17.000 1.5025 0.08691 0.08214 -0.0535 0.0031 1.0000
17.250 1.4984 0.09115 0.08648 -0.0547 0.0031 1.0000
17.500 1.4891 0.09629 0.09173 -0.0563 0.0031 1.0000
17.750 1.4847 0.10071 0.09625 -0.0577 0.0030 1.0000
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Polar data table (+)
Polar graphs
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