Eiffel 428 (Bleriot) (eiffel428-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: Eiffel 428 (Bleriot) (eiffel428-il) Reynolds number: 100,000 Max Cl/Cd: 59.37 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-eiffel428-il-100000.txt Download as CSV file: xf-eiffel428-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: Eiffel 428 (Bleriot)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.3400 0.10262 0.09771 -0.0353 1.0000 0.0788
-9.500 -0.3562 0.10216 0.09740 -0.0386 1.0000 0.0801
-9.250 -0.3715 0.10108 0.09647 -0.0404 1.0000 0.0804
-9.000 -0.3361 0.09336 0.08866 -0.0355 1.0000 0.0847
-8.750 -0.3337 0.09082 0.08618 -0.0349 1.0000 0.0873
-8.500 -0.3381 0.08869 0.08415 -0.0344 1.0000 0.0901
-8.250 -0.3503 0.08708 0.08269 -0.0336 1.0000 0.0922
-8.000 -0.3687 0.08599 0.08176 -0.0345 1.0000 0.0941
-7.750 -0.3928 0.08565 0.08155 -0.0330 1.0000 0.0947
-7.500 -0.4153 0.08530 0.08126 -0.0324 1.0000 0.0951
-7.250 -0.4195 0.08186 0.07782 -0.0351 0.9983 0.0962
-7.000 -0.4011 0.07798 0.07403 -0.0302 0.9949 0.0994
-6.750 -0.3598 0.07201 0.06778 -0.0478 0.9841 0.1116
-6.500 -0.3417 0.06906 0.06494 -0.0437 0.9788 0.1171
-6.250 -0.3056 0.06391 0.05963 -0.0537 0.9710 0.1290
-6.000 -0.2762 0.06000 0.05556 -0.0601 0.9611 0.1427
-5.750 -0.2450 0.05653 0.05198 -0.0644 0.9537 0.1575
-5.500 -0.2137 0.05352 0.04895 -0.0667 0.9456 0.1752
-5.250 -0.1767 0.05032 0.04551 -0.0727 0.9352 0.2020
-5.000 -0.1326 0.04657 0.04177 -0.0763 0.9288 0.2235
-4.750 -0.0938 0.04385 0.03885 -0.0804 0.9174 0.2598
-4.000 0.0458 0.02809 0.02045 -0.0953 0.8903 0.1244
-3.750 0.0868 0.02515 0.01706 -0.0972 0.8829 0.1152
-3.500 0.1149 0.02379 0.01526 -0.0966 0.8716 0.1139
-3.250 0.1474 0.02305 0.01409 -0.0966 0.8630 0.1109
-3.000 0.1795 0.02162 0.01247 -0.0968 0.8538 0.1101
-2.750 0.2072 0.02068 0.01136 -0.0962 0.8423 0.1102
-2.500 0.2365 0.01978 0.01033 -0.0958 0.8321 0.1113
-2.250 0.2651 0.01876 0.00940 -0.0955 0.8227 0.1173
-2.000 0.2899 0.01825 0.00889 -0.0946 0.8122 0.1214
-1.750 0.3175 0.01774 0.00832 -0.0939 0.8040 0.1253
-1.500 0.3422 0.01724 0.00788 -0.0929 0.7941 0.1320
-1.250 0.3676 0.01690 0.00757 -0.0921 0.7845 0.1448
-1.000 0.4389 0.01395 0.00704 -0.1004 0.7768 1.0000
-0.750 0.4628 0.01410 0.00692 -0.0992 0.7662 1.0000
-0.500 0.4885 0.01422 0.00680 -0.0984 0.7573 1.0000
-0.250 0.5135 0.01435 0.00677 -0.0976 0.7479 1.0000
0.000 0.5376 0.01450 0.00679 -0.0966 0.7375 1.0000
0.250 0.5637 0.01458 0.00671 -0.0959 0.7282 1.0000
0.500 0.5877 0.01473 0.00678 -0.0949 0.7178 1.0000
0.750 0.6122 0.01490 0.00689 -0.0941 0.7085 1.0000
1.000 0.6382 0.01502 0.00692 -0.0935 0.7002 1.0000
1.250 0.6617 0.01523 0.00711 -0.0926 0.6905 1.0000
1.500 0.6887 0.01535 0.00716 -0.0922 0.6836 1.0000
1.750 0.7116 0.01553 0.00737 -0.0911 0.6726 1.0000
2.000 0.7355 0.01561 0.00742 -0.0901 0.6604 1.0000
2.250 0.7596 0.01562 0.00740 -0.0890 0.6472 1.0000
2.500 0.7833 0.01561 0.00737 -0.0878 0.6329 1.0000
2.750 0.8065 0.01560 0.00736 -0.0866 0.6170 1.0000
3.000 0.8302 0.01565 0.00742 -0.0855 0.6037 1.0000
3.250 0.8546 0.01574 0.00751 -0.0847 0.5922 1.0000
3.500 0.8778 0.01583 0.00764 -0.0836 0.5781 1.0000
3.750 0.8999 0.01591 0.00778 -0.0823 0.5597 1.0000
4.000 0.9217 0.01600 0.00789 -0.0810 0.5384 1.0000
4.250 0.9437 0.01613 0.00800 -0.0797 0.5181 1.0000
4.500 0.9651 0.01633 0.00825 -0.0783 0.4951 1.0000
4.750 0.9849 0.01659 0.00842 -0.0767 0.4630 1.0000
5.000 1.0036 0.01697 0.00868 -0.0749 0.4256 1.0000
5.250 1.0224 0.01742 0.00908 -0.0732 0.3865 1.0000
5.500 1.0258 0.01883 0.00969 -0.0693 0.2592 1.0000
5.750 1.0332 0.02030 0.01078 -0.0663 0.1987 1.0000
6.000 1.0384 0.02191 0.01190 -0.0632 0.1344 1.0000
6.250 1.0465 0.02324 0.01316 -0.0603 0.1201 1.0000
6.500 1.0527 0.02461 0.01459 -0.0572 0.1070 1.0000
6.750 1.0621 0.02572 0.01580 -0.0544 0.0943 1.0000
7.000 1.0738 0.02658 0.01680 -0.0518 0.0837 1.0000
7.250 1.0845 0.02749 0.01780 -0.0492 0.0774 1.0000
7.500 1.0963 0.02834 0.01859 -0.0471 0.0723 1.0000
7.750 1.1035 0.02954 0.01978 -0.0445 0.0684 1.0000
8.000 1.1093 0.03096 0.02120 -0.0419 0.0664 1.0000
8.250 1.1159 0.03262 0.02279 -0.0394 0.0648 1.0000
8.500 1.1326 0.03426 0.02443 -0.0377 0.0634 1.0000
8.750 1.1622 0.03610 0.02631 -0.0374 0.0604 1.0000
9.000 1.2152 0.03890 0.02919 -0.0402 0.0589 1.0000
9.250 1.2630 0.04263 0.03325 -0.0426 0.0591 1.0000
9.500 1.2877 0.04590 0.03681 -0.0423 0.0581 1.0000
9.750 1.3019 0.04975 0.04124 -0.0405 0.0593 1.0000
10.000 1.3150 0.05464 0.04663 -0.0388 0.0624 1.0000
10.250 1.3215 0.05918 0.05169 -0.0362 0.0661 1.0000
10.500 1.3079 0.06479 0.05788 -0.0323 0.0709 1.0000
11.000 1.2933 0.08244 0.07642 -0.0286 0.0926 1.0000
11.250 1.2565 0.08403 0.07827 -0.0236 0.0929 1.0000
11.500 1.2227 0.08701 0.08146 -0.0211 0.0931 1.0000
11.750 1.1887 0.09112 0.08574 -0.0204 0.0933 1.0000
12.000 1.1548 0.09634 0.09112 -0.0213 0.0933 1.0000
12.250 1.1209 0.10262 0.09753 -0.0237 0.0933 1.0000
12.500 1.0875 0.10992 0.10493 -0.0275 0.0933 1.0000
12.750 1.0471 0.11953 0.11462 -0.0337 0.0933 1.0000
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Polar data table (+)
Polar graphs
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