GOE 8K AIRFOIL (goe08k-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: GOE 8K AIRFOIL (goe08k-il) Reynolds number: 500,000 Max Cl/Cd: 103.53 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe08k-il-500000.txt Download as CSV file: xf-goe08k-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 8K 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
------ -------- --------- --------- -------- -------- --------
-11.000 0.0462 0.08976 0.08690 -0.1786 0.9309 0.0306
-10.750 0.0253 0.08911 0.08628 -0.1720 0.9222 0.0306
-10.500 0.0310 0.08438 0.08156 -0.1760 0.9213 0.0307
-10.000 0.0519 0.07720 0.07436 -0.1800 0.9201 0.0316
-9.750 0.0687 0.07488 0.07202 -0.1822 0.9196 0.0324
-9.500 0.0777 0.07027 0.06740 -0.1871 0.9189 0.0325
-9.250 -0.0238 0.05360 0.05072 -0.1931 0.9067 0.0252
-9.000 -0.0578 0.05208 0.04918 -0.1856 0.8990 0.0250
-8.750 -0.0855 0.04690 0.04384 -0.1822 0.8935 0.0248
-8.500 -0.1183 0.03718 0.03361 -0.1798 0.8907 0.0246
-8.250 -0.1558 0.03829 0.03476 -0.1664 0.8798 0.0246
-8.000 -0.2289 0.03153 0.02738 -0.1498 0.8695 0.0251
-7.750 -0.2474 0.02688 0.02215 -0.1426 0.8654 0.0262
-7.500 -0.2115 0.02746 0.02280 -0.1446 0.8649 0.0268
-7.250 -0.1838 0.02676 0.02200 -0.1453 0.8641 0.0275
-7.000 -0.1663 0.02436 0.01923 -0.1440 0.8631 0.0292
-6.750 -0.1962 0.02427 0.01902 -0.1321 0.8534 0.0294
-6.500 -0.1841 0.02191 0.01619 -0.1293 0.8516 0.0313
-6.250 -0.1558 0.02145 0.01568 -0.1298 0.8507 0.0320
-6.000 -0.1245 0.02132 0.01554 -0.1309 0.8499 0.0332
-5.750 -0.0940 0.02077 0.01484 -0.1318 0.8492 0.0355
-5.500 -0.0658 0.01944 0.01323 -0.1321 0.8486 0.0377
-5.250 -0.0938 0.01999 0.01375 -0.1204 0.8391 0.0379
-5.000 -0.0660 0.01993 0.01372 -0.1208 0.8378 0.0392
-4.750 -0.0366 0.01956 0.01330 -0.1214 0.8367 0.0412
-4.500 -0.0063 0.01906 0.01262 -0.1219 0.8359 0.0437
-4.250 0.0244 0.01791 0.01133 -0.1229 0.8352 0.0459
-4.000 0.0583 0.01742 0.01083 -0.1246 0.8346 0.0478
-3.750 0.0934 0.01706 0.01042 -0.1265 0.8340 0.0509
-3.500 0.0590 0.01782 0.01117 -0.1132 0.8244 0.0508
-3.250 0.0869 0.01761 0.01085 -0.1134 0.8231 0.0528
-3.000 0.1180 0.01672 0.00987 -0.1143 0.8223 0.0551
-2.750 0.1499 0.01607 0.00924 -0.1155 0.8216 0.0571
-2.500 0.1828 0.01565 0.00881 -0.1169 0.8209 0.0595
-2.250 0.2176 0.01522 0.00834 -0.1187 0.8203 0.0618
-2.000 0.2536 0.01482 0.00790 -0.1207 0.8197 0.0633
-1.750 0.2155 0.01568 0.00876 -0.1066 0.8102 0.0633
-1.500 0.2431 0.01552 0.00856 -0.1068 0.8088 0.0646
-1.250 0.2718 0.01500 0.00803 -0.1072 0.8079 0.0660
-1.000 0.3008 0.01452 0.00754 -0.1076 0.8070 0.0677
-0.750 0.3327 0.01417 0.00719 -0.1088 0.8063 0.0694
-0.500 0.3665 0.01388 0.00690 -0.1103 0.8057 0.0721
-0.250 0.4015 0.01361 0.00662 -0.1121 0.8051 0.0743
0.000 0.4375 0.01339 0.00638 -0.1142 0.8046 0.0759
0.250 0.4753 0.01321 0.00619 -0.1167 0.8040 0.0780
0.750 0.6778 0.01103 0.00667 -0.1528 0.8065 0.9043
1.000 0.6289 0.01144 0.00704 -0.1357 0.8001 0.8900
1.250 0.4672 0.01490 0.00791 -0.0922 0.7858 0.0888
1.500 0.5207 0.01369 0.00751 -0.0984 0.7867 0.3635
1.750 0.9611 0.01142 0.00698 -0.1931 0.8063 1.0000
2.000 1.0039 0.01128 0.00680 -0.1969 0.8050 1.0000
2.250 0.9648 0.01181 0.00737 -0.1823 0.7979 1.0000
2.500 0.9829 0.01187 0.00742 -0.1805 0.7950 1.0000
2.750 1.0160 0.01176 0.00731 -0.1820 0.7932 1.0000
3.000 1.0543 0.01163 0.00717 -0.1847 0.7917 1.0000
3.250 1.0958 0.01152 0.00706 -0.1881 0.7904 1.0000
3.500 1.0584 0.01213 0.00771 -0.1739 0.7829 1.0000
3.750 1.0823 0.01214 0.00774 -0.1734 0.7803 1.0000
4.000 1.1192 0.01197 0.00758 -0.1757 0.7782 1.0000
4.250 1.1767 0.01152 0.00711 -0.1825 0.7753 1.0000
4.500 1.1415 0.01207 0.00771 -0.1687 0.7670 1.0000
4.750 1.1789 0.01181 0.00743 -0.1710 0.7632 1.0000
5.000 1.1942 0.01187 0.00751 -0.1684 0.7579 1.0000
5.250 1.1967 0.01206 0.00773 -0.1631 0.7511 1.0000
5.500 1.2268 0.01185 0.00751 -0.1637 0.7444 1.0000
5.750 1.2206 0.01216 0.00784 -0.1565 0.7353 1.0000
6.000 1.2261 0.01233 0.00802 -0.1518 0.7253 1.0000
6.250 1.2459 0.01231 0.00797 -0.1502 0.7156 1.0000
6.500 1.2388 0.01281 0.00850 -0.1431 0.7039 1.0000
6.750 1.2427 0.01323 0.00897 -0.1384 0.6943 1.0000
7.000 1.2493 0.01361 0.00935 -0.1343 0.6816 1.0000
7.250 1.2505 0.01417 0.00991 -0.1291 0.6654 1.0000
7.500 1.2509 0.01481 0.01053 -0.1239 0.6442 1.0000
7.750 1.2451 0.01572 0.01131 -0.1176 0.6071 1.0000
8.000 1.2363 0.01688 0.01226 -0.1110 0.5660 1.0000
8.250 1.2233 0.01835 0.01351 -0.1038 0.5247 1.0000
8.500 1.2114 0.01996 0.01489 -0.0972 0.4857 1.0000
8.750 1.2037 0.02150 0.01626 -0.0915 0.4484 1.0000
9.000 1.1964 0.02312 0.01770 -0.0862 0.4101 1.0000
9.250 1.1859 0.02501 0.01934 -0.0805 0.3603 1.0000
9.500 1.1755 0.02700 0.02104 -0.0752 0.3050 1.0000
9.750 1.1659 0.02904 0.02275 -0.0701 0.2478 1.0000
10.000 1.1622 0.03081 0.02427 -0.0661 0.2022 1.0000
10.250 1.1590 0.03261 0.02579 -0.0623 0.1529 1.0000
10.500 1.1521 0.03470 0.02750 -0.0582 0.0922 1.0000
10.750 1.1539 0.03629 0.02894 -0.0553 0.0667 1.0000
11.000 1.1590 0.03773 0.03030 -0.0528 0.0499 1.0000
11.250 1.1659 0.03906 0.03158 -0.0506 0.0404 1.0000
11.500 1.1751 0.04024 0.03277 -0.0488 0.0363 1.0000
11.750 1.1824 0.04159 0.03415 -0.0467 0.0332 1.0000
12.000 1.1925 0.04274 0.03535 -0.0451 0.0310 1.0000
12.250 1.1990 0.04418 0.03681 -0.0432 0.0287 1.0000
12.500 1.2021 0.04593 0.03862 -0.0408 0.0272 1.0000
12.750 1.2116 0.04720 0.03997 -0.0393 0.0259 1.0000
13.000 1.2202 0.04854 0.04135 -0.0378 0.0243 1.0000
13.250 1.2264 0.05009 0.04295 -0.0360 0.0233 1.0000
13.500 1.2280 0.05206 0.04497 -0.0339 0.0225 1.0000
13.750 1.2288 0.05411 0.04710 -0.0317 0.0217 1.0000
14.000 1.2368 0.05560 0.04866 -0.0304 0.0212 1.0000
14.250 1.2436 0.05719 0.05034 -0.0289 0.0207 1.0000
14.500 1.2485 0.05897 0.05220 -0.0273 0.0200 1.0000
14.750 1.2552 0.06062 0.05390 -0.0260 0.0191 1.0000
15.000 1.2609 0.06235 0.05566 -0.0248 0.0184 1.0000
15.250 1.2631 0.06439 0.05775 -0.0232 0.0179 1.0000
15.500 1.2647 0.06640 0.05983 -0.0214 0.0173 1.0000
15.750 1.2721 0.06808 0.06161 -0.0204 0.0169 1.0000
16.000 1.2783 0.06985 0.06348 -0.0193 0.0164 1.0000
16.250 1.2843 0.07158 0.06530 -0.0181 0.0161 1.0000
16.500 1.2896 0.07345 0.06726 -0.0171 0.0156 1.0000
16.750 1.2947 0.07536 0.06925 -0.0161 0.0152 1.0000
17.000 1.2999 0.07725 0.07121 -0.0151 0.0149 1.0000
17.250 1.3040 0.07927 0.07330 -0.0143 0.0146 1.0000
17.500 1.3084 0.08119 0.07524 -0.0134 0.0141 1.0000
17.750 1.3147 0.08273 0.07685 -0.0121 0.0137 1.0000
18.000 1.3180 0.08490 0.07918 -0.0111 0.0136 1.0000
18.250 1.3158 0.08796 0.08240 -0.0108 0.0133 1.0000
18.500 1.3170 0.09041 0.08502 -0.0098 0.0132 1.0000
18.750 1.3147 0.09352 0.08826 -0.0098 0.0128 1.0000
19.000 1.3126 0.09657 0.09146 -0.0095 0.0126 1.0000
19.250 1.3092 0.09982 0.09486 -0.0093 0.0123 1.0000
|
Polar data table (+)
Polar graphs
<< Back to GOE 8K AIRFOIL (goe08k-il)