A18 (original) (a18-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: A18 (original) (a18-il) Reynolds number: 1,000,000 Max Cl/Cd: 109.61 at α=2° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-a18-il-1000000-n5.txt Download as CSV file: xf-a18-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: A18 (original)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.000 -0.6088 0.08451 0.08268 -0.0352 1.0000 0.0041
-11.750 -0.6229 0.07853 0.07669 -0.0385 1.0000 0.0041
-11.500 -0.7349 0.02930 0.02678 -0.0937 0.9975 0.0034
-11.250 -0.7061 0.02379 0.02084 -0.1000 0.9963 0.0035
-11.000 -0.6749 0.02123 0.01801 -0.1033 0.9953 0.0037
-10.750 -0.6440 0.01950 0.01605 -0.1056 0.9941 0.0039
-10.500 -0.6140 0.01820 0.01455 -0.1071 0.9925 0.0040
-10.250 -0.5835 0.01713 0.01332 -0.1085 0.9910 0.0041
-10.000 -0.5528 0.01565 0.01162 -0.1102 0.9897 0.0044
-9.750 -0.5216 0.01458 0.01040 -0.1116 0.9886 0.0047
-9.500 -0.4902 0.01377 0.00947 -0.1128 0.9876 0.0050
-9.250 -0.4589 0.01307 0.00866 -0.1139 0.9865 0.0053
-9.000 -0.4292 0.01245 0.00793 -0.1146 0.9844 0.0056
-8.750 -0.3996 0.01191 0.00728 -0.1151 0.9818 0.0060
-8.500 -0.3690 0.01143 0.00671 -0.1158 0.9793 0.0063
-8.250 -0.3376 0.01082 0.00597 -0.1168 0.9769 0.0069
-8.000 -0.3083 0.01033 0.00541 -0.1172 0.9726 0.0078
-7.750 -0.2784 0.00993 0.00495 -0.1177 0.9682 0.0088
-7.500 -0.2481 0.00960 0.00455 -0.1182 0.9644 0.0096
-7.250 -0.2194 0.00919 0.00408 -0.1184 0.9587 0.0120
-7.000 -0.1900 0.00886 0.00370 -0.1187 0.9531 0.0153
-6.750 -0.1614 0.00851 0.00342 -0.1189 0.9464 0.0261
-6.500 -0.1329 0.00837 0.00324 -0.1189 0.9387 0.0307
-6.250 -0.1046 0.00820 0.00304 -0.1189 0.9298 0.0335
-6.000 -0.0765 0.00807 0.00289 -0.1188 0.9197 0.0360
-5.750 -0.0487 0.00800 0.00275 -0.1187 0.9080 0.0383
-5.500 -0.0208 0.00792 0.00261 -0.1185 0.8953 0.0395
-5.250 0.0073 0.00784 0.00246 -0.1185 0.8832 0.0408
-5.000 0.0356 0.00768 0.00226 -0.1185 0.8712 0.0444
-4.750 0.0638 0.00758 0.00209 -0.1184 0.8579 0.0460
-4.500 0.0920 0.00751 0.00194 -0.1184 0.8438 0.0475
-4.250 0.1201 0.00745 0.00181 -0.1183 0.8285 0.0489
-4.000 0.1483 0.00741 0.00168 -0.1183 0.8135 0.0502
-3.750 0.1766 0.00738 0.00158 -0.1183 0.7992 0.0512
-3.500 0.2047 0.00737 0.00149 -0.1183 0.7835 0.0520
-3.250 0.2330 0.00732 0.00136 -0.1183 0.7681 0.0560
-3.000 0.2614 0.00728 0.00129 -0.1184 0.7544 0.0601
-2.750 0.2898 0.00726 0.00123 -0.1184 0.7411 0.0639
-2.500 0.3182 0.00725 0.00118 -0.1185 0.7282 0.0695
-2.250 0.3465 0.00722 0.00114 -0.1186 0.7147 0.0797
-2.000 0.3747 0.00719 0.00111 -0.1186 0.6961 0.0999
-1.750 0.4026 0.00719 0.00110 -0.1187 0.6712 0.1281
-1.500 0.4303 0.00725 0.00111 -0.1187 0.6401 0.1494
-1.250 0.4578 0.00737 0.00113 -0.1186 0.6046 0.1661
-1.000 0.4854 0.00746 0.00116 -0.1187 0.5759 0.1883
-0.750 0.5134 0.00751 0.00121 -0.1187 0.5582 0.2150
-0.500 0.5414 0.00756 0.00126 -0.1188 0.5431 0.2377
-0.250 0.5695 0.00759 0.00131 -0.1189 0.5293 0.2601
0.000 0.5978 0.00754 0.00139 -0.1192 0.5191 0.3220
0.250 0.6261 0.00755 0.00147 -0.1193 0.5087 0.3633
0.500 0.6543 0.00758 0.00155 -0.1194 0.4973 0.3912
0.750 0.6822 0.00765 0.00161 -0.1195 0.4789 0.4052
1.000 0.7089 0.00792 0.00170 -0.1194 0.4286 0.4161
1.250 0.7363 0.00804 0.00183 -0.1194 0.4127 0.4388
1.500 0.7642 0.00798 0.00200 -0.1197 0.4002 0.5577
1.750 0.7915 0.00797 0.00220 -0.1198 0.3796 0.6714
2.000 0.8122 0.00741 0.00229 -0.1181 0.3628 1.0000
2.250 0.8362 0.00812 0.00255 -0.1177 0.2613 1.0000
2.500 0.8603 0.00882 0.00291 -0.1173 0.1903 1.0000
2.750 0.8868 0.00914 0.00312 -0.1171 0.1655 1.0000
3.000 0.9133 0.00943 0.00332 -0.1170 0.1452 1.0000
3.250 0.9393 0.00979 0.00354 -0.1168 0.1179 1.0000
3.500 0.9641 0.01033 0.00386 -0.1165 0.0746 1.0000
3.750 0.9894 0.01076 0.00419 -0.1162 0.0512 1.0000
4.000 1.0144 0.01124 0.00454 -0.1158 0.0296 1.0000
4.250 1.0395 0.01169 0.00490 -0.1154 0.0142 1.0000
4.500 1.0653 0.01200 0.00522 -0.1151 0.0119 1.0000
4.750 1.0907 0.01238 0.00561 -0.1148 0.0095 1.0000
5.000 1.1163 0.01270 0.00597 -0.1145 0.0085 1.0000
5.250 1.1417 0.01304 0.00633 -0.1142 0.0076 1.0000
5.500 1.1665 0.01343 0.00673 -0.1138 0.0068 1.0000
5.750 1.1904 0.01395 0.00729 -0.1132 0.0060 1.0000
6.000 1.2151 0.01434 0.00771 -0.1127 0.0057 1.0000
6.250 1.2393 0.01476 0.00818 -0.1122 0.0054 1.0000
6.500 1.2631 0.01523 0.00871 -0.1117 0.0050 1.0000
6.750 1.2867 0.01569 0.00920 -0.1111 0.0047 1.0000
7.000 1.3098 0.01619 0.00972 -0.1105 0.0043 1.0000
7.250 1.3308 0.01695 0.01054 -0.1094 0.0039 1.0000
7.500 1.3534 0.01746 0.01111 -0.1087 0.0038 1.0000
7.750 1.3752 0.01806 0.01177 -0.1079 0.0036 1.0000
8.000 1.3962 0.01870 0.01248 -0.1069 0.0035 1.0000
8.250 1.4167 0.01938 0.01324 -0.1058 0.0033 1.0000
8.500 1.4366 0.02009 0.01402 -0.1047 0.0032 1.0000
8.750 1.4559 0.02082 0.01485 -0.1035 0.0030 1.0000
9.000 1.4747 0.02157 0.01566 -0.1023 0.0029 1.0000
9.250 1.4929 0.02231 0.01648 -0.1009 0.0028 1.0000
9.500 1.5101 0.02312 0.01736 -0.0995 0.0027 1.0000
9.750 1.5256 0.02404 0.01835 -0.0977 0.0026 1.0000
10.000 1.5383 0.02511 0.01953 -0.0956 0.0026 1.0000
10.250 1.5452 0.02657 0.02113 -0.0925 0.0024 1.0000
10.500 1.5497 0.02792 0.02262 -0.0890 0.0024 1.0000
10.750 1.5570 0.02902 0.02383 -0.0861 0.0024 1.0000
11.250 1.5670 0.03174 0.02683 -0.0802 0.0023 1.0000
11.500 1.5710 0.03328 0.02850 -0.0774 0.0023 1.0000
11.750 1.5737 0.03499 0.03035 -0.0748 0.0022 1.0000
12.000 1.5751 0.03689 0.03240 -0.0724 0.0022 1.0000
12.250 1.5750 0.03904 0.03469 -0.0701 0.0021 1.0000
12.500 1.5742 0.04136 0.03716 -0.0682 0.0021 1.0000
12.750 1.5721 0.04395 0.03989 -0.0665 0.0020 1.0000
13.000 1.5677 0.04695 0.04306 -0.0652 0.0020 1.0000
13.250 1.5621 0.05029 0.04655 -0.0643 0.0020 1.0000
13.500 1.5554 0.05396 0.05038 -0.0639 0.0019 1.0000
13.750 1.5457 0.05828 0.05486 -0.0640 0.0019 1.0000
14.000 1.5353 0.06298 0.05971 -0.0646 0.0019 1.0000
14.250 1.5208 0.06858 0.06549 -0.0659 0.0019 1.0000
14.500 1.5038 0.07507 0.07214 -0.0680 0.0019 1.0000
14.750 1.4866 0.08194 0.07917 -0.0707 0.0019 1.0000
15.000 1.4644 0.09009 0.08750 -0.0742 0.0019 1.0000
15.250 1.4404 0.09922 0.09681 -0.0786 0.0019 1.0000
15.500 1.4102 0.11004 0.10780 -0.0840 0.0019 1.0000
15.750 1.3816 0.12115 0.11907 -0.0897 0.0019 1.0000
16.000 1.3448 0.13522 0.13333 -0.0971 0.0019 1.0000
16.250 1.3077 0.14969 0.14796 -0.1047 0.0020 1.0000
16.500 1.2739 0.16398 0.16237 -0.1125 0.0021 1.0000
|
Polar data table (+)
Polar graphs
<< Back to A18 (original) (a18-il)