GOE 548 AIRFOIL (goe548-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 548 AIRFOIL (goe548-il) Reynolds number: 50,000 Max Cl/Cd: 34.07 at α=7.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe548-il-50000.txt Download as CSV file: xf-goe548-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 548 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
------ -------- --------- --------- -------- -------- --------
-10.250 -0.4098 0.12084 0.11373 -0.0284 1.0000 0.2728
-10.000 -0.4009 0.11678 0.10970 -0.0277 1.0000 0.2797
-9.750 -0.4261 0.11649 0.10956 -0.0275 1.0000 0.2889
-9.500 -0.3997 0.11082 0.10384 -0.0262 1.0000 0.2973
-9.250 -0.4107 0.10863 0.10176 -0.0255 1.0000 0.3057
-9.000 -0.4165 0.10655 0.09973 -0.0242 1.0000 0.3173
-8.750 -0.4088 0.10308 0.09629 -0.0227 1.0000 0.3306
-8.500 -0.4030 0.09964 0.09288 -0.0213 1.0000 0.3403
-8.000 -0.4121 0.09430 0.08768 -0.0182 1.0000 0.3569
-7.750 -0.4292 0.09223 0.08575 -0.0161 1.0000 0.3643
-7.250 -0.6060 0.06995 0.06371 -0.0348 1.0000 0.1563
-7.000 -0.6267 0.06363 0.05706 -0.0344 1.0000 0.1429
-6.750 -0.6260 0.05920 0.05250 -0.0328 1.0000 0.1379
-6.500 -0.6369 0.05354 0.04612 -0.0312 1.0000 0.1293
-6.250 -0.6301 0.04970 0.04198 -0.0294 1.0000 0.1271
-6.000 -0.6228 0.04596 0.03780 -0.0275 1.0000 0.1257
-5.750 -0.6135 0.04276 0.03404 -0.0254 1.0000 0.1275
-5.500 -0.6015 0.03996 0.03052 -0.0233 1.0000 0.1303
-5.250 -0.5843 0.03726 0.02768 -0.0219 1.0000 0.1337
-5.000 -0.5663 0.03524 0.02536 -0.0202 1.0000 0.1406
-4.750 -0.5476 0.03332 0.02316 -0.0187 1.0000 0.1490
-4.500 -0.5271 0.03168 0.02111 -0.0172 1.0000 0.1581
-4.250 -0.5072 0.03033 0.01964 -0.0158 1.0000 0.1721
-4.000 -0.4857 0.02897 0.01826 -0.0145 1.0000 0.1858
-3.750 -0.4657 0.02782 0.01725 -0.0131 1.0000 0.2085
-3.500 -0.4435 0.02655 0.01611 -0.0119 1.0000 0.2430
-3.250 -0.4259 0.02450 0.01516 -0.0099 1.0000 0.3707
-3.000 -0.4228 0.02332 0.01518 -0.0038 1.0000 0.5840
-2.750 -0.4139 0.02308 0.01532 0.0015 1.0000 0.6909
-2.500 -0.4008 0.02306 0.01556 0.0064 1.0000 0.7921
-2.250 -0.1584 0.02661 0.01802 -0.0272 1.0000 1.0000
-2.000 -0.1859 0.02539 0.01678 -0.0219 1.0000 1.0000
-1.750 -0.2008 0.02460 0.01583 -0.0174 1.0000 1.0000
-1.500 -0.2000 0.02431 0.01529 -0.0148 1.0000 1.0000
-1.250 -0.1924 0.02429 0.01499 -0.0128 1.0000 1.0000
-1.000 -0.1816 0.02442 0.01487 -0.0111 1.0000 1.0000
-0.750 -0.1690 0.02464 0.01486 -0.0097 1.0000 1.0000
-0.500 -0.1552 0.02492 0.01494 -0.0084 1.0000 1.0000
-0.250 -0.1407 0.02527 0.01509 -0.0073 1.0000 1.0000
0.000 -0.1257 0.02567 0.01529 -0.0063 1.0000 1.0000
0.250 -0.1105 0.02612 0.01559 -0.0054 1.0000 1.0000
0.500 -0.0951 0.02662 0.01595 -0.0045 1.0000 1.0000
0.750 -0.0796 0.02717 0.01637 -0.0038 1.0000 1.0000
1.000 -0.0640 0.02776 0.01685 -0.0031 1.0000 1.0000
1.250 -0.0486 0.02841 0.01737 -0.0024 1.0000 1.0000
1.500 -0.0331 0.02910 0.01797 -0.0019 1.0000 1.0000
1.750 0.0129 0.03074 0.01952 -0.0073 0.9869 1.0000
2.000 0.0561 0.03226 0.02096 -0.0120 0.9734 1.0000
2.250 0.0946 0.03356 0.02222 -0.0157 0.9601 1.0000
2.500 0.1284 0.03470 0.02334 -0.0184 0.9475 1.0000
2.750 0.1607 0.03582 0.02445 -0.0208 0.9346 1.0000
3.000 0.1903 0.03691 0.02554 -0.0227 0.9225 1.0000
3.250 0.2201 0.03803 0.02669 -0.0245 0.9102 1.0000
3.500 0.2505 0.03919 0.02788 -0.0264 0.8984 1.0000
3.750 0.2832 0.04038 0.02912 -0.0285 0.8865 1.0000
4.000 0.3098 0.04146 0.03026 -0.0297 0.8747 1.0000
4.250 0.3324 0.04248 0.03135 -0.0302 0.8622 1.0000
4.500 0.3555 0.04355 0.03252 -0.0308 0.8500 1.0000
4.750 0.3812 0.04464 0.03370 -0.0316 0.8371 1.0000
5.000 0.4106 0.04563 0.03480 -0.0328 0.8220 1.0000
5.250 0.4552 0.04611 0.03549 -0.0353 0.8002 1.0000
5.500 0.5079 0.04595 0.03557 -0.0381 0.7753 1.0000
5.750 0.5338 0.04630 0.03608 -0.0376 0.7538 1.0000
6.000 0.5808 0.04612 0.03621 -0.0394 0.7339 1.0000
6.250 0.6144 0.04613 0.03647 -0.0394 0.7128 1.0000
6.500 0.6939 0.04322 0.03411 -0.0422 0.6876 1.0000
6.750 0.7790 0.03809 0.02959 -0.0434 0.6571 1.0000
7.000 0.8779 0.03169 0.02391 -0.0457 0.6140 1.0000
7.250 0.9158 0.02823 0.02058 -0.0415 0.5566 1.0000
7.500 0.9288 0.02726 0.01949 -0.0361 0.4969 1.0000
7.750 0.9311 0.02740 0.01944 -0.0304 0.4338 1.0000
8.000 0.9272 0.02811 0.01980 -0.0244 0.3708 1.0000
8.250 0.9195 0.02939 0.02061 -0.0186 0.3068 1.0000
8.500 0.9075 0.03140 0.02198 -0.0131 0.2453 1.0000
8.750 0.8961 0.03427 0.02417 -0.0083 0.1857 1.0000
9.000 0.8963 0.03719 0.02658 -0.0048 0.1368 1.0000
9.250 0.9260 0.03947 0.02866 -0.0041 0.1106 1.0000
9.500 0.9888 0.04255 0.03179 -0.0077 0.0942 1.0000
9.750 1.0359 0.04617 0.03557 -0.0106 0.0857 1.0000
10.000 1.0603 0.04965 0.03955 -0.0099 0.0827 1.0000
10.250 1.0752 0.05332 0.04366 -0.0083 0.0813 1.0000
10.500 1.0805 0.05692 0.04768 -0.0057 0.0811 1.0000
10.750 1.0769 0.06042 0.05157 -0.0024 0.0813 1.0000
11.000 1.0660 0.06382 0.05531 0.0016 0.0817 1.0000
11.250 1.0516 0.06725 0.05903 0.0053 0.0825 1.0000
11.500 1.0335 0.07087 0.06291 0.0086 0.0831 1.0000
11.750 1.0132 0.07476 0.06703 0.0112 0.0839 1.0000
12.000 0.9924 0.07891 0.07137 0.0128 0.0847 1.0000
12.250 0.9691 0.08357 0.07620 0.0136 0.0854 1.0000
12.500 0.9480 0.08866 0.08142 0.0134 0.0863 1.0000
12.750 0.9295 0.09424 0.08709 0.0125 0.0872 1.0000
13.000 0.9243 0.09981 0.09270 0.0116 0.0881 1.0000
13.250 0.8055 0.12031 0.11326 -0.0055 0.0960 1.0000
13.500 0.7967 0.12806 0.12096 -0.0090 0.0989 1.0000
13.750 0.8046 0.13250 0.12542 -0.0090 0.1008 1.0000
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Polar data table (+)
Polar graphs
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