GOE 803 (HACKLINGER) AIRFOIL (goe803h-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 803 (HACKLINGER) AIRFOIL (goe803h-il) Reynolds number: 1,000,000 Max Cl/Cd: 122.21 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe803h-il-1000000-n5.txt Download as CSV file: xf-goe803h-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 803 (HACKLINGER) 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
------ -------- --------- --------- -------- -------- --------
-7.750 -0.1676 0.09050 0.08848 -0.0464 0.8803 0.0115
-7.500 -0.1576 0.08792 0.08583 -0.0478 0.8644 0.0116
-7.250 -0.1472 0.08532 0.08318 -0.0493 0.8496 0.0116
-7.000 -0.1364 0.08271 0.08053 -0.0511 0.8349 0.0115
-6.750 -0.1216 0.07994 0.07770 -0.0538 0.8197 0.0117
-6.500 -0.1054 0.07711 0.07481 -0.0569 0.8039 0.0120
-6.250 -0.0877 0.07409 0.07173 -0.0605 0.7886 0.0119
-6.000 -0.0682 0.07098 0.06855 -0.0644 0.7738 0.0118
-5.750 -0.0467 0.06780 0.06530 -0.0688 0.7595 0.0120
-5.500 -0.0229 0.06448 0.06189 -0.0738 0.7459 0.0123
-5.000 0.0348 0.05685 0.05412 -0.0864 0.7229 0.0128
-4.750 0.0673 0.05308 0.05028 -0.0932 0.7144 0.0131
-4.500 0.0943 0.05121 0.04837 -0.0964 0.7061 0.0134
-4.250 0.1276 0.04815 0.04524 -0.1021 0.6982 0.0135
-4.000 0.1648 0.04465 0.04166 -0.1087 0.6895 0.0135
-3.750 0.2007 0.04184 0.03877 -0.1142 0.6809 0.0138
-3.500 0.2386 0.03892 0.03574 -0.1198 0.6702 0.0142
-2.500 0.4681 0.01044 0.00500 -0.1603 0.6228 0.0184
-2.250 0.4975 0.00991 0.00427 -0.1606 0.6086 0.0189
-2.000 0.5267 0.00952 0.00371 -0.1608 0.5972 0.0192
-1.750 0.5556 0.00927 0.00332 -0.1609 0.5862 0.0194
-1.500 0.5848 0.00889 0.00281 -0.1611 0.5742 0.0199
-1.250 0.6134 0.00873 0.00256 -0.1611 0.5619 0.0204
-1.000 0.6418 0.00863 0.00239 -0.1611 0.5491 0.0209
-0.750 0.6701 0.00857 0.00225 -0.1610 0.5347 0.0214
-0.500 0.6982 0.00854 0.00213 -0.1609 0.5182 0.0219
-0.250 0.7262 0.00854 0.00203 -0.1608 0.4994 0.0225
0.000 0.7538 0.00861 0.00197 -0.1606 0.4745 0.0231
0.250 0.7805 0.00881 0.00195 -0.1603 0.4313 0.0242
0.500 0.8070 0.00906 0.00201 -0.1600 0.3863 0.0256
0.750 0.8335 0.00932 0.00208 -0.1597 0.3467 0.0269
1.000 0.8605 0.00950 0.00214 -0.1595 0.3211 0.0287
1.250 0.8876 0.00967 0.00223 -0.1592 0.3003 0.0319
1.500 0.9147 0.00982 0.00233 -0.1590 0.2844 0.0354
1.750 0.9418 0.00999 0.00243 -0.1587 0.2711 0.0389
2.000 0.9690 0.01012 0.00253 -0.1585 0.2604 0.0418
2.250 0.9962 0.01024 0.00263 -0.1583 0.2518 0.0443
2.750 1.0503 0.01051 0.00283 -0.1578 0.2348 0.0477
3.000 1.0775 0.01062 0.00291 -0.1576 0.2286 0.0511
3.250 1.1047 0.01073 0.00301 -0.1573 0.2239 0.0536
3.500 1.1318 0.01083 0.00311 -0.1571 0.2194 0.0553
3.750 1.1586 0.01098 0.00323 -0.1568 0.2136 0.0566
4.000 1.1854 0.01111 0.00335 -0.1565 0.2081 0.0600
4.250 1.2124 0.01121 0.00348 -0.1563 0.2045 0.0650
4.500 1.2392 0.01134 0.00362 -0.1560 0.2007 0.0772
5.500 1.3431 0.01099 0.00458 -0.1549 0.1745 1.0000
5.750 1.3685 0.01127 0.00479 -0.1545 0.1630 1.0000
6.250 1.4152 0.01229 0.00551 -0.1530 0.1162 1.0000
6.500 1.4388 0.01275 0.00589 -0.1522 0.1021 1.0000
6.750 1.4623 0.01321 0.00627 -0.1515 0.0885 1.0000
7.000 1.4801 0.01433 0.00708 -0.1499 0.0442 1.0000
7.250 1.5038 0.01473 0.00746 -0.1492 0.0401 1.0000
7.500 1.5274 0.01511 0.00783 -0.1484 0.0365 1.0000
7.750 1.5512 0.01543 0.00817 -0.1477 0.0352 1.0000
8.000 1.5749 0.01576 0.00852 -0.1470 0.0346 1.0000
8.250 1.5982 0.01612 0.00891 -0.1463 0.0338 1.0000
8.500 1.6212 0.01650 0.00930 -0.1455 0.0330 1.0000
8.750 1.6437 0.01690 0.00971 -0.1446 0.0321 1.0000
9.000 1.6658 0.01732 0.01015 -0.1437 0.0311 1.0000
9.250 1.6875 0.01776 0.01062 -0.1427 0.0303 1.0000
9.500 1.7086 0.01823 0.01112 -0.1417 0.0292 1.0000
9.750 1.7292 0.01873 0.01165 -0.1405 0.0281 1.0000
10.000 1.7500 0.01917 0.01213 -0.1394 0.0275 1.0000
10.250 1.7709 0.01956 0.01256 -0.1384 0.0271 1.0000
10.500 1.7914 0.01996 0.01301 -0.1372 0.0266 1.0000
10.750 1.8112 0.02040 0.01348 -0.1360 0.0258 1.0000
11.000 1.8301 0.02087 0.01399 -0.1347 0.0245 1.0000
11.250 1.8473 0.02143 0.01458 -0.1331 0.0219 1.0000
11.500 1.8612 0.02217 0.01527 -0.1310 0.0178 1.0000
11.750 1.8713 0.02300 0.01608 -0.1283 0.0139 1.0000
12.000 1.8773 0.02401 0.01709 -0.1249 0.0093 1.0000
12.250 1.8831 0.02509 0.01821 -0.1217 0.0074 1.0000
12.500 1.8902 0.02615 0.01933 -0.1189 0.0067 1.0000
12.750 1.8970 0.02729 0.02053 -0.1162 0.0062 1.0000
13.000 1.9037 0.02851 0.02183 -0.1137 0.0058 1.0000
13.250 1.9109 0.02977 0.02317 -0.1116 0.0057 1.0000
13.500 1.9172 0.03119 0.02467 -0.1095 0.0055 1.0000
13.750 1.9225 0.03276 0.02634 -0.1076 0.0053 1.0000
14.000 1.9267 0.03452 0.02819 -0.1058 0.0052 1.0000
14.250 1.9300 0.03646 0.03022 -0.1041 0.0050 1.0000
14.500 1.9318 0.03861 0.03247 -0.1026 0.0049 1.0000
14.750 1.9322 0.04103 0.03497 -0.1012 0.0047 1.0000
15.000 1.9313 0.04368 0.03773 -0.1001 0.0046 1.0000
15.250 1.9286 0.04662 0.04078 -0.0990 0.0045 1.0000
15.500 1.9243 0.04988 0.04415 -0.0982 0.0044 1.0000
15.750 1.9176 0.05352 0.04791 -0.0976 0.0043 1.0000
16.000 1.9096 0.05743 0.05194 -0.0972 0.0042 1.0000
16.250 1.8994 0.06178 0.05642 -0.0971 0.0041 1.0000
16.500 1.8906 0.06612 0.06088 -0.0972 0.0041 1.0000
16.750 1.8805 0.07077 0.06566 -0.0976 0.0041 1.0000
17.000 1.8691 0.07577 0.07079 -0.0983 0.0040 1.0000
17.250 1.8565 0.08113 0.07627 -0.0993 0.0040 1.0000
17.500 1.8409 0.08710 0.08237 -0.1006 0.0040 1.0000
17.750 1.8244 0.09333 0.08874 -0.1022 0.0040 1.0000
18.000 1.8066 0.09996 0.09552 -0.1042 0.0040 1.0000
18.250 1.7873 0.10701 0.10270 -0.1065 0.0040 1.0000
18.500 1.7670 0.11432 0.11015 -0.1091 0.0039 1.0000
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Polar data table (+)
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