EPPLER 1098 AIRFOIL (e1098-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 1098 AIRFOIL (e1098-il) Reynolds number: 500,000 Max Cl/Cd: 112.47 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e1098-il-500000-n5.txt Download as CSV file: xf-e1098-il-500000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.500 -0.4326 0.09710 0.09333 -0.1021 0.7813 0.0069
-16.250 -0.4722 0.08510 0.08112 -0.1087 0.7776 0.0068
-16.000 -0.4949 0.07723 0.07304 -0.1132 0.7714 0.0068
-15.750 -0.5051 0.07195 0.06759 -0.1162 0.7639 0.0068
-15.500 -0.5241 0.06578 0.06121 -0.1193 0.7579 0.0068
-15.250 -0.5343 0.06121 0.05648 -0.1215 0.7515 0.0068
-15.000 -0.5452 0.05688 0.05196 -0.1232 0.7454 0.0068
-14.750 -0.5499 0.05348 0.04837 -0.1245 0.7395 0.0069
-14.500 -0.5519 0.05061 0.04534 -0.1254 0.7338 0.0070
-14.250 -0.5534 0.04793 0.04250 -0.1261 0.7282 0.0070
-14.000 -0.5564 0.04513 0.03954 -0.1265 0.7234 0.0070
-13.750 -0.5572 0.04271 0.03697 -0.1267 0.7185 0.0071
-13.500 -0.5584 0.04039 0.03452 -0.1266 0.7142 0.0073
-13.250 -0.5560 0.03837 0.03235 -0.1264 0.7104 0.0072
-13.000 -0.5494 0.03687 0.03081 -0.1264 0.7064 0.0075
-12.750 -0.5439 0.03523 0.02905 -0.1260 0.7027 0.0075
-12.500 -0.5354 0.03395 0.02769 -0.1258 0.6992 0.0077
-12.250 -0.5262 0.03271 0.02639 -0.1255 0.6962 0.0079
-12.000 -0.5160 0.03155 0.02516 -0.1252 0.6930 0.0081
-11.750 -0.5068 0.03028 0.02379 -0.1246 0.6900 0.0081
-11.500 -0.4966 0.02913 0.02255 -0.1239 0.6871 0.0083
-11.250 -0.4855 0.02809 0.02142 -0.1233 0.6844 0.0086
-11.000 -0.4744 0.02706 0.02030 -0.1225 0.6820 0.0087
-10.750 -0.4631 0.02602 0.01920 -0.1218 0.6797 0.0088
-10.500 -0.4511 0.02507 0.01817 -0.1210 0.6773 0.0091
-10.250 -0.4401 0.02408 0.01711 -0.1200 0.6749 0.0092
-10.000 -0.4284 0.02317 0.01613 -0.1191 0.6724 0.0093
-9.750 -0.4169 0.02227 0.01515 -0.1181 0.6702 0.0095
-9.500 -0.4052 0.02143 0.01423 -0.1171 0.6681 0.0097
-9.250 -0.3970 0.02039 0.01315 -0.1158 0.6662 0.0100
-9.000 -0.3880 0.01946 0.01219 -0.1144 0.6644 0.0102
-8.750 -0.3801 0.01867 0.01137 -0.1127 0.6625 0.0104
-8.500 -0.3718 0.01802 0.01068 -0.1109 0.6606 0.0107
-8.250 -0.3567 0.01745 0.01005 -0.1099 0.6589 0.0110
-8.000 -0.3394 0.01694 0.00949 -0.1091 0.6573 0.0114
-7.750 -0.3207 0.01645 0.00894 -0.1084 0.6557 0.0119
-7.500 -0.3006 0.01601 0.00843 -0.1078 0.6543 0.0125
-7.250 -0.2794 0.01560 0.00796 -0.1074 0.6529 0.0133
-7.000 -0.2577 0.01516 0.00750 -0.1070 0.6516 0.0143
-6.750 -0.2344 0.01479 0.00711 -0.1069 0.6503 0.0154
-6.500 -0.2104 0.01444 0.00671 -0.1067 0.6490 0.0167
-6.250 -0.1865 0.01405 0.00631 -0.1066 0.6476 0.0186
-6.000 -0.1614 0.01375 0.00597 -0.1067 0.6461 0.0213
-5.750 -0.1363 0.01342 0.00563 -0.1067 0.6447 0.0252
-5.500 -0.1107 0.01311 0.00532 -0.1068 0.6433 0.0319
-5.250 -0.0853 0.01273 0.00500 -0.1070 0.6420 0.0482
-5.000 -0.0602 0.01226 0.00466 -0.1072 0.6409 0.0829
-4.750 -0.0354 0.01167 0.00428 -0.1075 0.6398 0.1416
-4.500 -0.0118 0.01074 0.00377 -0.1080 0.6387 0.2537
-4.250 0.0120 0.00963 0.00328 -0.1088 0.6376 0.4187
-4.000 0.0407 0.00956 0.00333 -0.1092 0.6367 0.4716
-3.750 0.0700 0.00960 0.00336 -0.1097 0.6357 0.4946
-3.500 0.0994 0.00971 0.00345 -0.1101 0.6347 0.5145
-3.250 0.1287 0.00981 0.00353 -0.1105 0.6337 0.5259
-3.000 0.1579 0.00984 0.00352 -0.1109 0.6326 0.5312
-2.750 0.1872 0.00987 0.00353 -0.1113 0.6316 0.5349
-2.500 0.2164 0.00989 0.00351 -0.1118 0.6304 0.5380
-2.250 0.2458 0.00991 0.00347 -0.1123 0.6292 0.5406
-2.000 0.2751 0.00992 0.00343 -0.1128 0.6281 0.5425
-1.750 0.3045 0.00994 0.00339 -0.1133 0.6271 0.5441
-1.500 0.3337 0.00993 0.00337 -0.1138 0.6262 0.5456
-1.250 0.3629 0.00994 0.00336 -0.1142 0.6252 0.5469
-1.000 0.3922 0.00996 0.00336 -0.1147 0.6244 0.5482
-0.750 0.4216 0.01000 0.00337 -0.1152 0.6235 0.5497
-0.500 0.4511 0.01005 0.00339 -0.1158 0.6226 0.5514
-0.250 0.4803 0.01009 0.00342 -0.1163 0.6217 0.5529
0.000 0.5092 0.01011 0.00345 -0.1167 0.6207 0.5544
0.250 0.5381 0.01014 0.00348 -0.1172 0.6196 0.5559
0.500 0.5670 0.01018 0.00352 -0.1176 0.6186 0.5573
0.750 0.5960 0.01023 0.00357 -0.1181 0.6176 0.5587
1.000 0.6248 0.01027 0.00362 -0.1185 0.6165 0.5602
1.250 0.6535 0.01030 0.00368 -0.1189 0.6152 0.5618
1.500 0.6823 0.01034 0.00375 -0.1194 0.6140 0.5634
1.750 0.7110 0.01038 0.00381 -0.1198 0.6128 0.5649
2.000 0.7398 0.01042 0.00387 -0.1202 0.6114 0.5665
2.250 0.7686 0.01046 0.00392 -0.1206 0.6100 0.5682
2.500 0.7975 0.01052 0.00398 -0.1211 0.6085 0.5699
2.750 0.8263 0.01059 0.00406 -0.1215 0.6067 0.5716
3.000 0.8536 0.01062 0.00415 -0.1217 0.6046 0.5734
3.250 0.8810 0.01065 0.00422 -0.1218 0.6019 0.5750
3.500 0.9083 0.01065 0.00427 -0.1220 0.5988 0.5768
3.750 0.9358 0.01063 0.00429 -0.1221 0.5954 0.5787
4.000 0.9641 0.01067 0.00431 -0.1224 0.5923 0.5809
4.250 0.9900 0.01069 0.00443 -0.1223 0.5888 0.5831
4.500 1.0167 0.01072 0.00453 -0.1223 0.5855 0.5853
4.750 1.0436 0.01076 0.00461 -0.1224 0.5824 0.5876
5.000 1.0708 0.01080 0.00468 -0.1225 0.5794 0.5898
5.250 1.0976 0.01085 0.00478 -0.1226 0.5764 0.5919
5.500 1.1233 0.01090 0.00494 -0.1224 0.5725 0.5941
5.750 1.1491 0.01094 0.00507 -0.1223 0.5682 0.5966
6.000 1.1748 0.01098 0.00515 -0.1221 0.5640 0.5993
6.250 1.1998 0.01105 0.00530 -0.1218 0.5586 0.6021
6.500 1.2234 0.01110 0.00540 -0.1213 0.5508 0.6050
6.750 1.2456 0.01116 0.00553 -0.1204 0.5394 0.6080
7.000 1.2653 0.01125 0.00564 -0.1191 0.5233 0.6113
7.250 1.2804 0.01145 0.00581 -0.1169 0.5006 0.6148
7.500 1.2852 0.01184 0.00609 -0.1128 0.4731 0.6183
7.750 1.2829 0.01249 0.00661 -0.1075 0.4455 0.6216
8.000 1.2795 0.01334 0.00735 -0.1024 0.4186 0.6249
8.250 1.2768 0.01428 0.00823 -0.0978 0.3941 0.6286
8.500 1.2725 0.01541 0.00929 -0.0933 0.3719 0.6327
8.750 1.2704 0.01662 0.01045 -0.0895 0.3517 0.6368
9.000 1.2673 0.01804 0.01183 -0.0860 0.3321 0.6410
9.250 1.2654 0.01956 0.01333 -0.0828 0.3144 0.6457
9.500 1.2608 0.02139 0.01509 -0.0797 0.2928 0.6507
9.750 1.2611 0.02302 0.01670 -0.0773 0.2765 0.6558
10.000 1.2565 0.02505 0.01865 -0.0746 0.2552 0.6615
10.500 1.2580 0.02858 0.02213 -0.0705 0.2215 0.6747
10.750 1.2572 0.03053 0.02402 -0.0685 0.2012 0.6819
11.000 1.2560 0.03257 0.02597 -0.0666 0.1807 0.6894
11.250 1.2570 0.03451 0.02785 -0.0650 0.1602 0.6980
11.500 1.2605 0.03632 0.02963 -0.0636 0.1442 0.7072
11.750 1.2659 0.03802 0.03132 -0.0625 0.1306 0.7175
12.000 1.2689 0.03997 0.03323 -0.0612 0.1149 0.7291
12.250 1.2724 0.04190 0.03513 -0.0601 0.0996 0.7424
12.500 1.2769 0.04380 0.03704 -0.0591 0.0866 0.7581
13.000 1.2865 0.04755 0.04085 -0.0572 0.0639 0.8052
13.250 1.2912 0.04915 0.04261 -0.0558 0.0555 0.8669
13.750 1.3022 0.05329 0.04678 -0.0550 0.0363 1.0000
14.000 1.3084 0.05535 0.04882 -0.0546 0.0298 1.0000
14.250 1.3123 0.05770 0.05116 -0.0541 0.0231 1.0000
14.500 1.3174 0.05996 0.05343 -0.0537 0.0182 1.0000
14.750 1.3217 0.06236 0.05584 -0.0534 0.0138 1.0000
15.000 1.3264 0.06477 0.05827 -0.0532 0.0107 1.0000
15.250 1.3293 0.06742 0.06095 -0.0530 0.0078 1.0000
15.500 1.3348 0.06983 0.06341 -0.0530 0.0070 1.0000
15.750 1.3403 0.07226 0.06590 -0.0530 0.0063 1.0000
16.000 1.3440 0.07498 0.06868 -0.0530 0.0057 1.0000
16.250 1.3480 0.07769 0.07146 -0.0532 0.0053 1.0000
16.500 1.3524 0.08041 0.07427 -0.0534 0.0051 1.0000
16.750 1.3567 0.08316 0.07710 -0.0537 0.0049 1.0000
17.000 1.3590 0.08624 0.08028 -0.0541 0.0046 1.0000
17.250 1.3619 0.08925 0.08338 -0.0546 0.0044 1.0000
17.500 1.3636 0.09250 0.08671 -0.0552 0.0043 1.0000
17.750 1.3644 0.09592 0.09023 -0.0559 0.0041 1.0000
18.000 1.3644 0.09951 0.09391 -0.0567 0.0040 1.0000
18.250 1.3627 0.10338 0.09787 -0.0577 0.0038 1.0000
18.500 1.3611 0.10728 0.10188 -0.0588 0.0038 1.0000
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