E392 (10.15%) (e392-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: E392 (10.15%) (e392-il) Reynolds number: 1,000,000 Max Cl/Cd: 146.6 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e392-il-1000000.txt Download as CSV file: xf-e392-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: E392 (10.15%)
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
------ -------- --------- --------- -------- -------- --------
-9.000 -0.3314 0.09107 0.08950 -0.0375 1.0000 0.0098
-8.750 -0.3303 0.08793 0.08638 -0.0383 1.0000 0.0101
-8.500 -0.3309 0.08479 0.08328 -0.0390 1.0000 0.0102
-8.250 -0.3278 0.08095 0.07946 -0.0413 0.9992 0.0106
-8.000 -0.3158 0.07542 0.07394 -0.0475 0.9882 0.0111
-7.750 -0.2984 0.06894 0.06746 -0.0565 0.9749 0.0114
-7.500 -0.2655 0.05976 0.05824 -0.0732 0.9557 0.0117
-7.000 -0.2436 0.04014 0.03799 -0.0946 0.8682 0.0118
-6.750 -0.2544 0.03001 0.02719 -0.0982 0.8402 0.0123
-6.500 -0.2376 0.02741 0.02435 -0.0986 0.8215 0.0125
-6.250 -0.2263 0.01841 0.01420 -0.0985 0.8060 0.0087
-6.000 -0.2028 0.01637 0.01186 -0.0983 0.7918 0.0083
-5.750 -0.1779 0.01485 0.01000 -0.0981 0.7786 0.0084
-5.500 -0.1536 0.01270 0.00745 -0.0978 0.7665 0.0089
-5.250 -0.1276 0.01175 0.00635 -0.0977 0.7549 0.0092
-5.000 -0.1007 0.01119 0.00569 -0.0976 0.7441 0.0096
-4.750 -0.0737 0.01064 0.00503 -0.0975 0.7342 0.0099
-4.250 -0.0190 0.00973 0.00391 -0.0974 0.7157 0.0105
-4.000 0.0087 0.00942 0.00351 -0.0974 0.7074 0.0112
-3.750 0.0366 0.00910 0.00312 -0.0974 0.6993 0.0116
-3.500 0.0645 0.00872 0.00262 -0.0974 0.6921 0.0121
-3.250 0.0926 0.00835 0.00217 -0.0974 0.6846 0.0138
-3.000 0.1208 0.00817 0.00193 -0.0974 0.6779 0.0159
-2.750 0.1490 0.00783 0.00165 -0.0975 0.6713 0.0350
-2.500 0.1770 0.00760 0.00150 -0.0976 0.6650 0.0696
-2.250 0.2053 0.00738 0.00140 -0.0978 0.6587 0.1078
-2.000 0.2333 0.00719 0.00131 -0.0980 0.6528 0.1561
-1.750 0.2614 0.00692 0.00123 -0.0982 0.6472 0.2254
-1.500 0.2893 0.00656 0.00118 -0.0985 0.6413 0.3369
-1.250 0.3172 0.00635 0.00116 -0.0987 0.6359 0.4197
-1.000 0.3455 0.00618 0.00115 -0.0988 0.6305 0.4871
-0.750 0.3735 0.00608 0.00115 -0.0989 0.6250 0.5405
-0.500 0.4016 0.00597 0.00117 -0.0990 0.6199 0.5971
-0.250 0.4297 0.00588 0.00118 -0.0991 0.6145 0.6421
0.000 0.4574 0.00583 0.00121 -0.0990 0.6092 0.6886
0.250 0.4852 0.00574 0.00124 -0.0990 0.6042 0.7374
0.500 0.5123 0.00565 0.00128 -0.0987 0.5989 0.7908
0.750 0.5379 0.00558 0.00133 -0.0981 0.5937 0.8478
1.000 0.5610 0.00545 0.00137 -0.0969 0.5888 0.9129
1.250 0.5922 0.00536 0.00134 -0.0974 0.5831 1.0000
1.500 0.6204 0.00545 0.00137 -0.0975 0.5776 1.0000
1.750 0.6490 0.00550 0.00140 -0.0977 0.5714 1.0000
2.250 0.7054 0.00564 0.00148 -0.0979 0.5577 1.0000
2.500 0.7334 0.00574 0.00154 -0.0979 0.5507 1.0000
2.750 0.7617 0.00580 0.00160 -0.0980 0.5438 1.0000
3.000 0.7895 0.00591 0.00166 -0.0981 0.5363 1.0000
3.250 0.8176 0.00597 0.00173 -0.0982 0.5286 1.0000
3.500 0.8452 0.00609 0.00181 -0.0982 0.5203 1.0000
3.750 0.8732 0.00617 0.00189 -0.0982 0.5116 1.0000
4.000 0.9009 0.00628 0.00199 -0.0982 0.5029 1.0000
4.250 0.9283 0.00641 0.00209 -0.0982 0.4932 1.0000
4.500 0.9558 0.00652 0.00221 -0.0982 0.4822 1.0000
5.000 1.0088 0.00692 0.00247 -0.0979 0.4399 1.0000
5.250 1.0349 0.00717 0.00265 -0.0977 0.4172 1.0000
5.500 1.0595 0.00755 0.00287 -0.0973 0.3802 1.0000
5.750 1.0828 0.00808 0.00319 -0.0967 0.3324 1.0000
6.000 1.1043 0.00878 0.00361 -0.0959 0.2759 1.0000
6.250 1.1254 0.00951 0.00408 -0.0951 0.2238 1.0000
6.500 1.1465 0.01022 0.00455 -0.0942 0.1771 1.0000
6.750 1.1670 0.01098 0.00507 -0.0933 0.1327 1.0000
7.000 1.1869 0.01175 0.00561 -0.0922 0.0932 1.0000
7.250 1.2061 0.01256 0.00621 -0.0911 0.0583 1.0000
7.500 1.2229 0.01356 0.00697 -0.0896 0.0237 1.0000
7.750 1.2428 0.01423 0.00759 -0.0884 0.0148 1.0000
8.000 1.2640 0.01478 0.00818 -0.0874 0.0128 1.0000
8.250 1.2856 0.01525 0.00870 -0.0866 0.0122 1.0000
8.500 1.3062 0.01579 0.00930 -0.0855 0.0116 1.0000
8.750 1.3256 0.01637 0.00993 -0.0844 0.0109 1.0000
9.000 1.3430 0.01708 0.01069 -0.0829 0.0101 1.0000
9.250 1.3566 0.01800 0.01171 -0.0808 0.0096 1.0000
9.500 1.3667 0.01900 0.01282 -0.0782 0.0092 1.0000
9.750 1.3787 0.01968 0.01356 -0.0758 0.0091 1.0000
10.000 1.3891 0.02044 0.01438 -0.0733 0.0089 1.0000
10.250 1.3976 0.02134 0.01537 -0.0707 0.0088 1.0000
10.500 1.4053 0.02235 0.01646 -0.0681 0.0085 1.0000
10.750 1.4126 0.02345 0.01763 -0.0658 0.0083 1.0000
11.000 1.4191 0.02467 0.01894 -0.0636 0.0081 1.0000
11.250 1.4266 0.02591 0.02025 -0.0617 0.0079 1.0000
11.500 1.4341 0.02722 0.02163 -0.0601 0.0076 1.0000
11.750 1.4390 0.02883 0.02332 -0.0584 0.0074 1.0000
12.000 1.4434 0.03058 0.02513 -0.0569 0.0072 1.0000
12.250 1.4451 0.03267 0.02730 -0.0554 0.0070 1.0000
12.500 1.4453 0.03503 0.02977 -0.0541 0.0068 1.0000
12.750 1.4377 0.03833 0.03318 -0.0526 0.0066 1.0000
13.000 1.4289 0.04203 0.03704 -0.0510 0.0064 1.0000
13.250 1.4347 0.04411 0.03921 -0.0505 0.0063 1.0000
13.500 1.4409 0.04617 0.04138 -0.0502 0.0062 1.0000
13.750 1.4445 0.04860 0.04390 -0.0499 0.0062 1.0000
14.000 1.4467 0.05127 0.04669 -0.0497 0.0060 1.0000
14.250 1.4493 0.05397 0.04950 -0.0497 0.0059 1.0000
14.500 1.4513 0.05679 0.05242 -0.0499 0.0057 1.0000
14.750 1.4509 0.06002 0.05577 -0.0501 0.0056 1.0000
15.000 1.4490 0.06361 0.05947 -0.0505 0.0055 1.0000
15.250 1.4486 0.06705 0.06302 -0.0513 0.0054 1.0000
15.500 1.4469 0.07078 0.06685 -0.0522 0.0052 1.0000
15.750 1.4443 0.07481 0.07100 -0.0533 0.0051 1.0000
16.000 1.4404 0.07915 0.07546 -0.0546 0.0050 1.0000
16.250 1.4354 0.08380 0.08024 -0.0562 0.0049 1.0000
16.500 1.4291 0.08880 0.08535 -0.0580 0.0049 1.0000
16.750 1.4233 0.09387 0.09054 -0.0601 0.0048 1.0000
17.000 1.4173 0.09914 0.09591 -0.0625 0.0047 1.0000
17.250 1.4099 0.10476 0.10164 -0.0651 0.0047 1.0000
17.500 1.4006 0.11086 0.10786 -0.0680 0.0046 1.0000
17.750 1.3910 0.11721 0.11433 -0.0712 0.0046 1.0000
18.000 1.3800 0.12399 0.12123 -0.0748 0.0045 1.0000
18.250 1.3682 0.13108 0.12846 -0.0787 0.0045 1.0000
18.500 1.3549 0.13871 0.13622 -0.0832 0.0044 1.0000
18.750 1.3411 0.14670 0.14435 -0.0880 0.0044 1.0000
19.000 1.3274 0.15492 0.15271 -0.0931 0.0044 1.0000
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Polar data table (+)
Polar graphs
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