EPPLER 397 AIRFOIL (e397-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: EPPLER 397 AIRFOIL (e397-il) Reynolds number: 100,000 Max Cl/Cd: 50.95 at α=9° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e397-il-100000.txt Download as CSV file: xf-e397-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 397 AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-8.750 -0.2679 0.10847 0.10419 -0.0605 0.9684 0.1247
-8.500 -0.2682 0.10541 0.10115 -0.0636 0.9618 0.1304
-8.250 -0.3559 0.08388 0.07982 -0.0786 0.9505 0.0657
-8.000 -0.2953 0.09025 0.08605 -0.0738 0.9485 0.0873
-7.750 -0.4173 0.06057 0.05621 -0.0998 0.9330 0.0556
-7.500 -0.3957 0.05655 0.05203 -0.1049 0.9293 0.0578
-7.250 -0.4021 0.05184 0.04697 -0.1069 0.9214 0.0588
-7.000 -0.3814 0.04549 0.03985 -0.1136 0.9173 0.0621
-6.750 -0.3466 0.04019 0.03373 -0.1196 0.9148 0.0681
-6.500 -0.3323 0.03912 0.03246 -0.1188 0.9090 0.0745
-6.250 -0.3036 0.03707 0.03012 -0.1207 0.9048 0.0832
-6.000 -0.2676 0.03528 0.02799 -0.1235 0.9017 0.0952
-5.750 -0.2276 0.03392 0.02637 -0.1266 0.8994 0.1094
-5.500 -0.2142 0.03335 0.02548 -0.1250 0.8934 0.1194
-5.250 -0.1841 0.03262 0.02463 -0.1261 0.8892 0.1340
-5.000 -0.1481 0.03191 0.02393 -0.1282 0.8861 0.1512
-4.750 -0.1155 0.03153 0.02351 -0.1296 0.8830 0.1696
-4.500 -0.1015 0.03145 0.02338 -0.1280 0.8770 0.1837
-4.250 -0.0696 0.03120 0.02302 -0.1292 0.8730 0.2062
-4.000 -0.0326 0.03096 0.02282 -0.1312 0.8702 0.2304
-3.750 -0.0141 0.03114 0.02297 -0.1303 0.8652 0.2501
-3.500 0.0083 0.03124 0.02302 -0.1299 0.8601 0.2719
-3.250 0.0419 0.03124 0.02305 -0.1312 0.8565 0.2982
-3.000 0.0808 0.03122 0.02304 -0.1333 0.8540 0.3265
-2.750 0.0858 0.03178 0.02361 -0.1304 0.8471 0.3423
-2.500 0.1147 0.03192 0.02374 -0.1309 0.8428 0.3679
-2.250 0.1516 0.03198 0.02377 -0.1327 0.8398 0.3970
-2.000 0.1651 0.03251 0.02436 -0.1309 0.8342 0.4160
-1.750 0.1865 0.03285 0.02474 -0.1304 0.8289 0.4389
-1.500 0.2203 0.03298 0.02490 -0.1315 0.8255 0.4670
-1.250 0.2499 0.03326 0.02520 -0.1321 0.8218 0.4944
-1.000 0.2569 0.03397 0.02598 -0.1295 0.8147 0.5136
-0.750 0.2882 0.03416 0.02622 -0.1302 0.8109 0.5434
-0.500 0.3278 0.03418 0.02630 -0.1319 0.8083 0.5770
-0.250 0.3249 0.03524 0.02743 -0.1281 0.7998 0.5968
0.000 0.3549 0.03544 0.02772 -0.1284 0.7958 0.6316
0.250 0.3935 0.03540 0.02777 -0.1296 0.7931 0.6720
0.500 0.3888 0.03656 0.02904 -0.1256 0.7842 0.6993
0.750 0.4173 0.03665 0.02925 -0.1253 0.7802 0.7464
1.000 0.4391 0.03681 0.02957 -0.1238 0.7759 0.8013
1.250 0.4334 0.03743 0.03041 -0.1186 0.7677 0.8758
1.500 0.4783 0.03739 0.03027 -0.1220 0.7639 1.0000
1.750 0.4908 0.03864 0.03140 -0.1214 0.7556 1.0000
2.000 0.5246 0.03912 0.03175 -0.1230 0.7505 1.0000
2.250 0.5703 0.03918 0.03169 -0.1256 0.7476 1.0000
2.500 0.5694 0.04081 0.03327 -0.1231 0.7372 1.0000
2.750 0.6109 0.04088 0.03328 -0.1250 0.7335 1.0000
3.000 0.6166 0.04235 0.03472 -0.1231 0.7238 1.0000
3.250 0.6538 0.04251 0.03483 -0.1245 0.7192 1.0000
3.500 0.6976 0.04242 0.03472 -0.1264 0.7162 1.0000
3.750 0.6985 0.04403 0.03632 -0.1240 0.7048 1.0000
4.000 0.7447 0.04370 0.03598 -0.1260 0.7020 1.0000
4.250 0.7452 0.04539 0.03769 -0.1235 0.6901 1.0000
4.500 0.7917 0.04488 0.03719 -0.1254 0.6872 1.0000
4.750 0.7939 0.04655 0.03888 -0.1231 0.6752 1.0000
5.000 0.8406 0.04586 0.03823 -0.1248 0.6722 1.0000
5.250 0.8444 0.04748 0.03989 -0.1227 0.6600 1.0000
5.500 0.8921 0.04654 0.03901 -0.1243 0.6572 1.0000
5.750 0.8969 0.04810 0.04061 -0.1222 0.6448 1.0000
6.000 0.9465 0.04681 0.03941 -0.1237 0.6421 1.0000
6.250 0.9526 0.04824 0.04090 -0.1217 0.6295 1.0000
6.500 1.0045 0.04650 0.03926 -0.1231 0.6271 1.0000
6.750 1.0129 0.04772 0.04057 -0.1212 0.6145 1.0000
7.000 1.0337 0.04801 0.04094 -0.1202 0.6046 1.0000
7.250 1.0777 0.04635 0.03942 -0.1206 0.5997 1.0000
7.500 1.1362 0.04329 0.03653 -0.1218 0.5982 1.0000
7.750 1.2079 0.03893 0.03236 -0.1239 0.5977 1.0000
8.000 1.3162 0.03220 0.02587 -0.1303 0.5951 1.0000
8.250 1.3497 0.03075 0.02456 -0.1296 0.5823 1.0000
8.500 1.3732 0.03003 0.02395 -0.1279 0.5686 1.0000
8.750 1.4006 0.02914 0.02318 -0.1267 0.5538 1.0000
9.000 1.4317 0.02810 0.02223 -0.1259 0.5369 1.0000
9.250 1.4397 0.02830 0.02253 -0.1225 0.5179 1.0000
9.500 1.4486 0.02855 0.02284 -0.1193 0.4964 1.0000
9.750 1.4612 0.02872 0.02302 -0.1165 0.4719 1.0000
10.000 1.4699 0.02921 0.02345 -0.1135 0.4445 1.0000
10.250 1.4731 0.03017 0.02433 -0.1101 0.4152 1.0000
10.500 1.4734 0.03149 0.02553 -0.1067 0.3855 1.0000
10.750 1.4712 0.03313 0.02705 -0.1033 0.3555 1.0000
11.000 1.4664 0.03511 0.02890 -0.1000 0.3255 1.0000
11.250 1.4593 0.03741 0.03106 -0.0968 0.2959 1.0000
11.500 1.4505 0.04001 0.03352 -0.0939 0.2665 1.0000
11.750 1.4404 0.04292 0.03627 -0.0912 0.2375 1.0000
12.000 1.4294 0.04611 0.03929 -0.0888 0.2090 1.0000
12.250 1.4183 0.04955 0.04256 -0.0866 0.1815 1.0000
12.500 1.4088 0.05308 0.04590 -0.0848 0.1566 1.0000
12.750 1.4022 0.05648 0.04911 -0.0832 0.1372 1.0000
13.000 1.3996 0.05961 0.05206 -0.0819 0.1214 1.0000
13.250 1.4000 0.06252 0.05488 -0.0807 0.1082 1.0000
13.500 1.4009 0.06547 0.05786 -0.0798 0.0968 1.0000
13.750 1.4034 0.06838 0.06083 -0.0788 0.0863 1.0000
14.000 1.4064 0.07129 0.06377 -0.0779 0.0770 1.0000
14.250 1.4109 0.07407 0.06649 -0.0771 0.0690 1.0000
14.500 1.4131 0.07711 0.06959 -0.0766 0.0624 1.0000
14.750 1.4209 0.07984 0.07240 -0.0758 0.0561 1.0000
15.000 1.4416 0.08165 0.07404 -0.0746 0.0495 1.0000
15.250 1.4409 0.08532 0.07807 -0.0742 0.0465 1.0000
15.500 1.4445 0.08853 0.08139 -0.0739 0.0431 1.0000
15.750 1.4643 0.09173 0.08469 -0.0730 0.0398 1.0000
16.000 1.4551 0.09634 0.08968 -0.0731 0.0388 1.0000
16.250 1.4450 0.10122 0.09490 -0.0737 0.0379 1.0000
16.500 1.4341 0.10632 0.10030 -0.0747 0.0369 1.0000
16.750 1.4229 0.11154 0.10579 -0.0760 0.0361 1.0000
17.000 1.4127 0.11674 0.11122 -0.0777 0.0352 1.0000
17.250 1.4092 0.12101 0.11559 -0.0791 0.0340 1.0000
17.500 1.4009 0.12615 0.12088 -0.0811 0.0332 1.0000
17.750 1.3878 0.13228 0.12722 -0.0839 0.0329 1.0000
18.000 1.3610 0.14098 0.13628 -0.0890 0.0335 1.0000
18.250 1.2960 0.15940 0.15529 -0.1016 0.0374 1.0000
18.500 1.2691 0.17091 0.16696 -0.1096 0.0387 1.0000
18.750 1.2471 0.18207 0.17821 -0.1172 0.0397 1.0000
19.000 1.2316 0.19228 0.18845 -0.1237 0.0404 1.0000
|
Polar data table (+)
Polar graphs
<< Back to EPPLER 397 AIRFOIL (e397-il)