GOE 5K AIRFOIL (goe05k-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: GOE 5K AIRFOIL (goe05k-il) Reynolds number: 200,000 Max Cl/Cd: 39.8 at α=1.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe05k-il-200000-n5.txt Download as CSV file: xf-goe05k-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 5K AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.5223 0.09858 0.09501 -0.0117 1.0000 0.0093
-8.000 -0.5214 0.09552 0.09199 -0.0130 1.0000 0.0093
-7.750 -0.5225 0.09265 0.08918 -0.0142 1.0000 0.0093
-7.500 -0.5204 0.08942 0.08599 -0.0161 1.0000 0.0093
-7.250 -0.5191 0.08540 0.08199 -0.0150 1.0000 0.0095
-7.000 -0.5160 0.08192 0.07852 -0.0158 1.0000 0.0099
-6.750 -0.5108 0.07832 0.07494 -0.0179 1.0000 0.0101
-6.500 -0.5035 0.07467 0.07129 -0.0201 1.0000 0.0104
-6.250 -0.4944 0.07088 0.06748 -0.0225 1.0000 0.0107
-6.000 -0.4834 0.06698 0.06355 -0.0248 1.0000 0.0111
-5.750 -0.4701 0.06307 0.05959 -0.0271 1.0000 0.0116
-5.500 -0.4535 0.05912 0.05554 -0.0293 1.0000 0.0122
-5.250 -0.4299 0.05528 0.05151 -0.0318 1.0000 0.0127
-5.000 -0.4083 0.05181 0.04782 -0.0328 1.0000 0.0128
-4.750 -0.3980 0.04738 0.04334 -0.0328 1.0000 0.0132
-4.500 -0.3858 0.04389 0.03975 -0.0326 1.0000 0.0140
-4.250 -0.3674 0.04070 0.03638 -0.0324 1.0000 0.0151
-4.000 -0.3452 0.03779 0.03322 -0.0319 1.0000 0.0165
-3.750 -0.3172 0.03686 0.03188 -0.0305 1.0000 0.0180
-3.500 -0.3021 0.03144 0.02624 -0.0304 1.0000 0.0194
-3.250 -0.2843 0.02880 0.02345 -0.0300 1.0000 0.0233
-3.000 -0.2584 0.02709 0.02111 -0.0283 1.0000 0.0290
-2.750 -0.2385 0.02407 0.01802 -0.0279 1.0000 0.0329
-2.250 -0.1824 0.01852 0.01149 -0.0244 1.0000 0.0097
-2.000 -0.1524 0.01655 0.00917 -0.0242 0.9990 0.0087
-1.750 -0.1220 0.01486 0.00716 -0.0241 0.9978 0.0084
-1.500 -0.0917 0.01352 0.00556 -0.0241 0.9964 0.0091
-1.250 -0.0622 0.01249 0.00446 -0.0245 0.9945 0.0114
-1.000 -0.0322 0.01166 0.00348 -0.0249 0.9921 0.0148
-0.750 -0.0014 0.01096 0.00280 -0.0254 0.9897 0.0604
-0.500 0.0358 0.00821 0.00266 -0.0279 0.9946 1.0000
-0.250 0.0684 0.00829 0.00253 -0.0292 0.9912 1.0000
0.000 0.1019 0.00840 0.00251 -0.0308 0.9883 1.0000
0.250 0.1334 0.00847 0.00248 -0.0319 0.9845 1.0000
0.500 0.1662 0.00856 0.00253 -0.0332 0.9808 1.0000
0.750 0.1987 0.00865 0.00263 -0.0345 0.9774 1.0000
1.000 0.2299 0.00871 0.00272 -0.0355 0.9724 1.0000
1.250 0.2673 0.00877 0.00287 -0.0378 0.9683 1.0000
1.500 0.3020 0.00873 0.00296 -0.0394 0.9592 1.0000
1.750 0.3423 0.00860 0.00311 -0.0419 0.9478 1.0000
2.000 0.4063 0.01158 0.00254 -0.0478 0.0179 1.0000
2.250 0.4287 0.01229 0.00347 -0.0463 0.0119 1.0000
2.500 0.4501 0.01318 0.00449 -0.0449 0.0091 1.0000
2.750 0.4712 0.01434 0.00576 -0.0431 0.0085 1.0000
3.000 0.4934 0.01578 0.00727 -0.0416 0.0077 1.0000
3.250 0.5176 0.01746 0.00915 -0.0404 0.0069 1.0000
3.500 0.5433 0.01944 0.01139 -0.0392 0.0070 1.0000
3.750 0.5698 0.02165 0.01401 -0.0377 0.0080 1.0000
4.000 0.5935 0.02455 0.01727 -0.0360 0.0097 1.0000
4.500 0.6450 0.03121 0.02494 -0.0308 0.0260 1.0000
4.750 0.6641 0.03404 0.02811 -0.0289 0.0231 1.0000
5.000 0.6792 0.03755 0.03179 -0.0276 0.0210 1.0000
5.250 0.6860 0.04421 0.03871 -0.0260 0.0196 1.0000
5.500 0.7129 0.04442 0.03946 -0.0234 0.0171 1.0000
5.750 0.7284 0.04783 0.04314 -0.0219 0.0155 1.0000
6.250 0.7414 0.05731 0.05280 -0.0201 0.0138 1.0000
7.250 0.7140 0.06196 0.05867 -0.0141 0.0132 1.0000
7.500 0.7089 0.06665 0.06345 -0.0146 0.0130 1.0000
7.750 0.6982 0.07083 0.06767 -0.0144 0.0131 1.0000
8.000 0.6862 0.07529 0.07215 -0.0156 0.0132 1.0000
8.250 0.6756 0.08030 0.07715 -0.0184 0.0134 1.0000
8.500 0.6682 0.08543 0.08227 -0.0211 0.0134 1.0000
|
Polar data table (+)
Polar graphs
<< Back to GOE 5K AIRFOIL (goe05k-il)