GOE 443 AIRFOIL (goe443-il) Xfoil prediction polar at RE=50,000 Ncrit=9
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Airfoil: GOE 443 AIRFOIL (goe443-il) Reynolds number: 50,000 Max Cl/Cd: 16.08 at α=3.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe443-il-50000.txt Download as CSV file: xf-goe443-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 443 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.750 -0.6559 0.09584 0.08935 0.0238 1.0000 0.3028
-7.500 -0.6383 0.09147 0.08498 0.0267 1.0000 0.3341
-7.250 -0.6331 0.08849 0.08205 0.0290 1.0000 0.3675
-7.000 -0.6274 0.08566 0.07927 0.0323 1.0000 0.4088
-6.750 -0.6051 0.08217 0.07564 0.0378 1.0000 0.4755
-6.500 -0.5901 0.07901 0.07249 0.0419 1.0000 0.5295
-4.750 -0.5306 0.03914 0.02967 -0.0103 1.0000 0.1319
-4.500 -0.5051 0.03535 0.02545 -0.0094 1.0000 0.1211
-4.250 -0.4777 0.03220 0.02160 -0.0082 1.0000 0.1115
-4.000 -0.4488 0.02997 0.01851 -0.0066 1.0000 0.1050
-3.750 -0.4209 0.02727 0.01546 -0.0055 1.0000 0.1045
-3.500 -0.3921 0.02467 0.01275 -0.0046 1.0000 0.1075
-3.250 -0.3648 0.02269 0.01079 -0.0037 1.0000 0.1252
-3.000 -0.2357 0.01571 0.00699 -0.0142 1.0000 1.0000
-2.750 -0.2178 0.01535 0.00610 -0.0130 1.0000 1.0000
-2.500 -0.1996 0.01503 0.00525 -0.0118 1.0000 1.0000
-2.250 -0.1809 0.01478 0.00467 -0.0106 1.0000 1.0000
-2.000 -0.1617 0.01456 0.00419 -0.0094 1.0000 1.0000
-1.750 -0.1421 0.01439 0.00378 -0.0083 1.0000 1.0000
-1.500 -0.1221 0.01425 0.00345 -0.0071 1.0000 1.0000
-1.250 -0.1020 0.01415 0.00318 -0.0060 1.0000 1.0000
-1.000 -0.0816 0.01406 0.00297 -0.0048 1.0000 1.0000
-0.750 -0.0612 0.01400 0.00276 -0.0036 1.0000 1.0000
-0.500 -0.0408 0.01396 0.00264 -0.0024 1.0000 1.0000
-0.250 -0.0204 0.01393 0.00257 -0.0012 1.0000 1.0000
0.000 0.0000 0.01392 0.00255 0.0000 1.0000 1.0000
0.250 0.0204 0.01393 0.00257 0.0012 1.0000 1.0000
0.500 0.0408 0.01396 0.00264 0.0024 1.0000 1.0000
0.750 0.0612 0.01400 0.00276 0.0036 1.0000 1.0000
1.000 0.0817 0.01406 0.00297 0.0048 1.0000 1.0000
1.250 0.1020 0.01415 0.00318 0.0060 1.0000 1.0000
1.500 0.1222 0.01425 0.00345 0.0071 1.0000 1.0000
1.750 0.1422 0.01439 0.00378 0.0083 1.0000 1.0000
2.000 0.1619 0.01456 0.00418 0.0094 1.0000 1.0000
2.250 0.1811 0.01477 0.00467 0.0106 1.0000 1.0000
2.500 0.1999 0.01503 0.00525 0.0117 1.0000 1.0000
2.750 0.2181 0.01534 0.00609 0.0129 1.0000 1.0000
3.000 0.2361 0.01571 0.00699 0.0141 1.0000 1.0000
3.250 0.3647 0.02268 0.01078 0.0037 0.1258 1.0000
3.500 0.3919 0.02465 0.01273 0.0046 0.1076 1.0000
3.750 0.4207 0.02726 0.01544 0.0056 0.1046 1.0000
4.000 0.4487 0.02993 0.01847 0.0066 0.1050 1.0000
4.250 0.4776 0.03218 0.02158 0.0082 0.1114 1.0000
4.500 0.5050 0.03534 0.02544 0.0094 0.1211 1.0000
4.750 0.5306 0.03908 0.02963 0.0103 0.1321 1.0000
5.000 0.5577 0.04275 0.03424 0.0108 0.1548 1.0000
6.250 0.5548 0.07386 0.06728 -0.0438 0.5786 1.0000
6.500 0.5880 0.07882 0.07229 -0.0419 0.5291 1.0000
6.750 0.6032 0.08203 0.07548 -0.0379 0.4750 1.0000
7.000 0.6257 0.08551 0.07911 -0.0324 0.4084 1.0000
7.250 0.6315 0.08835 0.08190 -0.0292 0.3665 1.0000
7.500 0.6522 0.09258 0.08615 -0.0257 0.3294 1.0000
7.750 0.6572 0.09587 0.08939 -0.0239 0.3029 1.0000
8.000 0.6662 0.09962 0.09311 -0.0219 0.2769 1.0000
8.500 0.6545 0.10513 0.09844 -0.0229 0.2438 1.0000
8.750 0.6726 0.11038 0.10370 -0.0206 0.2237 1.0000
9.000 0.6745 0.11408 0.10735 -0.0208 0.2104 1.0000
9.250 0.6648 0.11617 0.10934 -0.0230 0.2012 1.0000
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Polar data table (+)
Polar graphs
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