GOE 124 (MVA H.4) AIRFOIL (goe124-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 124 (MVA H.4) AIRFOIL (goe124-il) Reynolds number: 1,000,000 Max Cl/Cd: 133.18 at α=3.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe124-il-1000000.txt Download as CSV file: xf-goe124-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 124 (MVA H.4) 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.2941 0.09079 0.08917 -0.0270 0.9362 0.0168
-7.750 -0.2917 0.08753 0.08583 -0.0299 0.9084 0.0169
-7.500 -0.2797 0.08339 0.08162 -0.0355 0.8892 0.0169
-7.250 -0.2709 0.07929 0.07746 -0.0367 0.8743 0.0171
-7.000 -0.2577 0.07667 0.07478 -0.0379 0.8599 0.0173
-6.750 -0.2420 0.07397 0.07201 -0.0404 0.8456 0.0175
-5.250 -0.0833 0.04837 0.04580 -0.0771 0.7670 0.0209
-5.000 -0.0603 0.04618 0.04353 -0.0789 0.7546 0.0211
-4.750 -0.0343 0.04388 0.04115 -0.0813 0.7432 0.0214
-4.500 -0.0060 0.04149 0.03866 -0.0841 0.7325 0.0220
-4.000 0.0739 0.03355 0.03025 -0.0933 0.7126 0.0248
-3.750 0.1072 0.03002 0.02647 -0.0960 0.7029 0.0249
-3.500 0.1368 0.02551 0.02173 -0.0992 0.6936 0.0255
-3.250 0.1648 0.02426 0.02039 -0.1002 0.6848 0.0259
-3.000 0.1940 0.02287 0.01887 -0.1013 0.6765 0.0264
-2.750 0.2245 0.02132 0.01716 -0.1024 0.6688 0.0275
-2.500 0.2585 0.02036 0.01586 -0.1026 0.6610 0.0300
-2.250 0.2897 0.01906 0.01432 -0.1034 0.6539 0.0301
-2.000 0.3204 0.01778 0.01281 -0.1042 0.6467 0.0302
0.250 0.5902 0.00981 0.00371 -0.1086 0.5841 0.0346
0.500 0.6200 0.00920 0.00304 -0.1088 0.5772 0.0330
0.750 0.6493 0.00888 0.00268 -0.1090 0.5691 0.0329
1.000 0.6785 0.00868 0.00247 -0.1092 0.5598 0.0335
1.250 0.7075 0.00857 0.00232 -0.1094 0.5495 0.0343
1.500 0.7366 0.00847 0.00219 -0.1096 0.5395 0.0349
1.750 0.7656 0.00840 0.00210 -0.1098 0.5283 0.0355
2.000 0.7943 0.00839 0.00205 -0.1100 0.5138 0.0362
2.250 0.8230 0.00839 0.00199 -0.1102 0.4984 0.0374
2.500 0.8518 0.00837 0.00191 -0.1104 0.4845 0.0397
2.750 0.8803 0.00843 0.00194 -0.1105 0.4689 0.0423
3.000 0.9085 0.00854 0.00198 -0.1106 0.4519 0.0450
3.250 0.9399 0.00740 0.00233 -0.1123 0.4327 0.8100
3.500 0.9602 0.00721 0.00237 -0.1104 0.4141 1.0000
3.750 0.9879 0.00744 0.00249 -0.1104 0.3949 1.0000
4.000 1.0156 0.00767 0.00263 -0.1105 0.3786 1.0000
4.250 1.0433 0.00788 0.00277 -0.1105 0.3660 1.0000
4.500 1.0708 0.00810 0.00294 -0.1106 0.3540 1.0000
4.750 1.0984 0.00829 0.00309 -0.1106 0.3440 1.0000
5.000 1.1260 0.00848 0.00325 -0.1106 0.3352 1.0000
5.250 1.1534 0.00870 0.00343 -0.1106 0.3261 1.0000
5.500 1.1809 0.00888 0.00359 -0.1106 0.3176 1.0000
5.750 1.2080 0.00911 0.00378 -0.1106 0.3071 1.0000
6.000 1.2348 0.00937 0.00399 -0.1106 0.2943 1.0000
6.250 1.2617 0.00960 0.00419 -0.1105 0.2809 1.0000
6.500 1.2881 0.00989 0.00441 -0.1105 0.2625 1.0000
6.750 1.3126 0.01045 0.00475 -0.1102 0.2202 1.0000
7.000 1.3318 0.01173 0.00557 -0.1093 0.1435 1.0000
7.250 1.3557 0.01231 0.00604 -0.1088 0.1244 1.0000
7.500 1.3803 0.01275 0.00643 -0.1085 0.1138 1.0000
7.750 1.4053 0.01310 0.00678 -0.1082 0.1059 1.0000
8.000 1.4296 0.01354 0.00718 -0.1078 0.0972 1.0000
8.250 1.4545 0.01386 0.00751 -0.1075 0.0910 1.0000
8.500 1.4784 0.01430 0.00791 -0.1071 0.0817 1.0000
8.750 1.5009 0.01486 0.00838 -0.1065 0.0665 1.0000
9.000 1.5195 0.01583 0.00915 -0.1054 0.0417 1.0000
9.250 1.5356 0.01699 0.01014 -0.1039 0.0213 1.0000
9.500 1.5547 0.01777 0.01093 -0.1028 0.0174 1.0000
9.750 1.5753 0.01835 0.01156 -0.1018 0.0163 1.0000
10.000 1.5939 0.01906 0.01231 -0.1006 0.0151 1.0000
10.250 1.6092 0.02002 0.01333 -0.0989 0.0137 1.0000
10.500 1.6276 0.02063 0.01400 -0.0977 0.0132 1.0000
10.750 1.6438 0.02135 0.01477 -0.0962 0.0126 1.0000
11.000 1.6575 0.02214 0.01563 -0.0943 0.0121 1.0000
11.250 1.6667 0.02303 0.01658 -0.0917 0.0117 1.0000
11.500 1.6722 0.02418 0.01780 -0.0888 0.0112 1.0000
11.750 1.6728 0.02582 0.01955 -0.0857 0.0108 1.0000
12.000 1.6761 0.02745 0.02128 -0.0833 0.0105 1.0000
12.250 1.6843 0.02880 0.02271 -0.0818 0.0103 1.0000
12.500 1.6913 0.03035 0.02435 -0.0803 0.0101 1.0000
12.750 1.6967 0.03213 0.02622 -0.0789 0.0099 1.0000
13.000 1.7013 0.03409 0.02827 -0.0777 0.0096 1.0000
13.250 1.7054 0.03616 0.03042 -0.0767 0.0093 1.0000
13.500 1.7085 0.03844 0.03278 -0.0758 0.0091 1.0000
13.750 1.7104 0.04091 0.03534 -0.0750 0.0089 1.0000
14.000 1.7100 0.04371 0.03823 -0.0744 0.0087 1.0000
14.250 1.7063 0.04699 0.04160 -0.0739 0.0085 1.0000
14.500 1.6985 0.05081 0.04553 -0.0735 0.0084 1.0000
14.750 1.6863 0.05527 0.05012 -0.0733 0.0082 1.0000
15.000 1.6716 0.06018 0.05516 -0.0733 0.0081 1.0000
15.250 1.6591 0.06499 0.06009 -0.0735 0.0080 1.0000
15.500 1.6553 0.06879 0.06400 -0.0738 0.0079 1.0000
15.750 1.6514 0.07268 0.06799 -0.0743 0.0079 1.0000
16.000 1.6457 0.07689 0.07231 -0.0749 0.0078 1.0000
16.250 1.6390 0.08135 0.07687 -0.0757 0.0077 1.0000
16.500 1.6321 0.08594 0.08156 -0.0767 0.0076 1.0000
16.750 1.6241 0.09074 0.08647 -0.0778 0.0075 1.0000
17.000 1.6152 0.09571 0.09156 -0.0790 0.0075 1.0000
17.250 1.6067 0.10074 0.09669 -0.0804 0.0074 1.0000
17.500 1.5982 0.10585 0.10190 -0.0819 0.0073 1.0000
17.750 1.5892 0.11106 0.10722 -0.0835 0.0072 1.0000
18.000 1.5804 0.11629 0.11255 -0.0853 0.0071 1.0000
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Polar data table (+)
Polar graphs
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