GOE 176 (ALBATROS 7020) AIRFOIL (goe176-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 176 (ALBATROS 7020) AIRFOIL (goe176-il) Reynolds number: 1,000,000 Max Cl/Cd: 93.54 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe176-il-1000000-n5.txt Download as CSV file: xf-goe176-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.500 -0.3471 0.14354 0.14182 -0.0199 1.0000 0.0050
-12.250 -0.3422 0.14018 0.13847 -0.0208 1.0000 0.0048
-12.000 -0.3375 0.13678 0.13508 -0.0216 1.0000 0.0047
-11.750 -0.3330 0.13340 0.13171 -0.0225 1.0000 0.0046
-11.500 -0.3282 0.13014 0.12847 -0.0233 1.0000 0.0048
-9.500 -0.4102 0.02366 0.02096 -0.1248 0.9182 0.0043
-9.250 -0.3782 0.02085 0.01766 -0.1290 0.8750 0.0044
-9.000 -0.3530 0.01917 0.01566 -0.1303 0.8521 0.0045
-8.500 -0.3015 0.01661 0.01259 -0.1317 0.8206 0.0048
-8.250 -0.2752 0.01565 0.01139 -0.1320 0.8063 0.0049
-8.000 -0.2486 0.01484 0.01037 -0.1322 0.7915 0.0051
-7.750 -0.2219 0.01420 0.00955 -0.1323 0.7754 0.0053
-7.500 -0.1950 0.01359 0.00875 -0.1324 0.7590 0.0055
-7.250 -0.1679 0.01309 0.00807 -0.1324 0.7419 0.0056
-7.000 -0.1407 0.01229 0.00705 -0.1325 0.7245 0.0059
-6.750 -0.1133 0.01177 0.00637 -0.1326 0.7062 0.0061
-6.500 -0.0857 0.01143 0.00589 -0.1326 0.6886 0.0064
-6.250 -0.0581 0.01115 0.00547 -0.1325 0.6704 0.0067
-6.000 -0.0304 0.01086 0.00504 -0.1325 0.6518 0.0070
-5.750 -0.0025 0.01060 0.00465 -0.1324 0.6329 0.0074
-5.500 0.0254 0.01037 0.00428 -0.1324 0.6142 0.0078
-5.250 0.0533 0.01019 0.00395 -0.1323 0.5959 0.0081
-5.000 0.0813 0.00991 0.00354 -0.1323 0.5778 0.0090
-4.750 0.1091 0.00979 0.00332 -0.1323 0.5605 0.0099
-4.500 0.1373 0.00967 0.00310 -0.1322 0.5468 0.0108
-4.250 0.1657 0.00954 0.00287 -0.1322 0.5363 0.0115
-4.000 0.1941 0.00935 0.00261 -0.1322 0.5269 0.0132
-3.750 0.2225 0.00923 0.00245 -0.1322 0.5178 0.0151
-3.500 0.2510 0.00913 0.00230 -0.1322 0.5097 0.0175
-3.250 0.2793 0.00904 0.00216 -0.1322 0.5004 0.0216
-3.000 0.3076 0.00900 0.00206 -0.1321 0.4894 0.0239
-2.750 0.3359 0.00891 0.00193 -0.1321 0.4777 0.0295
-2.500 0.3641 0.00889 0.00183 -0.1321 0.4631 0.0331
-2.250 0.3917 0.00891 0.00174 -0.1319 0.4358 0.0415
-2.000 0.4158 0.00917 0.00176 -0.1314 0.3427 0.0943
-1.500 0.4710 0.00914 0.00178 -0.1314 0.3152 0.1670
-1.250 0.4989 0.00918 0.00181 -0.1313 0.3088 0.1826
-1.000 0.5269 0.00925 0.00183 -0.1312 0.3018 0.1902
-0.750 0.5549 0.00930 0.00186 -0.1311 0.2964 0.1968
-0.500 0.5829 0.00937 0.00188 -0.1310 0.2924 0.2012
-0.250 0.6108 0.00942 0.00193 -0.1310 0.2885 0.2114
0.000 0.6390 0.00946 0.00196 -0.1309 0.2862 0.2161
0.250 0.6671 0.00950 0.00199 -0.1309 0.2833 0.2195
0.500 0.6950 0.00956 0.00203 -0.1308 0.2792 0.2238
0.750 0.7226 0.00965 0.00209 -0.1307 0.2740 0.2282
1.000 0.7505 0.00971 0.00213 -0.1306 0.2700 0.2328
1.250 0.7781 0.00979 0.00219 -0.1305 0.2621 0.2381
1.500 0.8057 0.00988 0.00226 -0.1304 0.2567 0.2438
1.750 0.8333 0.00995 0.00233 -0.1303 0.2508 0.2498
2.000 0.8606 0.01007 0.00242 -0.1302 0.2427 0.2562
2.250 0.8875 0.01022 0.00252 -0.1300 0.2296 0.2620
2.500 0.9067 0.01123 0.00306 -0.1286 0.1324 0.2690
2.750 0.9324 0.01151 0.00328 -0.1283 0.1160 0.2775
3.000 0.9585 0.01173 0.00348 -0.1280 0.1067 0.2872
3.250 0.9850 0.01190 0.00365 -0.1277 0.0999 0.2978
3.500 1.0097 0.01226 0.00391 -0.1272 0.0742 0.3107
3.750 1.0346 0.01259 0.00420 -0.1267 0.0583 0.3283
4.000 1.0609 0.01275 0.00442 -0.1265 0.0535 0.3567
4.250 1.0874 0.01285 0.00465 -0.1263 0.0520 0.4120
4.500 1.1138 0.01295 0.00490 -0.1261 0.0511 0.4767
4.750 1.1407 0.01270 0.00522 -0.1263 0.0503 0.7510
5.250 1.1861 0.01269 0.00566 -0.1241 0.0490 1.0000
5.500 1.2114 0.01295 0.00592 -0.1237 0.0479 1.0000
5.750 1.2363 0.01326 0.00623 -0.1232 0.0457 1.0000
6.000 1.2610 0.01357 0.00655 -0.1227 0.0440 1.0000
6.250 1.2860 0.01383 0.00682 -0.1223 0.0431 1.0000
6.500 1.3111 0.01405 0.00705 -0.1219 0.0422 1.0000
6.750 1.3359 0.01431 0.00731 -0.1214 0.0404 1.0000
7.000 1.3598 0.01464 0.00762 -0.1209 0.0372 1.0000
7.250 1.3838 0.01495 0.00793 -0.1203 0.0337 1.0000
7.500 1.4037 0.01562 0.00847 -0.1191 0.0132 1.0000
7.750 1.4254 0.01611 0.00900 -0.1181 0.0100 1.0000
8.000 1.4476 0.01652 0.00945 -0.1172 0.0086 1.0000
8.250 1.4690 0.01698 0.00993 -0.1163 0.0075 1.0000
8.500 1.4895 0.01749 0.01047 -0.1152 0.0065 1.0000
8.750 1.5104 0.01794 0.01097 -0.1141 0.0060 1.0000
9.000 1.5303 0.01843 0.01150 -0.1129 0.0054 1.0000
9.250 1.5488 0.01899 0.01208 -0.1116 0.0049 1.0000
9.500 1.5662 0.01960 0.01274 -0.1100 0.0045 1.0000
9.750 1.5832 0.02017 0.01336 -0.1084 0.0042 1.0000
10.000 1.5974 0.02077 0.01401 -0.1062 0.0040 1.0000
10.250 1.6104 0.02143 0.01472 -0.1040 0.0038 1.0000
10.500 1.6226 0.02214 0.01550 -0.1016 0.0036 1.0000
10.750 1.6334 0.02295 0.01636 -0.0992 0.0034 1.0000
11.000 1.6420 0.02393 0.01741 -0.0967 0.0032 1.0000
11.250 1.6487 0.02508 0.01864 -0.0940 0.0030 1.0000
11.500 1.6574 0.02615 0.01979 -0.0918 0.0029 1.0000
11.750 1.6652 0.02735 0.02107 -0.0898 0.0028 1.0000
12.000 1.6720 0.02872 0.02252 -0.0879 0.0027 1.0000
12.250 1.6785 0.03021 0.02409 -0.0862 0.0026 1.0000
12.500 1.6838 0.03190 0.02585 -0.0847 0.0025 1.0000
12.750 1.6880 0.03379 0.02783 -0.0833 0.0024 1.0000
13.000 1.6918 0.03581 0.02995 -0.0821 0.0023 1.0000
13.250 1.6932 0.03817 0.03241 -0.0811 0.0023 1.0000
13.500 1.6937 0.04075 0.03508 -0.0802 0.0022 1.0000
13.750 1.6923 0.04364 0.03807 -0.0796 0.0021 1.0000
14.000 1.6892 0.04684 0.04137 -0.0791 0.0021 1.0000
14.250 1.6830 0.05055 0.04518 -0.0789 0.0020 1.0000
14.500 1.6754 0.05457 0.04933 -0.0789 0.0020 1.0000
14.750 1.6637 0.05927 0.05415 -0.0792 0.0019 1.0000
15.000 1.6494 0.06450 0.05952 -0.0798 0.0019 1.0000
15.250 1.6377 0.06952 0.06466 -0.0806 0.0019 1.0000
15.500 1.6265 0.07452 0.06977 -0.0814 0.0019 1.0000
15.750 1.6134 0.07994 0.07532 -0.0825 0.0019 1.0000
16.000 1.6004 0.08546 0.08095 -0.0837 0.0018 1.0000
16.250 1.5849 0.09145 0.08707 -0.0852 0.0018 1.0000
16.500 1.5706 0.09742 0.09316 -0.0868 0.0018 1.0000
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