GOE 176 (ALBATROS 7020) AIRFOIL (goe176-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 176 (ALBATROS 7020) AIRFOIL (goe176-il) Reynolds number: 100,000 Max Cl/Cd: 57.5 at α=4° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe176-il-100000-n5.txt Download as CSV file: xf-goe176-il-100000-n5.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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.750 -0.2916 0.09361 0.08928 -0.0333 1.0000 0.0328
-7.500 -0.2969 0.09150 0.08727 -0.0312 1.0000 0.0324
-7.250 -0.3058 0.08971 0.08560 -0.0290 1.0000 0.0320
-7.000 -0.2870 0.08494 0.08084 -0.0346 0.9930 0.0314
-6.750 -0.2636 0.07968 0.07558 -0.0417 0.9826 0.0305
-6.500 -0.2402 0.07410 0.06999 -0.0494 0.9701 0.0293
-6.250 -0.2147 0.06773 0.06360 -0.0586 0.9564 0.0281
-6.000 -0.1843 0.05970 0.05550 -0.0703 0.9429 0.0270
-5.750 -0.1255 0.03751 0.03230 -0.1018 0.9312 0.0247
-5.500 -0.0833 0.03200 0.02613 -0.1094 0.9228 0.0253
-5.250 -0.0428 0.02905 0.02279 -0.1140 0.9140 0.0276
-5.000 -0.0030 0.02615 0.01928 -0.1177 0.9041 0.0297
-4.750 0.0392 0.02361 0.01616 -0.1209 0.8959 0.0312
-4.500 0.0766 0.02201 0.01412 -0.1228 0.8843 0.0332
-4.250 0.1123 0.02028 0.01228 -0.1247 0.8725 0.0375
-4.000 0.1482 0.01915 0.01090 -0.1262 0.8607 0.0413
-3.750 0.1836 0.01815 0.00967 -0.1275 0.8488 0.0476
-3.500 0.2176 0.01730 0.00861 -0.1286 0.8354 0.0559
-3.250 0.2498 0.01644 0.00770 -0.1294 0.8209 0.0746
-3.000 0.2806 0.01582 0.00742 -0.1301 0.8066 0.1592
-2.750 0.3105 0.01601 0.00742 -0.1300 0.7928 0.2046
-2.500 0.3398 0.01622 0.00741 -0.1300 0.7791 0.2312
-2.250 0.3682 0.01637 0.00744 -0.1298 0.7646 0.2514
-2.000 0.3965 0.01639 0.00731 -0.1296 0.7497 0.2669
-1.750 0.4248 0.01631 0.00703 -0.1294 0.7355 0.2770
-1.500 0.4525 0.01617 0.00680 -0.1291 0.7212 0.2843
-1.000 0.5074 0.01600 0.00638 -0.1284 0.6921 0.3013
-0.750 0.5347 0.01594 0.00620 -0.1281 0.6774 0.3106
-0.500 0.5617 0.01588 0.00606 -0.1277 0.6638 0.3196
-0.250 0.5887 0.01584 0.00594 -0.1273 0.6508 0.3284
0.000 0.6154 0.01582 0.00583 -0.1268 0.6374 0.3382
0.250 0.6421 0.01580 0.00577 -0.1264 0.6235 0.3475
0.500 0.6687 0.01581 0.00574 -0.1259 0.6091 0.3592
0.750 0.6952 0.01584 0.00573 -0.1255 0.5945 0.3732
1.000 0.7215 0.01587 0.00574 -0.1250 0.5796 0.3901
1.250 0.7476 0.01592 0.00579 -0.1245 0.5645 0.4136
1.500 0.7736 0.01594 0.00587 -0.1240 0.5492 0.4519
1.750 0.7989 0.01581 0.00596 -0.1235 0.5339 0.5336
2.250 0.8444 0.01544 0.00608 -0.1208 0.5025 1.0000
2.500 0.8699 0.01572 0.00624 -0.1202 0.4859 1.0000
2.750 0.8953 0.01601 0.00641 -0.1197 0.4694 1.0000
3.000 0.9206 0.01631 0.00661 -0.1192 0.4533 1.0000
3.250 0.9457 0.01663 0.00684 -0.1186 0.4377 1.0000
3.500 0.9704 0.01696 0.00706 -0.1180 0.4222 1.0000
3.750 0.9946 0.01732 0.00730 -0.1173 0.4071 1.0000
4.000 1.0183 0.01771 0.00757 -0.1166 0.3924 1.0000
4.250 1.0415 0.01814 0.00786 -0.1158 0.3786 1.0000
4.500 1.0647 0.01861 0.00820 -0.1150 0.3662 1.0000
4.750 1.0883 0.01905 0.00862 -0.1144 0.3556 1.0000
5.000 1.1120 0.01951 0.00902 -0.1137 0.3482 1.0000
5.250 1.1364 0.01992 0.00947 -0.1132 0.3422 1.0000
5.500 1.1604 0.02038 0.00995 -0.1126 0.3371 1.0000
5.750 1.1846 0.02083 0.01043 -0.1120 0.3323 1.0000
6.000 1.2086 0.02125 0.01094 -0.1114 0.3266 1.0000
6.250 1.2318 0.02176 0.01145 -0.1108 0.3210 1.0000
6.500 1.2554 0.02221 0.01202 -0.1101 0.3155 1.0000
6.750 1.2785 0.02266 0.01258 -0.1094 0.3097 1.0000
7.000 1.3012 0.02319 0.01314 -0.1087 0.3044 1.0000
7.250 1.3239 0.02362 0.01376 -0.1079 0.2986 1.0000
7.500 1.3460 0.02410 0.01440 -0.1071 0.2927 1.0000
7.750 1.3680 0.02463 0.01501 -0.1062 0.2882 1.0000
8.000 1.3897 0.02508 0.01571 -0.1053 0.2821 1.0000
8.250 1.4083 0.02556 0.01631 -0.1040 0.2715 1.0000
8.500 1.4251 0.02597 0.01691 -0.1024 0.2524 1.0000
8.750 1.4411 0.02647 0.01751 -0.1008 0.2224 1.0000
9.250 1.4522 0.02896 0.01949 -0.0951 0.1495 1.0000
9.500 1.4572 0.03036 0.02085 -0.0922 0.1325 1.0000
9.750 1.4632 0.03176 0.02228 -0.0897 0.1179 1.0000
10.000 1.4695 0.03318 0.02375 -0.0872 0.0966 1.0000
10.500 1.4575 0.03809 0.02845 -0.0813 0.0585 1.0000
10.750 1.4507 0.04086 0.03132 -0.0790 0.0535 1.0000
11.000 1.4513 0.04315 0.03382 -0.0775 0.0483 1.0000
11.500 1.4512 0.04825 0.03936 -0.0753 0.0353 1.0000
11.750 1.4444 0.05175 0.04295 -0.0746 0.0239 1.0000
12.000 1.4327 0.05602 0.04725 -0.0744 0.0221 1.0000
12.250 1.4216 0.06051 0.05184 -0.0745 0.0209 1.0000
12.500 1.4102 0.06527 0.05675 -0.0751 0.0201 1.0000
13.000 1.3839 0.07588 0.06774 -0.0771 0.0193 1.0000
13.250 1.3698 0.08161 0.07367 -0.0785 0.0190 1.0000
13.500 1.3553 0.08761 0.07985 -0.0802 0.0188 1.0000
13.750 1.3414 0.09368 0.08610 -0.0820 0.0186 1.0000
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Polar data table (+)
Polar graphs
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