EPPLER 1098 AIRFOIL (e1098-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 1098 AIRFOIL (e1098-il) Reynolds number: 1,000,000 Max Cl/Cd: 151.76 at α=7.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e1098-il-1000000.txt Download as CSV file: xf-e1098-il-1000000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.500 -0.5289 0.06184 0.05822 -0.1252 0.7816 0.0075
-15.250 -0.5357 0.05811 0.05436 -0.1268 0.7705 0.0076
-15.000 -0.5588 0.05254 0.04850 -0.1287 0.7618 0.0074
-14.750 -0.5451 0.05168 0.04769 -0.1295 0.7524 0.0078
-14.500 -0.5439 0.04940 0.04531 -0.1303 0.7444 0.0079
-14.250 -0.5467 0.04671 0.04251 -0.1310 0.7379 0.0080
-14.000 -0.5684 0.04207 0.03757 -0.1311 0.7322 0.0078
-13.750 -0.5582 0.04114 0.03663 -0.1316 0.7263 0.0081
-13.500 -0.5568 0.03920 0.03460 -0.1317 0.7211 0.0082
-13.250 -0.5685 0.03570 0.03080 -0.1307 0.7166 0.0080
-13.000 -0.5579 0.03489 0.02999 -0.1309 0.7119 0.0083
-12.750 -0.5573 0.03270 0.02763 -0.1302 0.7081 0.0082
-12.500 -0.5501 0.03133 0.02617 -0.1298 0.7042 0.0083
-12.250 -0.5431 0.02995 0.02468 -0.1291 0.7004 0.0085
-12.000 -0.5343 0.02873 0.02336 -0.1285 0.6969 0.0087
-11.750 -0.5250 0.02736 0.02189 -0.1276 0.6940 0.0086
-11.500 -0.5147 0.02615 0.02057 -0.1268 0.6910 0.0087
-11.250 -0.5034 0.02510 0.01944 -0.1259 0.6879 0.0089
-11.000 -0.4918 0.02410 0.01834 -0.1250 0.6850 0.0089
-10.750 -0.4795 0.02318 0.01735 -0.1240 0.6821 0.0091
-10.500 -0.4659 0.02234 0.01645 -0.1233 0.6801 0.0093
-10.250 -0.4538 0.02139 0.01545 -0.1222 0.6779 0.0093
-10.000 -0.4406 0.02058 0.01458 -0.1212 0.6758 0.0095
-9.750 -0.4262 0.01987 0.01382 -0.1204 0.6736 0.0096
-9.500 -0.4139 0.01908 0.01295 -0.1192 0.6714 0.0098
-9.250 -0.4168 0.01756 0.01136 -0.1164 0.6692 0.0103
-9.000 -0.4127 0.01680 0.01054 -0.1140 0.6670 0.0105
-8.750 -0.4014 0.01619 0.00991 -0.1124 0.6656 0.0108
-8.500 -0.3851 0.01564 0.00934 -0.1115 0.6641 0.0111
-8.250 -0.3671 0.01512 0.00878 -0.1106 0.6625 0.0113
-8.000 -0.3473 0.01466 0.00828 -0.1100 0.6610 0.0117
-7.750 -0.3265 0.01421 0.00778 -0.1095 0.6594 0.0122
-7.500 -0.3047 0.01379 0.00731 -0.1090 0.6579 0.0125
-7.250 -0.2811 0.01347 0.00694 -0.1088 0.6562 0.0129
-7.000 -0.2603 0.01288 0.00628 -0.1083 0.6545 0.0136
-6.750 -0.2363 0.01253 0.00589 -0.1082 0.6527 0.0146
-6.500 -0.2108 0.01223 0.00556 -0.1083 0.6516 0.0156
-6.250 -0.1845 0.01198 0.00529 -0.1084 0.6506 0.0168
-6.000 -0.1593 0.01157 0.00488 -0.1084 0.6496 0.0199
-5.750 -0.1330 0.01126 0.00456 -0.1086 0.6485 0.0242
-5.500 -0.1066 0.01093 0.00426 -0.1088 0.6473 0.0331
-5.250 -0.0809 0.01046 0.00393 -0.1090 0.6462 0.0640
-5.000 -0.0558 0.00981 0.00355 -0.1094 0.6450 0.1302
-4.750 -0.0311 0.00898 0.00312 -0.1099 0.6439 0.2352
-4.500 -0.0066 0.00789 0.00260 -0.1106 0.6429 0.3890
-4.250 0.0217 0.00761 0.00255 -0.1111 0.6418 0.4688
-4.000 0.0513 0.00762 0.00256 -0.1117 0.6407 0.4879
-3.750 0.0811 0.00768 0.00258 -0.1122 0.6395 0.5010
-3.500 0.1111 0.00781 0.00265 -0.1128 0.6381 0.5122
-3.250 0.1408 0.00788 0.00272 -0.1133 0.6369 0.5204
-3.000 0.1706 0.00798 0.00279 -0.1138 0.6362 0.5306
-2.750 0.2001 0.00804 0.00286 -0.1142 0.6355 0.5366
-2.500 0.2299 0.00809 0.00289 -0.1147 0.6347 0.5407
-2.250 0.2597 0.00815 0.00291 -0.1153 0.6338 0.5435
-2.000 0.2891 0.00812 0.00287 -0.1158 0.6329 0.5463
-1.750 0.3187 0.00812 0.00287 -0.1163 0.6320 0.5486
-1.500 0.3483 0.00814 0.00288 -0.1169 0.6311 0.5504
-1.250 0.3779 0.00816 0.00288 -0.1174 0.6301 0.5520
-1.000 0.4075 0.00817 0.00288 -0.1180 0.6291 0.5536
-0.750 0.4371 0.00819 0.00288 -0.1185 0.6281 0.5551
-0.500 0.4668 0.00821 0.00288 -0.1191 0.6271 0.5564
-0.250 0.4964 0.00825 0.00290 -0.1197 0.6262 0.5576
0.000 0.5261 0.00830 0.00292 -0.1202 0.6253 0.5588
0.250 0.5558 0.00835 0.00296 -0.1208 0.6243 0.5601
0.500 0.5854 0.00840 0.00301 -0.1215 0.6229 0.5619
0.750 0.6149 0.00847 0.00309 -0.1220 0.6218 0.5634
1.000 0.6440 0.00847 0.00312 -0.1225 0.6211 0.5648
1.250 0.6730 0.00847 0.00315 -0.1229 0.6200 0.5663
1.500 0.7020 0.00848 0.00318 -0.1234 0.6187 0.5677
1.750 0.7309 0.00849 0.00321 -0.1238 0.6171 0.5693
2.000 0.7599 0.00850 0.00323 -0.1243 0.6154 0.5709
2.250 0.7890 0.00850 0.00324 -0.1247 0.6136 0.5726
2.500 0.8181 0.00851 0.00324 -0.1252 0.6115 0.5741
2.750 0.8471 0.00855 0.00326 -0.1256 0.6089 0.5753
3.000 0.8756 0.00858 0.00331 -0.1260 0.6063 0.5775
3.250 0.9034 0.00852 0.00332 -0.1262 0.6040 0.5794
3.500 0.9315 0.00850 0.00335 -0.1265 0.6016 0.5812
3.750 0.9600 0.00850 0.00338 -0.1268 0.5994 0.5831
4.000 0.9885 0.00851 0.00342 -0.1272 0.5973 0.5850
4.250 1.0169 0.00854 0.00346 -0.1276 0.5952 0.5870
4.500 1.0459 0.00864 0.00355 -0.1280 0.5927 0.5889
4.750 1.0735 0.00866 0.00362 -0.1282 0.5907 0.5907
5.000 1.1008 0.00863 0.00368 -0.1284 0.5882 0.5934
5.250 1.1283 0.00862 0.00373 -0.1286 0.5853 0.5961
5.500 1.1557 0.00861 0.00377 -0.1287 0.5822 0.5987
5.750 1.1830 0.00865 0.00381 -0.1288 0.5782 0.6013
6.000 1.2088 0.00863 0.00387 -0.1287 0.5732 0.6039
6.250 1.2349 0.00862 0.00390 -0.1285 0.5674 0.6063
6.500 1.2606 0.00865 0.00396 -0.1284 0.5622 0.6095
6.750 1.2868 0.00865 0.00406 -0.1283 0.5555 0.6127
7.000 1.3111 0.00870 0.00413 -0.1279 0.5468 0.6161
7.250 1.3340 0.00879 0.00423 -0.1271 0.5325 0.6195
7.500 1.3541 0.00897 0.00438 -0.1259 0.5110 0.6228
7.750 1.3623 0.00946 0.00472 -0.1225 0.4731 0.6267
8.000 1.3629 0.01009 0.00520 -0.1176 0.4391 0.6307
8.250 1.3624 0.01078 0.00578 -0.1126 0.4106 0.6352
8.500 1.3579 0.01168 0.00653 -0.1072 0.3788 0.6393
8.750 1.3552 0.01258 0.00735 -0.1024 0.3525 0.6442
9.000 1.3442 0.01390 0.00852 -0.0967 0.3203 0.6494
9.250 1.3362 0.01532 0.00983 -0.0920 0.2941 0.6545
9.500 1.3323 0.01676 0.01122 -0.0883 0.2725 0.6606
9.750 1.3297 0.01831 0.01272 -0.0850 0.2540 0.6672
10.000 1.3288 0.01990 0.01426 -0.0822 0.2348 0.6742
10.250 1.3287 0.02153 0.01585 -0.0797 0.2173 0.6823
10.500 1.3272 0.02331 0.01758 -0.0772 0.1988 0.6908
10.750 1.3284 0.02498 0.01921 -0.0750 0.1833 0.7005
11.000 1.3288 0.02673 0.02094 -0.0729 0.1664 0.7117
11.250 1.3287 0.02858 0.02274 -0.0709 0.1478 0.7239
11.500 1.3293 0.03041 0.02454 -0.0690 0.1313 0.7389
11.750 1.3331 0.03207 0.02620 -0.0674 0.1184 0.7572
12.000 1.3356 0.03385 0.02799 -0.0659 0.1044 0.7795
12.250 1.3389 0.03555 0.02974 -0.0643 0.0924 0.8150
12.500 1.3459 0.03689 0.03139 -0.0634 0.0820 0.9917
12.750 1.3506 0.03861 0.03307 -0.0621 0.0734 1.0000
13.000 1.3551 0.04052 0.03491 -0.0610 0.0617 1.0000
13.250 1.3598 0.04246 0.03680 -0.0601 0.0522 1.0000
13.500 1.3625 0.04461 0.03886 -0.0591 0.0399 1.0000
13.750 1.3611 0.04719 0.04135 -0.0580 0.0269 1.0000
14.000 1.3623 0.04959 0.04370 -0.0571 0.0177 1.0000
14.250 1.3600 0.05243 0.04649 -0.0561 0.0093 1.0000
14.500 1.3654 0.05457 0.04864 -0.0556 0.0072 1.0000
14.750 1.3724 0.05660 0.05072 -0.0552 0.0064 1.0000
15.000 1.3791 0.05870 0.05285 -0.0549 0.0058 1.0000
15.250 1.3838 0.06102 0.05524 -0.0545 0.0052 1.0000
15.500 1.3910 0.06315 0.05742 -0.0544 0.0051 1.0000
15.750 1.3980 0.06531 0.05964 -0.0542 0.0049 1.0000
16.000 1.4036 0.06768 0.06207 -0.0541 0.0047 1.0000
16.250 1.4091 0.07008 0.06454 -0.0541 0.0045 1.0000
16.500 1.4142 0.07257 0.06710 -0.0541 0.0044 1.0000
16.750 1.4178 0.07529 0.06989 -0.0542 0.0043 1.0000
17.000 1.4187 0.07841 0.07308 -0.0544 0.0041 1.0000
17.250 1.4205 0.08146 0.07621 -0.0547 0.0040 1.0000
17.500 1.4204 0.08486 0.07969 -0.0551 0.0039 1.0000
17.750 1.4190 0.08845 0.08337 -0.0556 0.0038 1.0000
18.000 1.4153 0.09246 0.08749 -0.0563 0.0038 1.0000
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