GOE 176 (ALBATROS 7020) AIRFOIL (goe176-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 176 (ALBATROS 7020) AIRFOIL (goe176-il) Reynolds number: 500,000 Max Cl/Cd: 99.17 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe176-il-500000.txt Download as CSV file: xf-goe176-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 176 (ALBATROS 7020) 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.3149 0.08941 0.08735 -0.0328 1.0000 0.0205
-8.000 -0.3266 0.08554 0.08355 -0.0313 1.0000 0.0210
-7.750 -0.3307 0.08364 0.08170 -0.0296 0.9998 0.0212
-7.500 -0.3065 0.08002 0.07807 -0.0348 0.9961 0.0216
-7.250 -0.2799 0.07581 0.07385 -0.0415 0.9913 0.0223
-7.000 -0.2523 0.07074 0.06878 -0.0500 0.9851 0.0233
-6.750 -0.2257 0.06440 0.06243 -0.0602 0.9730 0.0248
-6.500 -0.1753 0.04279 0.04040 -0.0950 0.9455 0.0266
-6.250 -0.1372 0.02418 0.02063 -0.1134 0.9340 0.0192
-6.000 -0.0912 0.01954 0.01533 -0.1196 0.9237 0.0187
-5.750 -0.0445 0.01750 0.01283 -0.1240 0.9094 0.0197
-5.500 -0.0057 0.01587 0.01077 -0.1265 0.8900 0.0202
-5.250 0.0249 0.01452 0.00907 -0.1271 0.8699 0.0207
-5.000 0.0525 0.01300 0.00737 -0.1273 0.8511 0.0218
-4.750 0.0800 0.01242 0.00666 -0.1271 0.8334 0.0229
-4.500 0.1075 0.01199 0.00610 -0.1269 0.8173 0.0244
-4.250 0.1352 0.01174 0.00571 -0.1266 0.8016 0.0262
-4.000 0.1627 0.01089 0.00471 -0.1264 0.7863 0.0281
-3.750 0.1903 0.01045 0.00417 -0.1262 0.7705 0.0305
-3.500 0.2179 0.01019 0.00379 -0.1260 0.7538 0.0335
-3.250 0.2455 0.00979 0.00324 -0.1257 0.7355 0.0379
-3.000 0.2732 0.00953 0.00286 -0.1255 0.7169 0.0433
-2.750 0.3010 0.00925 0.00248 -0.1253 0.6991 0.0553
-2.500 0.3284 0.00872 0.00232 -0.1254 0.6821 0.1750
-2.250 0.3558 0.00881 0.00236 -0.1251 0.6652 0.2017
-2.000 0.3832 0.00891 0.00235 -0.1247 0.6478 0.2148
-1.750 0.4106 0.00904 0.00234 -0.1244 0.6318 0.2251
-1.500 0.4380 0.00909 0.00234 -0.1242 0.6162 0.2347
-1.250 0.4654 0.00917 0.00232 -0.1239 0.6006 0.2423
-1.000 0.4928 0.00923 0.00232 -0.1237 0.5859 0.2497
-0.750 0.5202 0.00932 0.00231 -0.1234 0.5707 0.2575
-0.500 0.5474 0.00937 0.00232 -0.1231 0.5545 0.2641
-0.250 0.5746 0.00946 0.00230 -0.1229 0.5354 0.2692
0.000 0.6012 0.00956 0.00229 -0.1225 0.5117 0.2746
0.250 0.6279 0.00968 0.00231 -0.1222 0.4834 0.2812
0.500 0.6540 0.00986 0.00233 -0.1218 0.4421 0.2885
0.750 0.6785 0.01021 0.00242 -0.1212 0.3835 0.2963
1.000 0.7042 0.01048 0.00253 -0.1207 0.3599 0.3036
1.250 0.7307 0.01065 0.00265 -0.1205 0.3486 0.3125
1.500 0.7577 0.01076 0.00276 -0.1203 0.3408 0.3238
1.750 0.7844 0.01090 0.00289 -0.1200 0.3338 0.3389
2.250 0.8388 0.01097 0.00319 -0.1198 0.3237 0.4171
2.500 0.8652 0.01063 0.00343 -0.1199 0.3184 0.6529
2.750 0.8853 0.01014 0.00352 -0.1178 0.3141 1.0000
3.000 0.9125 0.01030 0.00364 -0.1176 0.3081 1.0000
3.250 0.9389 0.01053 0.00380 -0.1173 0.3032 1.0000
3.500 0.9659 0.01069 0.00395 -0.1171 0.2993 1.0000
3.750 0.9932 0.01082 0.00407 -0.1170 0.2952 1.0000
4.000 1.0200 0.01099 0.00423 -0.1167 0.2905 1.0000
4.250 1.0461 0.01123 0.00442 -0.1164 0.2857 1.0000
4.500 1.0736 0.01132 0.00454 -0.1163 0.2807 1.0000
4.750 1.1002 0.01148 0.00469 -0.1161 0.2747 1.0000
5.000 1.1266 0.01166 0.00486 -0.1158 0.2691 1.0000
5.250 1.1535 0.01179 0.00501 -0.1156 0.2625 1.0000
5.500 1.1796 0.01199 0.00519 -0.1153 0.2553 1.0000
5.750 1.2059 0.01216 0.00535 -0.1150 0.2443 1.0000
6.000 1.2310 0.01245 0.00554 -0.1146 0.2204 1.0000
6.250 1.2468 0.01368 0.00626 -0.1129 0.1433 1.0000
6.500 1.2692 0.01422 0.00674 -0.1121 0.1278 1.0000
6.750 1.2915 0.01477 0.00721 -0.1112 0.1132 1.0000
7.000 1.3138 0.01529 0.00767 -0.1104 0.0986 1.0000
7.250 1.3326 0.01613 0.00831 -0.1091 0.0663 1.0000
7.500 1.3538 0.01671 0.00890 -0.1081 0.0605 1.0000
7.750 1.3748 0.01729 0.00950 -0.1070 0.0568 1.0000
8.000 1.3959 0.01783 0.01008 -0.1060 0.0530 1.0000
8.250 1.4181 0.01823 0.01056 -0.1051 0.0512 1.0000
8.500 1.4387 0.01875 0.01116 -0.1041 0.0476 1.0000
8.750 1.4571 0.01945 0.01188 -0.1027 0.0426 1.0000
9.000 1.4800 0.01971 0.01212 -0.1020 0.0343 1.0000
9.250 1.4937 0.02070 0.01294 -0.0999 0.0179 1.0000
9.500 1.5096 0.02147 0.01378 -0.0981 0.0158 1.0000
9.750 1.5231 0.02230 0.01473 -0.0959 0.0149 1.0000
10.000 1.5326 0.02323 0.01578 -0.0931 0.0141 1.0000
10.250 1.5395 0.02436 0.01702 -0.0901 0.0133 1.0000
10.500 1.5427 0.02576 0.01855 -0.0867 0.0126 1.0000
10.750 1.5451 0.02729 0.02020 -0.0837 0.0121 1.0000
11.000 1.5509 0.02865 0.02168 -0.0813 0.0118 1.0000
11.250 1.5539 0.03034 0.02348 -0.0790 0.0115 1.0000
11.500 1.5548 0.03236 0.02562 -0.0770 0.0112 1.0000
11.750 1.5541 0.03471 0.02809 -0.0753 0.0110 1.0000
12.000 1.5521 0.03736 0.03089 -0.0740 0.0107 1.0000
12.250 1.5486 0.04038 0.03403 -0.0730 0.0105 1.0000
12.500 1.5435 0.04374 0.03751 -0.0723 0.0103 1.0000
12.750 1.5369 0.04747 0.04137 -0.0720 0.0102 1.0000
13.000 1.5288 0.05151 0.04553 -0.0720 0.0100 1.0000
13.250 1.5195 0.05587 0.05001 -0.0722 0.0099 1.0000
13.500 1.5097 0.06037 0.05462 -0.0726 0.0098 1.0000
13.750 1.4988 0.06508 0.05944 -0.0731 0.0097 1.0000
14.000 1.4881 0.06985 0.06432 -0.0737 0.0096 1.0000
14.250 1.4772 0.07467 0.06924 -0.0743 0.0095 1.0000
14.500 1.4671 0.07942 0.07407 -0.0749 0.0094 1.0000
14.750 1.4581 0.08393 0.07866 -0.0753 0.0093 1.0000
15.000 1.4498 0.08796 0.08274 -0.0750 0.0091 1.0000
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Polar data table (+)
Polar graphs
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