GOE 456 AIRFOIL (goe456-il) Xfoil prediction polar at RE=200,000 Ncrit=5
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Airfoil: GOE 456 AIRFOIL (goe456-il) Reynolds number: 200,000 Max Cl/Cd: 86.35 at α=4° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe456-il-200000-n5.txt Download as CSV file: xf-goe456-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 456 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
------ -------- --------- --------- -------- -------- --------
-9.000 -0.2927 0.10872 0.10536 -0.0349 1.0000 0.0145
-8.750 -0.2938 0.10661 0.10330 -0.0339 1.0000 0.0150
-8.500 -0.2970 0.10468 0.10142 -0.0326 1.0000 0.0153
-8.250 -0.2870 0.10141 0.09817 -0.0350 0.9976 0.0157
-8.000 -0.2705 0.09738 0.09415 -0.0394 0.9930 0.0164
-7.750 -0.2543 0.09352 0.09028 -0.0438 0.9882 0.0172
-7.500 -0.2398 0.08979 0.08657 -0.0478 0.9823 0.0181
-7.250 -0.2242 0.08602 0.08281 -0.0523 0.9761 0.0190
-7.000 -0.2081 0.08236 0.07915 -0.0575 0.9688 0.0201
-6.750 -0.1863 0.07838 0.07517 -0.0660 0.9594 0.0213
-6.500 -0.1581 0.07381 0.07059 -0.0749 0.9537 0.0217
-6.250 -0.1344 0.06947 0.06619 -0.0813 0.9460 0.0218
-6.000 -0.1045 0.06466 0.06133 -0.0889 0.9416 0.0218
-5.750 -0.0807 0.06020 0.05683 -0.0944 0.9328 0.0219
-5.500 -0.0493 0.05517 0.05170 -0.1015 0.9279 0.0219
-5.250 -0.0246 0.05051 0.04696 -0.1062 0.9192 0.0219
-5.000 -0.0022 0.04403 0.04037 -0.1100 0.9132 0.0114
-4.750 0.0266 0.03862 0.03477 -0.1154 0.9049 0.0109
-4.500 0.0605 0.03227 0.02811 -0.1209 0.8988 0.0104
-4.250 0.0904 0.02665 0.02198 -0.1241 0.8911 0.0102
-4.000 0.1214 0.02309 0.01782 -0.1258 0.8852 0.0110
-3.750 0.1495 0.02128 0.01549 -0.1260 0.8776 0.0120
-3.500 0.1789 0.01893 0.01258 -0.1265 0.8716 0.0121
-3.250 0.2057 0.01679 0.00996 -0.1262 0.8640 0.0123
-3.000 0.2338 0.01490 0.00771 -0.1261 0.8575 0.0130
-2.750 0.2606 0.01381 0.00646 -0.1258 0.8495 0.0151
-2.500 0.2881 0.01314 0.00565 -0.1256 0.8420 0.0184
-2.250 0.3161 0.01253 0.00481 -0.1254 0.8344 0.0211
-2.000 0.3432 0.01199 0.00413 -0.1251 0.8259 0.0302
-1.750 0.3706 0.01118 0.00361 -0.1250 0.8183 0.1261
-1.500 0.3971 0.01109 0.00353 -0.1247 0.8086 0.1773
-1.250 0.4241 0.01100 0.00338 -0.1245 0.7997 0.2016
-1.000 0.4515 0.01089 0.00319 -0.1244 0.7909 0.2150
-0.750 0.4779 0.01080 0.00304 -0.1240 0.7808 0.2264
-0.500 0.5046 0.01071 0.00291 -0.1237 0.7709 0.2426
-0.250 0.5315 0.01063 0.00281 -0.1235 0.7612 0.2671
0.000 0.5577 0.01054 0.00275 -0.1232 0.7506 0.2999
0.250 0.5837 0.01042 0.00271 -0.1229 0.7402 0.3474
0.500 0.6089 0.01012 0.00270 -0.1224 0.7300 0.4648
1.000 0.6721 0.00925 0.00267 -0.1238 0.7094 1.0000
1.250 0.6981 0.00937 0.00267 -0.1234 0.6972 1.0000
1.500 0.7238 0.00949 0.00269 -0.1229 0.6835 1.0000
1.750 0.7493 0.00963 0.00272 -0.1223 0.6692 1.0000
2.000 0.7747 0.00978 0.00280 -0.1218 0.6561 1.0000
2.250 0.8001 0.00994 0.00289 -0.1213 0.6433 1.0000
2.500 0.8254 0.01012 0.00300 -0.1207 0.6309 1.0000
2.750 0.8504 0.01030 0.00316 -0.1202 0.6174 1.0000
3.000 0.8753 0.01050 0.00331 -0.1196 0.6041 1.0000
3.250 0.9004 0.01068 0.00350 -0.1190 0.5928 1.0000
3.500 0.9257 0.01086 0.00372 -0.1186 0.5830 1.0000
3.750 0.9509 0.01105 0.00399 -0.1181 0.5728 1.0000
4.000 0.9740 0.01128 0.00421 -0.1171 0.5515 1.0000
4.250 0.9926 0.01165 0.00440 -0.1152 0.5018 1.0000
4.500 1.0069 0.01232 0.00468 -0.1126 0.4130 1.0000
4.750 1.0046 0.01446 0.00568 -0.1079 0.2270 1.0000
5.250 1.0205 0.01782 0.00793 -0.1017 0.0176 1.0000
5.500 1.0397 0.01854 0.00882 -0.1001 0.0147 1.0000
5.750 1.0563 0.01949 0.00998 -0.0981 0.0118 1.0000
6.000 1.0736 0.02032 0.01098 -0.0963 0.0109 1.0000
6.250 1.0882 0.02133 0.01216 -0.0941 0.0102 1.0000
6.500 1.0991 0.02251 0.01352 -0.0913 0.0096 1.0000
6.750 1.1072 0.02375 0.01485 -0.0881 0.0091 1.0000
7.000 1.1161 0.02498 0.01613 -0.0852 0.0083 1.0000
7.250 1.1217 0.02671 0.01787 -0.0821 0.0074 1.0000
7.500 1.1330 0.02904 0.02018 -0.0799 0.0070 1.0000
7.750 1.1538 0.03071 0.02194 -0.0787 0.0068 1.0000
8.000 1.1806 0.03278 0.02413 -0.0785 0.0067 1.0000
8.250 1.2127 0.03539 0.02691 -0.0792 0.0066 1.0000
8.500 1.2415 0.03840 0.03012 -0.0793 0.0067 1.0000
9.000 1.2897 0.04493 0.03716 -0.0784 0.0072 1.0000
9.500 1.2962 0.04921 0.04221 -0.0715 0.0064 1.0000
9.750 1.2979 0.05108 0.04440 -0.0679 0.0060 1.0000
10.000 1.2964 0.05328 0.04688 -0.0642 0.0057 1.0000
10.250 1.2912 0.05607 0.04995 -0.0606 0.0057 1.0000
10.500 1.2832 0.05921 0.05336 -0.0573 0.0058 1.0000
10.750 1.2727 0.06251 0.05690 -0.0544 0.0060 1.0000
11.000 1.2608 0.06604 0.06066 -0.0520 0.0061 1.0000
11.250 1.2467 0.06989 0.06474 -0.0501 0.0062 1.0000
11.500 1.2316 0.07403 0.06909 -0.0489 0.0063 1.0000
11.750 1.2154 0.07855 0.07380 -0.0483 0.0064 1.0000
12.000 1.1987 0.08344 0.07888 -0.0485 0.0065 1.0000
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Polar data table (+)
Polar graphs
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