EPPLER 1098 AIRFOIL (e1098-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 1098 AIRFOIL (e1098-il) Reynolds number: 500,000 Max Cl/Cd: 117.3 at α=8.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e1098-il-500000.txt Download as CSV file: xf-e1098-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 1098 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.500 -0.4029 0.05207 0.04767 -0.1330 0.7458 0.0164
-12.250 -0.4207 0.04807 0.04351 -0.1334 0.7418 0.0160
-12.000 -0.4366 0.04457 0.03983 -0.1333 0.7377 0.0159
-11.750 -0.4489 0.04132 0.03640 -0.1327 0.7338 0.0154
-11.500 -0.4692 0.03697 0.03166 -0.1312 0.7304 0.0145
-11.250 -0.4829 0.03300 0.02724 -0.1292 0.7272 0.0140
-11.000 -0.4789 0.03081 0.02481 -0.1279 0.7239 0.0138
-10.750 -0.4689 0.02929 0.02316 -0.1270 0.7205 0.0139
-10.500 -0.4568 0.02841 0.02223 -0.1262 0.7175 0.0144
-10.250 -0.4432 0.02715 0.02081 -0.1253 0.7147 0.0145
-10.000 -0.4286 0.02608 0.01963 -0.1244 0.7121 0.0149
-9.750 -0.4126 0.02503 0.01848 -0.1236 0.7097 0.0153
-9.500 -0.3928 0.02392 0.01725 -0.1229 0.7073 0.0155
-9.250 -0.3728 0.02293 0.01617 -0.1221 0.7051 0.0159
-9.000 -0.3534 0.02208 0.01522 -0.1213 0.7029 0.0161
-8.750 -0.3356 0.02133 0.01438 -0.1203 0.7009 0.0165
-8.500 -0.3191 0.02069 0.01365 -0.1192 0.6989 0.0168
-8.250 -0.3045 0.02002 0.01291 -0.1178 0.6971 0.0170
-8.000 -0.2991 0.01893 0.01182 -0.1152 0.6953 0.0175
-7.750 -0.2876 0.01813 0.01101 -0.1137 0.6934 0.0181
-7.500 -0.2723 0.01749 0.01035 -0.1126 0.6916 0.0188
-7.250 -0.2546 0.01695 0.00977 -0.1118 0.6897 0.0196
-7.000 -0.2350 0.01646 0.00924 -0.1111 0.6879 0.0207
-6.750 -0.2131 0.01609 0.00879 -0.1107 0.6863 0.0219
-6.500 -0.1970 0.01522 0.00788 -0.1098 0.6847 0.0239
-6.250 -0.1742 0.01481 0.00741 -0.1096 0.6832 0.0262
-6.000 -0.1519 0.01428 0.00683 -0.1094 0.6819 0.0304
-5.750 -0.1284 0.01378 0.00635 -0.1092 0.6806 0.0387
-5.500 -0.1067 0.01301 0.00580 -0.1091 0.6792 0.0815
-5.250 -0.0885 0.01157 0.00504 -0.1093 0.6779 0.2310
-5.000 -0.0682 0.01015 0.00446 -0.1097 0.6765 0.4345
-4.750 -0.0393 0.01018 0.00454 -0.1101 0.6752 0.4840
-4.500 -0.0100 0.01032 0.00465 -0.1105 0.6739 0.5054
-4.250 0.0195 0.01050 0.00477 -0.1109 0.6727 0.5203
-4.000 0.0490 0.01066 0.00484 -0.1113 0.6715 0.5309
-3.750 0.0785 0.01091 0.00504 -0.1116 0.6703 0.5424
-3.500 0.1076 0.01124 0.00539 -0.1118 0.6690 0.5549
-3.250 0.1369 0.01147 0.00556 -0.1121 0.6678 0.5626
-3.000 0.1658 0.01160 0.00570 -0.1125 0.6668 0.5671
-2.750 0.1947 0.01166 0.00572 -0.1129 0.6659 0.5708
-2.500 0.2239 0.01171 0.00571 -0.1134 0.6648 0.5739
-2.250 0.2528 0.01171 0.00568 -0.1139 0.6638 0.5763
-2.000 0.2816 0.01170 0.00567 -0.1143 0.6626 0.5783
-1.750 0.3105 0.01172 0.00569 -0.1147 0.6615 0.5801
-1.500 0.3395 0.01174 0.00569 -0.1152 0.6602 0.5820
-1.250 0.3687 0.01176 0.00569 -0.1157 0.6589 0.5839
-1.000 0.3980 0.01179 0.00568 -0.1162 0.6578 0.5856
-0.750 0.4274 0.01183 0.00569 -0.1168 0.6568 0.5875
-0.500 0.4569 0.01188 0.00570 -0.1175 0.6559 0.5893
-0.250 0.4866 0.01194 0.00571 -0.1181 0.6549 0.5907
0.000 0.5161 0.01197 0.00572 -0.1187 0.6538 0.5922
0.250 0.5453 0.01208 0.00582 -0.1193 0.6526 0.5938
0.500 0.5737 0.01216 0.00594 -0.1197 0.6516 0.5955
0.750 0.6018 0.01221 0.00602 -0.1200 0.6505 0.5971
1.000 0.6299 0.01226 0.00611 -0.1204 0.6491 0.5987
1.250 0.6580 0.01233 0.00620 -0.1207 0.6476 0.6004
1.500 0.6864 0.01239 0.00628 -0.1211 0.6461 0.6022
1.750 0.7149 0.01245 0.00635 -0.1216 0.6445 0.6040
2.000 0.7438 0.01250 0.00639 -0.1221 0.6429 0.6058
2.250 0.7729 0.01251 0.00641 -0.1226 0.6413 0.6077
2.500 0.8023 0.01253 0.00646 -0.1231 0.6398 0.6096
2.750 0.8322 0.01262 0.00654 -0.1238 0.6382 0.6114
3.000 0.8601 0.01272 0.00669 -0.1241 0.6362 0.6133
3.250 0.8865 0.01272 0.00676 -0.1241 0.6335 0.6154
3.500 0.9138 0.01270 0.00678 -0.1242 0.6305 0.6176
3.750 0.9424 0.01263 0.00672 -0.1246 0.6275 0.6198
4.000 0.9728 0.01256 0.00662 -0.1252 0.6248 0.6220
4.250 1.0036 0.01259 0.00665 -0.1260 0.6223 0.6243
4.500 1.0284 0.01259 0.00677 -0.1257 0.6196 0.6266
4.750 1.0544 0.01261 0.00687 -0.1256 0.6166 0.6293
5.000 1.0818 0.01259 0.00692 -0.1258 0.6137 0.6322
5.250 1.1107 0.01256 0.00691 -0.1262 0.6110 0.6352
5.500 1.1411 0.01255 0.00688 -0.1269 0.6085 0.6380
5.750 1.1674 0.01256 0.00700 -0.1269 0.6055 0.6408
6.000 1.1913 0.01255 0.00711 -0.1264 0.6016 0.6438
6.250 1.2181 0.01247 0.00710 -0.1264 0.5977 0.6472
6.500 1.2476 0.01233 0.00695 -0.1268 0.5934 0.6510
6.750 1.2695 0.01227 0.00700 -0.1259 0.5874 0.6546
7.000 1.2939 0.01213 0.00695 -0.1253 0.5815 0.6583
7.250 1.3193 0.01206 0.00693 -0.1250 0.5762 0.6628
7.500 1.3399 0.01205 0.00704 -0.1239 0.5691 0.6677
7.750 1.3631 0.01197 0.00702 -0.1231 0.5621 0.6723
8.000 1.3820 0.01198 0.00717 -0.1217 0.5526 0.6774
8.250 1.4007 0.01201 0.00728 -0.1201 0.5411 0.6832
8.500 1.4146 0.01206 0.00738 -0.1177 0.5234 0.6887
8.750 1.4192 0.01226 0.00755 -0.1134 0.4998 0.6951
9.000 1.4116 0.01291 0.00806 -0.1072 0.4672 0.7019
9.250 1.4044 0.01380 0.00886 -0.1016 0.4405 0.7092
9.500 1.3844 0.01534 0.01023 -0.0945 0.4063 0.7175
9.750 1.3724 0.01691 0.01174 -0.0894 0.3806 0.7269
10.000 1.3584 0.01886 0.01361 -0.0846 0.3550 0.7376
10.250 1.3468 0.02095 0.01565 -0.0806 0.3306 0.7503
10.500 1.3392 0.02297 0.01765 -0.0773 0.3097 0.7659
10.750 1.3315 0.02509 0.01977 -0.0742 0.2877 0.7856
11.000 1.3267 0.02706 0.02177 -0.0715 0.2698 0.8138
11.250 1.3210 0.02879 0.02363 -0.0683 0.2535 0.8771
11.500 1.3223 0.03071 0.02558 -0.0670 0.2335 1.0000
11.750 1.3221 0.03279 0.02757 -0.0653 0.2149 1.0000
12.000 1.3218 0.03493 0.02961 -0.0638 0.1968 1.0000
12.250 1.3226 0.03705 0.03164 -0.0624 0.1770 1.0000
12.500 1.3238 0.03920 0.03368 -0.0611 0.1582 1.0000
12.750 1.3266 0.04124 0.03565 -0.0600 0.1422 1.0000
13.250 1.3328 0.04546 0.03971 -0.0581 0.1128 1.0000
13.500 1.3363 0.04761 0.04180 -0.0573 0.1000 1.0000
13.750 1.3410 0.04968 0.04382 -0.0566 0.0884 1.0000
14.000 1.3462 0.05175 0.04588 -0.0560 0.0782 1.0000
14.250 1.3503 0.05397 0.04806 -0.0554 0.0671 1.0000
14.500 1.3537 0.05632 0.05036 -0.0549 0.0561 1.0000
14.750 1.3537 0.05905 0.05301 -0.0543 0.0435 1.0000
15.000 1.3519 0.06205 0.05592 -0.0538 0.0301 1.0000
15.250 1.3421 0.06604 0.05979 -0.0531 0.0166 1.0000
15.500 1.3422 0.06907 0.06285 -0.0529 0.0133 1.0000
15.750 1.3443 0.07190 0.06574 -0.0528 0.0115 1.0000
16.000 1.3449 0.07500 0.06890 -0.0528 0.0104 1.0000
16.250 1.3446 0.07828 0.07226 -0.0529 0.0097 1.0000
16.500 1.3473 0.08125 0.07533 -0.0531 0.0092 1.0000
16.750 1.3492 0.08436 0.07853 -0.0535 0.0089 1.0000
17.000 1.3491 0.08779 0.08206 -0.0539 0.0084 1.0000
17.250 1.3488 0.09131 0.08566 -0.0545 0.0081 1.0000
17.500 1.3462 0.09524 0.08968 -0.0553 0.0077 1.0000
17.750 1.3407 0.09967 0.09421 -0.0562 0.0075 1.0000
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Polar data table (+)
Polar graphs
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