GOE 176 (ALBATROS 7020) AIRFOIL (goe176-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 176 (ALBATROS 7020) AIRFOIL (goe176-il) Reynolds number: 1,000,000 Max Cl/Cd: 113.1 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe176-il-1000000.txt Download as CSV file: xf-goe176-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.3289 0.09068 0.08918 -0.0301 1.0000 0.0124
-8.500 -0.3242 0.08803 0.08655 -0.0309 0.9997 0.0125
-8.250 -0.3604 0.02698 0.02461 -0.1058 0.9839 0.0093
-8.000 -0.3318 0.02238 0.01957 -0.1109 0.9758 0.0095
-7.750 -0.3047 0.02075 0.01776 -0.1122 0.9638 0.0098
-7.500 -0.2713 0.01913 0.01594 -0.1145 0.9468 0.0101
-7.250 -0.2178 0.01685 0.01332 -0.1214 0.9333 0.0106
-7.000 -0.1690 0.01498 0.01104 -0.1267 0.9054 0.0111
-6.750 -0.1399 0.01394 0.00966 -0.1273 0.8760 0.0114
-6.500 -0.1130 0.01323 0.00871 -0.1272 0.8551 0.0117
-6.250 -0.0860 0.01275 0.00805 -0.1270 0.8373 0.0120
-6.000 -0.0597 0.01132 0.00637 -0.1270 0.8214 0.0128
-5.750 -0.0324 0.01106 0.00603 -0.1269 0.8059 0.0135
-5.500 -0.0050 0.01081 0.00567 -0.1267 0.7906 0.0142
-5.250 0.0225 0.01046 0.00519 -0.1265 0.7740 0.0150
-5.000 0.0501 0.01020 0.00481 -0.1263 0.7571 0.0156
-4.750 0.0777 0.00958 0.00402 -0.1262 0.7400 0.0166
-4.500 0.1053 0.00933 0.00367 -0.1261 0.7214 0.0177
-4.250 0.1331 0.00917 0.00341 -0.1259 0.7022 0.0190
-4.000 0.1608 0.00910 0.00323 -0.1257 0.6819 0.0203
-3.500 0.2165 0.00867 0.00256 -0.1254 0.6411 0.0248
-3.250 0.2443 0.00864 0.00242 -0.1252 0.6211 0.0266
-3.000 0.2724 0.00841 0.00208 -0.1251 0.6041 0.0316
-2.750 0.3004 0.00836 0.00194 -0.1250 0.5886 0.0349
-2.500 0.3286 0.00820 0.00172 -0.1249 0.5746 0.0446
-2.250 0.3566 0.00773 0.00152 -0.1251 0.5600 0.1411
-2.000 0.3844 0.00771 0.00153 -0.1251 0.5441 0.1810
-1.750 0.4123 0.00778 0.00154 -0.1249 0.5292 0.1954
-1.500 0.4403 0.00783 0.00155 -0.1248 0.5153 0.2065
-1.250 0.4681 0.00790 0.00156 -0.1246 0.4993 0.2147
-1.000 0.4956 0.00802 0.00157 -0.1244 0.4729 0.2209
-0.750 0.5208 0.00841 0.00162 -0.1239 0.3981 0.2253
-0.500 0.5459 0.00880 0.00176 -0.1234 0.3444 0.2328
-0.250 0.5732 0.00895 0.00183 -0.1232 0.3314 0.2376
0.000 0.6010 0.00903 0.00187 -0.1231 0.3244 0.2432
0.250 0.6287 0.00912 0.00193 -0.1229 0.3180 0.2480
0.500 0.6567 0.00918 0.00198 -0.1229 0.3139 0.2527
0.750 0.6846 0.00924 0.00203 -0.1228 0.3101 0.2582
1.000 0.7122 0.00933 0.00211 -0.1226 0.3049 0.2654
1.250 0.7399 0.00941 0.00217 -0.1225 0.2998 0.2725
1.500 0.7679 0.00944 0.00223 -0.1225 0.2961 0.2807
1.750 0.7957 0.00951 0.00230 -0.1224 0.2923 0.2894
2.000 0.8232 0.00959 0.00239 -0.1223 0.2883 0.3007
2.250 0.8509 0.00965 0.00248 -0.1222 0.2850 0.3157
2.500 0.8789 0.00965 0.00255 -0.1222 0.2806 0.3382
2.750 0.9065 0.00967 0.00265 -0.1222 0.2753 0.3825
3.000 0.9341 0.00964 0.00281 -0.1222 0.2701 0.4745
3.250 0.9556 0.00870 0.00297 -0.1209 0.2661 1.0000
3.500 0.9829 0.00885 0.00305 -0.1207 0.2589 1.0000
3.750 1.0103 0.00898 0.00316 -0.1206 0.2512 1.0000
4.000 1.0371 0.00917 0.00327 -0.1204 0.2379 1.0000
4.250 1.0559 0.01022 0.00380 -0.1190 0.1489 1.0000
4.500 1.0790 0.01080 0.00420 -0.1182 0.1187 1.0000
4.750 1.1042 0.01114 0.00446 -0.1178 0.1065 1.0000
5.000 1.1294 0.01147 0.00471 -0.1173 0.0951 1.0000
5.250 1.1520 0.01208 0.00513 -0.1165 0.0618 1.0000
5.500 1.1770 0.01241 0.00543 -0.1160 0.0571 1.0000
5.750 1.2026 0.01267 0.00570 -0.1156 0.0548 1.0000
6.000 1.2280 0.01294 0.00597 -0.1152 0.0529 1.0000
6.250 1.2533 0.01320 0.00626 -0.1147 0.0522 1.0000
6.500 1.2784 0.01347 0.00657 -0.1143 0.0511 1.0000
6.750 1.3030 0.01378 0.00691 -0.1138 0.0498 1.0000
7.000 1.3271 0.01413 0.00728 -0.1132 0.0478 1.0000
7.250 1.3506 0.01453 0.00769 -0.1125 0.0455 1.0000
7.500 1.3735 0.01497 0.00818 -0.1117 0.0428 1.0000
7.750 1.3993 0.01509 0.00829 -0.1115 0.0417 1.0000
8.000 1.4236 0.01534 0.00851 -0.1110 0.0363 1.0000
8.250 1.4421 0.01615 0.00913 -0.1095 0.0153 1.0000
8.500 1.4625 0.01675 0.00978 -0.1083 0.0126 1.0000
8.750 1.4837 0.01724 0.01033 -0.1073 0.0117 1.0000
9.000 1.5039 0.01779 0.01094 -0.1061 0.0109 1.0000
9.250 1.5225 0.01844 0.01164 -0.1047 0.0102 1.0000
9.500 1.5378 0.01931 0.01260 -0.1027 0.0093 1.0000
9.750 1.5536 0.02007 0.01344 -0.1009 0.0088 1.0000
10.000 1.5701 0.02072 0.01415 -0.0992 0.0085 1.0000
10.250 1.5833 0.02143 0.01492 -0.0969 0.0082 1.0000
10.500 1.5939 0.02222 0.01578 -0.0943 0.0078 1.0000
10.750 1.6034 0.02310 0.01673 -0.0916 0.0075 1.0000
11.000 1.6113 0.02411 0.01781 -0.0889 0.0072 1.0000
11.250 1.6169 0.02530 0.01909 -0.0861 0.0070 1.0000
11.500 1.6177 0.02691 0.02080 -0.0830 0.0068 1.0000
11.750 1.6112 0.02925 0.02328 -0.0798 0.0066 1.0000
12.000 1.6013 0.03222 0.02639 -0.0771 0.0064 1.0000
12.250 1.6083 0.03389 0.02815 -0.0760 0.0063 1.0000
12.500 1.6141 0.03577 0.03011 -0.0750 0.0062 1.0000
12.750 1.6164 0.03811 0.03255 -0.0741 0.0060 1.0000
13.000 1.6175 0.04069 0.03522 -0.0735 0.0059 1.0000
13.250 1.6158 0.04373 0.03836 -0.0730 0.0057 1.0000
13.500 1.6128 0.04705 0.04178 -0.0728 0.0056 1.0000
13.750 1.6073 0.05079 0.04563 -0.0728 0.0055 1.0000
14.000 1.6008 0.05477 0.04973 -0.0730 0.0054 1.0000
14.250 1.5931 0.05904 0.05411 -0.0734 0.0053 1.0000
14.500 1.5837 0.06361 0.05879 -0.0740 0.0053 1.0000
14.750 1.5731 0.06846 0.06375 -0.0748 0.0052 1.0000
15.000 1.5629 0.07337 0.06877 -0.0757 0.0051 1.0000
15.250 1.5511 0.07857 0.07407 -0.0768 0.0051 1.0000
15.500 1.5400 0.08380 0.07941 -0.0780 0.0050 1.0000
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Polar data table (+)
Polar graphs
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