GOE 184 (MVA H.29) AIRFOIL (goe184-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 184 (MVA H.29) AIRFOIL (goe184-il) Reynolds number: 1,000,000 Max Cl/Cd: 127.66 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe184-il-1000000.txt Download as CSV file: xf-goe184-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 184 (MVA H.29) 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
------ -------- --------- --------- -------- -------- --------
-8.500 -0.3372 0.09182 0.09027 -0.0241 1.0000 0.0168
-8.250 -0.3332 0.08816 0.08663 -0.0261 1.0000 0.0168
-8.000 -0.3320 0.08464 0.08315 -0.0276 1.0000 0.0168
-7.750 -0.3426 0.02324 0.02057 -0.0972 0.9713 0.0172
-7.500 -0.3161 0.02203 0.01928 -0.0979 0.9607 0.0176
-7.250 -0.2896 0.02202 0.01928 -0.0977 0.9494 0.0181
-7.000 -0.2641 0.02200 0.01925 -0.0972 0.9367 0.0186
-6.750 -0.2396 0.02010 0.01709 -0.0977 0.9216 0.0193
-6.500 -0.2149 0.01814 0.01476 -0.0979 0.9031 0.0201
-6.250 -0.1893 0.01720 0.01351 -0.0977 0.8816 0.0207
-6.000 -0.1623 0.01729 0.01339 -0.0973 0.8599 0.0211
-5.750 -0.1384 0.01421 0.00989 -0.0979 0.8401 0.0223
-5.500 -0.1116 0.01376 0.00932 -0.0977 0.8211 0.0230
-5.250 -0.0845 0.01323 0.00863 -0.0976 0.8039 0.0237
-5.000 -0.0570 0.01265 0.00785 -0.0975 0.7886 0.0244
-4.750 -0.0292 0.01213 0.00715 -0.0975 0.7748 0.0251
-4.500 -0.0011 0.01176 0.00664 -0.0974 0.7619 0.0257
-4.250 0.0271 0.01176 0.00651 -0.0972 0.7492 0.0262
-4.000 0.0549 0.01074 0.00527 -0.0973 0.7378 0.0268
-3.750 0.0828 0.00991 0.00431 -0.0973 0.7272 0.0275
-3.500 0.1111 0.00944 0.00376 -0.0973 0.7173 0.0282
-3.250 0.1394 0.00911 0.00337 -0.0973 0.7073 0.0290
-3.000 0.1677 0.00885 0.00303 -0.0973 0.6963 0.0299
-2.750 0.1962 0.00861 0.00272 -0.0972 0.6846 0.0304
-2.500 0.2247 0.00841 0.00243 -0.0972 0.6715 0.0308
-2.250 0.2531 0.00825 0.00219 -0.0972 0.6555 0.0313
-2.000 0.2813 0.00813 0.00198 -0.0971 0.6353 0.0318
-1.750 0.3095 0.00805 0.00179 -0.0970 0.6106 0.0323
-1.500 0.3375 0.00804 0.00165 -0.0969 0.5847 0.0329
-1.250 0.3655 0.00802 0.00149 -0.0968 0.5620 0.0344
-1.000 0.3936 0.00802 0.00140 -0.0967 0.5454 0.0360
-0.750 0.4219 0.00800 0.00133 -0.0967 0.5337 0.0381
-0.500 0.4502 0.00797 0.00129 -0.0967 0.5244 0.0460
-0.250 0.4786 0.00800 0.00137 -0.0967 0.5161 0.0666
0.000 0.5069 0.00806 0.00142 -0.0966 0.5088 0.0711
0.250 0.5352 0.00811 0.00148 -0.0966 0.5014 0.0765
0.500 0.5633 0.00820 0.00154 -0.0966 0.4937 0.0795
0.750 0.5915 0.00824 0.00155 -0.0966 0.4840 0.0814
1.000 0.6198 0.00822 0.00152 -0.0966 0.4746 0.0846
1.250 0.6479 0.00825 0.00153 -0.0966 0.4647 0.0866
1.500 0.6762 0.00827 0.00153 -0.0966 0.4549 0.0883
1.750 0.7044 0.00831 0.00155 -0.0966 0.4453 0.0897
2.000 0.7324 0.00837 0.00158 -0.0966 0.4341 0.0916
2.250 0.7602 0.00845 0.00162 -0.0966 0.4208 0.0934
2.500 0.7881 0.00852 0.00166 -0.0965 0.4063 0.0962
2.750 0.8158 0.00862 0.00172 -0.0965 0.3917 0.0993
3.000 0.8434 0.00873 0.00180 -0.0964 0.3780 0.1051
3.250 0.8711 0.00875 0.00193 -0.0965 0.3650 0.1711
3.500 0.8982 0.00774 0.00225 -0.0970 0.3554 0.7962
4.000 0.9484 0.00765 0.00246 -0.0956 0.3396 1.0000
4.250 0.9757 0.00783 0.00259 -0.0955 0.3321 1.0000
4.500 1.0032 0.00799 0.00272 -0.0954 0.3229 1.0000
4.750 1.0303 0.00818 0.00287 -0.0953 0.3139 1.0000
5.000 1.0577 0.00834 0.00301 -0.0952 0.3068 1.0000
5.250 1.0848 0.00852 0.00317 -0.0951 0.2987 1.0000
5.500 1.1118 0.00872 0.00333 -0.0950 0.2887 1.0000
5.750 1.1387 0.00892 0.00350 -0.0949 0.2758 1.0000
6.000 1.1648 0.00921 0.00370 -0.0947 0.2570 1.0000
6.250 1.1892 0.00973 0.00400 -0.0943 0.2139 1.0000
6.500 1.2108 0.01059 0.00457 -0.0936 0.1650 1.0000
6.750 1.2355 0.01104 0.00494 -0.0932 0.1497 1.0000
7.000 1.2608 0.01138 0.00525 -0.0929 0.1379 1.0000
7.250 1.2847 0.01189 0.00563 -0.0924 0.1140 1.0000
7.500 1.3056 0.01275 0.00625 -0.0916 0.0777 1.0000
7.750 1.3242 0.01385 0.00708 -0.0904 0.0358 1.0000
8.000 1.3464 0.01449 0.00770 -0.0896 0.0274 1.0000
8.250 1.3692 0.01503 0.00827 -0.0889 0.0238 1.0000
8.500 1.3924 0.01549 0.00878 -0.0883 0.0217 1.0000
8.750 1.4130 0.01620 0.00952 -0.0873 0.0190 1.0000
9.000 1.4357 0.01666 0.01002 -0.0866 0.0180 1.0000
9.250 1.4578 0.01714 0.01054 -0.0859 0.0169 1.0000
9.500 1.4787 0.01772 0.01114 -0.0850 0.0157 1.0000
9.750 1.4948 0.01872 0.01222 -0.0834 0.0143 1.0000
10.000 1.5159 0.01918 0.01271 -0.0826 0.0138 1.0000
10.250 1.5357 0.01973 0.01331 -0.0815 0.0131 1.0000
10.500 1.5540 0.02036 0.01398 -0.0803 0.0125 1.0000
10.750 1.5704 0.02109 0.01475 -0.0789 0.0119 1.0000
11.000 1.5805 0.02216 0.01589 -0.0765 0.0112 1.0000
11.250 1.5829 0.02348 0.01733 -0.0731 0.0108 1.0000
11.500 1.5942 0.02432 0.01823 -0.0710 0.0106 1.0000
11.750 1.6036 0.02533 0.01932 -0.0690 0.0103 1.0000
12.000 1.6114 0.02654 0.02061 -0.0670 0.0100 1.0000
12.250 1.6185 0.02789 0.02204 -0.0652 0.0097 1.0000
12.500 1.6251 0.02938 0.02360 -0.0637 0.0094 1.0000
12.750 1.6311 0.03102 0.02532 -0.0624 0.0091 1.0000
13.000 1.6362 0.03287 0.02724 -0.0613 0.0089 1.0000
13.250 1.6369 0.03531 0.02976 -0.0604 0.0086 1.0000
13.500 1.6307 0.03863 0.03319 -0.0596 0.0084 1.0000
13.750 1.6170 0.04303 0.03774 -0.0591 0.0082 1.0000
14.000 1.6095 0.04684 0.04168 -0.0590 0.0080 1.0000
14.250 1.6094 0.04989 0.04483 -0.0590 0.0080 1.0000
14.500 1.6074 0.05324 0.04829 -0.0592 0.0079 1.0000
14.750 1.6027 0.05703 0.05218 -0.0596 0.0078 1.0000
15.000 1.5974 0.06101 0.05627 -0.0602 0.0077 1.0000
15.250 1.5909 0.06522 0.06059 -0.0609 0.0076 1.0000
15.500 1.5836 0.06962 0.06509 -0.0617 0.0075 1.0000
15.750 1.5756 0.07421 0.06979 -0.0626 0.0074 1.0000
16.000 1.5673 0.07888 0.07456 -0.0637 0.0073 1.0000
16.250 1.5585 0.08367 0.07945 -0.0648 0.0072 1.0000
16.500 1.5496 0.08857 0.08445 -0.0660 0.0071 1.0000
16.750 1.5412 0.09348 0.08945 -0.0674 0.0070 1.0000
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