EPPLER 1098 AIRFOIL (e1098-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 1098 AIRFOIL (e1098-il) Reynolds number: 1,000,000 Max Cl/Cd: 139.8 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e1098-il-1000000-n5.txt Download as CSV file: xf-e1098-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-18.500 -0.5284 0.11054 0.10727 -0.0940 0.7793 0.0047
-18.250 -0.5564 0.10097 0.09754 -0.0990 0.7743 0.0047
-18.000 -0.5712 0.09410 0.09055 -0.1028 0.7670 0.0047
-17.750 -0.6041 0.08453 0.08078 -0.1080 0.7621 0.0047
-17.500 -0.6127 0.07936 0.07549 -0.1109 0.7551 0.0047
-17.250 -0.6233 0.07408 0.07006 -0.1137 0.7480 0.0047
-17.000 -0.6412 0.06807 0.06388 -0.1168 0.7424 0.0047
-16.750 -0.6416 0.06466 0.06037 -0.1186 0.7358 0.0047
-16.500 -0.6449 0.06105 0.05664 -0.1203 0.7293 0.0047
-16.250 -0.6561 0.05664 0.05208 -0.1221 0.7244 0.0047
-16.000 -0.6654 0.05275 0.04804 -0.1235 0.7187 0.0048
-15.500 -0.6694 0.04699 0.04206 -0.1251 0.7088 0.0048
-15.250 -0.6717 0.04429 0.03924 -0.1257 0.7040 0.0049
-15.000 -0.6729 0.04181 0.03664 -0.1260 0.6993 0.0049
-14.750 -0.6735 0.03945 0.03420 -0.1261 0.6956 0.0051
-14.500 -0.6668 0.03781 0.03249 -0.1263 0.6919 0.0051
-14.250 -0.6608 0.03618 0.03078 -0.1262 0.6880 0.0052
-14.000 -0.6583 0.03439 0.02889 -0.1259 0.6843 0.0052
-13.750 -0.6495 0.03309 0.02753 -0.1257 0.6812 0.0053
-13.500 -0.6410 0.03178 0.02617 -0.1255 0.6782 0.0054
-13.250 -0.6369 0.03019 0.02449 -0.1249 0.6753 0.0054
-13.000 -0.6259 0.02913 0.02338 -0.1246 0.6721 0.0055
-12.750 -0.6174 0.02793 0.02211 -0.1240 0.6693 0.0056
-12.500 -0.6070 0.02687 0.02099 -0.1235 0.6668 0.0056
-12.250 -0.5958 0.02585 0.01993 -0.1230 0.6646 0.0058
-12.000 -0.5847 0.02486 0.01889 -0.1224 0.6622 0.0059
-11.750 -0.5759 0.02374 0.01771 -0.1215 0.6599 0.0059
-11.500 -0.5645 0.02281 0.01672 -0.1208 0.6575 0.0060
-11.250 -0.5523 0.02194 0.01580 -0.1201 0.6551 0.0062
-10.750 -0.5288 0.02021 0.01396 -0.1184 0.6508 0.0064
-10.500 -0.5132 0.01957 0.01329 -0.1178 0.6491 0.0067
-10.250 -0.5027 0.01867 0.01234 -0.1167 0.6472 0.0067
-10.000 -0.4900 0.01793 0.01155 -0.1157 0.6454 0.0068
-9.750 -0.4786 0.01720 0.01078 -0.1144 0.6436 0.0069
-9.500 -0.4714 0.01652 0.01005 -0.1124 0.6418 0.0070
-9.250 -0.4619 0.01591 0.00938 -0.1107 0.6401 0.0071
-9.000 -0.4475 0.01530 0.00871 -0.1094 0.6385 0.0073
-8.750 -0.4295 0.01481 0.00817 -0.1086 0.6370 0.0076
-8.500 -0.4092 0.01437 0.00770 -0.1081 0.6359 0.0078
-8.250 -0.3874 0.01398 0.00729 -0.1077 0.6347 0.0080
-8.000 -0.3646 0.01362 0.00691 -0.1074 0.6335 0.0083
-7.750 -0.3412 0.01328 0.00653 -0.1072 0.6322 0.0087
-7.500 -0.3171 0.01296 0.00618 -0.1070 0.6309 0.0090
-7.250 -0.2923 0.01268 0.00587 -0.1070 0.6297 0.0094
-7.000 -0.2670 0.01241 0.00557 -0.1070 0.6284 0.0097
-6.750 -0.2420 0.01210 0.00523 -0.1070 0.6271 0.0106
-6.500 -0.2162 0.01184 0.00496 -0.1070 0.6257 0.0116
-6.250 -0.1898 0.01163 0.00472 -0.1072 0.6244 0.0128
-6.000 -0.1636 0.01139 0.00447 -0.1073 0.6231 0.0149
-5.750 -0.1366 0.01120 0.00426 -0.1075 0.6220 0.0171
-5.500 -0.1094 0.01096 0.00404 -0.1078 0.6212 0.0206
-5.250 -0.0820 0.01075 0.00383 -0.1081 0.6204 0.0249
-5.000 -0.0545 0.01053 0.00363 -0.1084 0.6195 0.0320
-4.750 -0.0272 0.01024 0.00342 -0.1088 0.6186 0.0485
-4.500 -0.0001 0.00989 0.00319 -0.1092 0.6177 0.0806
-4.250 0.0265 0.00941 0.00292 -0.1096 0.6167 0.1373
-4.000 0.0531 0.00883 0.00262 -0.1102 0.6158 0.2153
-3.750 0.0793 0.00802 0.00223 -0.1109 0.6148 0.3359
-3.500 0.1066 0.00740 0.00203 -0.1116 0.6139 0.4572
-3.250 0.1360 0.00738 0.00203 -0.1121 0.6130 0.4805
-3.000 0.1656 0.00740 0.00205 -0.1126 0.6121 0.4989
-2.750 0.1950 0.00743 0.00207 -0.1131 0.6111 0.5081
-2.500 0.2246 0.00747 0.00206 -0.1136 0.6100 0.5130
-2.250 0.2539 0.00748 0.00205 -0.1140 0.6089 0.5172
-2.000 0.2833 0.00751 0.00206 -0.1145 0.6079 0.5204
-1.750 0.3128 0.00754 0.00206 -0.1150 0.6070 0.5227
-1.500 0.3424 0.00754 0.00205 -0.1155 0.6064 0.5243
-1.250 0.3720 0.00755 0.00204 -0.1161 0.6057 0.5257
-1.000 0.4016 0.00757 0.00204 -0.1166 0.6050 0.5269
-0.750 0.4311 0.00758 0.00204 -0.1171 0.6043 0.5279
-0.500 0.4606 0.00759 0.00205 -0.1176 0.6035 0.5292
-0.250 0.4899 0.00759 0.00206 -0.1181 0.6026 0.5307
0.000 0.5193 0.00760 0.00208 -0.1186 0.6016 0.5321
0.250 0.5486 0.00762 0.00210 -0.1191 0.6006 0.5333
0.500 0.5779 0.00764 0.00212 -0.1196 0.5997 0.5346
0.750 0.6072 0.00766 0.00215 -0.1201 0.5988 0.5359
1.000 0.6364 0.00769 0.00218 -0.1206 0.5979 0.5372
1.250 0.6656 0.00772 0.00222 -0.1211 0.5967 0.5386
1.500 0.6946 0.00776 0.00225 -0.1215 0.5954 0.5401
1.750 0.7234 0.00781 0.00229 -0.1220 0.5937 0.5416
2.000 0.7523 0.00786 0.00234 -0.1224 0.5918 0.5428
2.250 0.7811 0.00787 0.00237 -0.1228 0.5899 0.5439
2.500 0.8097 0.00786 0.00241 -0.1232 0.5875 0.5454
2.750 0.8382 0.00786 0.00244 -0.1235 0.5844 0.5469
3.000 0.8663 0.00788 0.00246 -0.1238 0.5809 0.5484
3.250 0.8940 0.00794 0.00251 -0.1240 0.5774 0.5500
3.500 0.9226 0.00794 0.00257 -0.1243 0.5748 0.5516
3.750 0.9511 0.00796 0.00263 -0.1247 0.5719 0.5532
4.000 0.9793 0.00800 0.00270 -0.1250 0.5690 0.5549
4.250 1.0071 0.00804 0.00276 -0.1252 0.5659 0.5567
4.500 1.0344 0.00811 0.00283 -0.1254 0.5629 0.5584
4.750 1.0627 0.00814 0.00292 -0.1257 0.5596 0.5601
5.000 1.0904 0.00818 0.00301 -0.1260 0.5554 0.5622
5.250 1.1171 0.00823 0.00309 -0.1260 0.5503 0.5643
5.500 1.1442 0.00829 0.00319 -0.1261 0.5446 0.5664
5.750 1.1694 0.00838 0.00329 -0.1259 0.5347 0.5685
6.000 1.1925 0.00853 0.00341 -0.1252 0.5156 0.5707
6.250 1.2065 0.00898 0.00368 -0.1228 0.4775 0.5727
6.500 1.2167 0.00958 0.00411 -0.1199 0.4407 0.5746
6.750 1.2258 0.01015 0.00455 -0.1167 0.4107 0.5767
7.000 1.2303 0.01069 0.00499 -0.1126 0.3848 0.5791
7.250 1.2364 0.01127 0.00549 -0.1089 0.3614 0.5816
7.500 1.2409 0.01194 0.00608 -0.1051 0.3383 0.5843
7.750 1.2375 0.01290 0.00689 -0.1002 0.3074 0.5869
8.000 1.2402 0.01374 0.00766 -0.0966 0.2874 0.5896
8.250 1.2428 0.01468 0.00854 -0.0932 0.2698 0.5927
8.500 1.2446 0.01576 0.00958 -0.0899 0.2518 0.5958
8.750 1.2486 0.01686 0.01065 -0.0872 0.2369 0.5992
9.000 1.2524 0.01807 0.01183 -0.0847 0.2222 0.6027
9.250 1.2545 0.01947 0.01318 -0.0822 0.2051 0.6058
9.500 1.2543 0.02109 0.01473 -0.0796 0.1856 0.6091
9.750 1.2546 0.02275 0.01632 -0.0772 0.1679 0.6130
10.000 1.2541 0.02453 0.01802 -0.0748 0.1471 0.6170
10.250 1.2534 0.02636 0.01975 -0.0726 0.1282 0.6208
10.500 1.2563 0.02801 0.02136 -0.0707 0.1132 0.6249
10.750 1.2606 0.02959 0.02291 -0.0691 0.1001 0.6296
11.000 1.2657 0.03118 0.02446 -0.0677 0.0885 0.6347
11.500 1.2769 0.03440 0.02762 -0.0650 0.0661 0.6457
11.750 1.2826 0.03606 0.02926 -0.0639 0.0558 0.6521
12.000 1.2892 0.03770 0.03088 -0.0628 0.0462 0.6583
12.250 1.2944 0.03950 0.03267 -0.0617 0.0368 0.6664
12.500 1.3011 0.04121 0.03437 -0.0608 0.0294 0.6738
12.750 1.3090 0.04285 0.03603 -0.0600 0.0242 0.6829
13.000 1.3140 0.04479 0.03797 -0.0591 0.0174 0.6919
13.250 1.3220 0.04650 0.03971 -0.0585 0.0135 0.7019
13.500 1.3270 0.04852 0.04175 -0.0577 0.0086 0.7131
13.750 1.3339 0.05039 0.04368 -0.0571 0.0058 0.7258
14.000 1.3427 0.05212 0.04549 -0.0567 0.0050 0.7411
14.250 1.3508 0.05394 0.04740 -0.0562 0.0042 0.7594
14.500 1.3598 0.05567 0.04924 -0.0558 0.0038 0.7834
14.750 1.3678 0.05748 0.05120 -0.0554 0.0035 0.8204
15.250 1.3839 0.06095 0.05508 -0.0547 0.0031 1.0000
15.500 1.3917 0.06301 0.05718 -0.0545 0.0030 1.0000
15.750 1.3992 0.06510 0.05933 -0.0544 0.0029 1.0000
16.000 1.4056 0.06737 0.06164 -0.0543 0.0027 1.0000
16.250 1.4111 0.06976 0.06409 -0.0543 0.0026 1.0000
16.500 1.4170 0.07213 0.06653 -0.0543 0.0025 1.0000
16.750 1.4212 0.07477 0.06923 -0.0544 0.0024 1.0000
17.000 1.4250 0.07749 0.07202 -0.0546 0.0023 1.0000
17.250 1.4294 0.08019 0.07479 -0.0549 0.0023 1.0000
17.500 1.4341 0.08287 0.07754 -0.0552 0.0023 1.0000
17.750 1.4368 0.08588 0.08062 -0.0556 0.0022 1.0000
18.000 1.4393 0.08892 0.08373 -0.0561 0.0022 1.0000
18.250 1.4418 0.09202 0.08691 -0.0567 0.0022 1.0000
18.500 1.4431 0.09533 0.09030 -0.0574 0.0021 1.0000
18.750 1.4441 0.09872 0.09377 -0.0582 0.0021 1.0000
19.000 1.4447 0.10223 0.09737 -0.0591 0.0021 1.0000
19.250 1.4437 0.10599 0.10122 -0.0602 0.0020 1.0000
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Polar data table (+)
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