EPPLER 1098 AIRFOIL (e1098-il) Xfoil prediction polar at RE=200,000 Ncrit=9
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Airfoil: EPPLER 1098 AIRFOIL (e1098-il) Reynolds number: 200,000 Max Cl/Cd: 51.93 at α=10.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e1098-il-200000.txt Download as CSV file: xf-e1098-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.250 -0.1476 0.11398 0.10991 -0.1079 0.8537 0.0616
-13.000 -0.1505 0.10935 0.10524 -0.1109 0.8449 0.0651
-12.750 -0.2038 0.09765 0.09358 -0.1223 0.8392 0.0675
-12.500 -0.1735 0.09687 0.09276 -0.1184 0.8325 0.0693
-12.250 -0.1560 0.09579 0.09160 -0.1174 0.8256 0.0710
-12.000 -0.1503 0.09281 0.08855 -0.1184 0.8205 0.0732
-11.750 -0.1554 0.08814 0.08390 -0.1208 0.8153 0.0756
-10.000 -0.4326 0.04227 0.03589 -0.1268 0.7846 0.0363
-9.750 -0.4115 0.03914 0.03266 -0.1266 0.7813 0.0340
-9.500 -0.4025 0.03626 0.02950 -0.1254 0.7783 0.0328
-9.250 -0.3892 0.03373 0.02664 -0.1242 0.7758 0.0320
-9.000 -0.3719 0.03162 0.02424 -0.1233 0.7734 0.0315
-8.750 -0.3514 0.02989 0.02231 -0.1227 0.7706 0.0316
-8.500 -0.3282 0.02845 0.02072 -0.1222 0.7679 0.0320
-8.250 -0.3053 0.02741 0.01954 -0.1217 0.7655 0.0332
-8.000 -0.2832 0.02664 0.01861 -0.1211 0.7632 0.0347
-7.750 -0.2581 0.02570 0.01755 -0.1207 0.7613 0.0357
-7.500 -0.2306 0.02423 0.01614 -0.1203 0.7596 0.0373
-7.250 -0.2145 0.02352 0.01549 -0.1190 0.7573 0.0389
-7.000 -0.2006 0.02291 0.01489 -0.1174 0.7546 0.0409
-6.750 -0.1866 0.02234 0.01428 -0.1160 0.7522 0.0434
-6.500 -0.1766 0.02151 0.01346 -0.1142 0.7500 0.0472
-6.250 -0.1612 0.02093 0.01286 -0.1132 0.7481 0.0540
-6.000 -0.1476 0.02008 0.01201 -0.1120 0.7464 0.0653
-5.750 -0.1388 0.01856 0.01092 -0.1107 0.7448 0.1351
-5.500 -0.1360 0.01661 0.01063 -0.1093 0.7431 0.4638
-5.250 -0.1110 0.01739 0.01135 -0.1087 0.7412 0.5158
-5.000 -0.0858 0.01823 0.01218 -0.1078 0.7391 0.5385
-4.750 -0.0602 0.01895 0.01286 -0.1070 0.7369 0.5534
-4.500 -0.0343 0.01979 0.01369 -0.1060 0.7351 0.5679
-4.250 -0.0089 0.02109 0.01506 -0.1041 0.7336 0.5854
-4.000 0.0163 0.02223 0.01625 -0.1022 0.7322 0.5982
-3.750 0.0421 0.02254 0.01643 -0.1019 0.7309 0.6084
-3.500 0.0682 0.02302 0.01690 -0.1010 0.7298 0.6126
-3.250 0.0949 0.02315 0.01692 -0.1012 0.7287 0.6186
-3.000 0.1151 0.02325 0.01697 -0.1009 0.7265 0.6240
-2.750 0.1339 0.02367 0.01741 -0.0996 0.7241 0.6267
-2.500 0.1544 0.02399 0.01772 -0.0989 0.7221 0.6300
-2.250 0.1770 0.02414 0.01779 -0.0990 0.7203 0.6344
-2.000 0.2024 0.02410 0.01764 -0.0998 0.7185 0.6387
-1.750 0.2279 0.02419 0.01769 -0.0996 0.7169 0.6408
-1.500 0.2548 0.02427 0.01773 -0.0998 0.7156 0.6431
-1.250 0.2826 0.02435 0.01774 -0.1002 0.7146 0.6457
-1.000 0.3111 0.02442 0.01773 -0.1010 0.7135 0.6488
-0.750 0.3075 0.02575 0.01913 -0.0979 0.7084 0.6519
-0.500 0.3165 0.02660 0.01997 -0.0963 0.7048 0.6545
-0.250 0.3388 0.02685 0.02021 -0.0959 0.7026 0.6562
0.000 0.3655 0.02699 0.02032 -0.0962 0.7010 0.6580
0.250 0.3959 0.02701 0.02030 -0.0969 0.6999 0.6603
0.500 0.4301 0.02688 0.02013 -0.0983 0.6989 0.6627
0.750 0.4656 0.02676 0.01993 -0.0999 0.6981 0.6649
1.000 0.4040 0.03065 0.02396 -0.0893 0.6858 0.6672
1.250 0.3469 0.03446 0.02778 -0.0799 0.6738 0.6695
1.500 0.3768 0.03444 0.02777 -0.0803 0.6716 0.6714
1.750 0.4120 0.03423 0.02755 -0.0815 0.6703 0.6733
2.000 0.4516 0.03381 0.02712 -0.0832 0.6695 0.6753
2.250 0.4932 0.03333 0.02662 -0.0851 0.6688 0.6776
2.500 0.5382 0.03276 0.02604 -0.0877 0.6684 0.6800
2.750 0.5846 0.03226 0.02551 -0.0906 0.6679 0.6830
3.000 0.6296 0.03174 0.02499 -0.0932 0.6675 0.6857
3.250 0.5110 0.03839 0.03170 -0.0769 0.6418 0.6872
3.500 0.5478 0.03800 0.03135 -0.0779 0.6402 0.6896
3.750 0.5874 0.03749 0.03086 -0.0794 0.6392 0.6922
4.000 0.6107 0.03784 0.03122 -0.0792 0.6352 0.6950
4.250 0.6630 0.03662 0.03002 -0.0820 0.6362 0.6983
4.500 0.7130 0.03541 0.02883 -0.0845 0.6367 0.7012
4.750 0.7630 0.03409 0.02760 -0.0869 0.6368 0.7043
5.000 0.8175 0.03277 0.02633 -0.0903 0.6370 0.7079
5.250 0.7717 0.03627 0.02987 -0.0821 0.6212 0.7112
5.500 0.8220 0.03484 0.02846 -0.0845 0.6213 0.7153
5.750 0.8730 0.03333 0.02705 -0.0869 0.6214 0.7186
6.000 0.9294 0.03173 0.02554 -0.0904 0.6216 0.7227
6.250 0.9919 0.03023 0.02411 -0.0952 0.6220 0.7275
6.500 0.8808 0.03670 0.03058 -0.0794 0.5947 0.7311
6.750 0.9260 0.03518 0.02919 -0.0807 0.5945 0.7355
7.000 0.9735 0.03358 0.02770 -0.0824 0.5946 0.7414
7.250 1.0250 0.03188 0.02610 -0.0848 0.5946 0.7478
7.500 1.0797 0.03007 0.02442 -0.0877 0.5944 0.7537
7.750 1.1431 0.02809 0.02255 -0.0921 0.5941 0.7611
8.000 1.1799 0.02709 0.02168 -0.0929 0.5901 0.7677
8.250 1.1800 0.02739 0.02208 -0.0888 0.5812 0.7762
8.500 1.2584 0.02449 0.01932 -0.0951 0.5794 0.7847
8.750 1.2337 0.02563 0.02058 -0.0875 0.5683 0.7953
9.250 1.2711 0.02464 0.01986 -0.0842 0.5526 0.8225
9.500 1.2621 0.02557 0.02095 -0.0797 0.5408 0.8411
9.750 1.2664 0.02588 0.02143 -0.0766 0.5292 0.8703
10.000 1.2676 0.02638 0.02213 -0.0737 0.5145 1.0000
10.250 1.2890 0.02651 0.02227 -0.0736 0.4980 1.0000
10.500 1.3216 0.02575 0.02144 -0.0739 0.4789 1.0000
10.750 1.3418 0.02584 0.02140 -0.0731 0.4541 1.0000
11.000 1.3543 0.02648 0.02185 -0.0716 0.4266 1.0000
11.250 1.3578 0.02782 0.02299 -0.0694 0.4000 1.0000
11.500 1.3553 0.02964 0.02464 -0.0669 0.3743 1.0000
11.750 1.3508 0.03173 0.02662 -0.0646 0.3501 1.0000
12.000 1.3466 0.03386 0.02861 -0.0624 0.3282 1.0000
12.250 1.3425 0.03615 0.03082 -0.0604 0.3064 1.0000
12.500 1.3391 0.03846 0.03303 -0.0587 0.2863 1.0000
12.750 1.3357 0.04088 0.03535 -0.0571 0.2665 1.0000
13.000 1.3324 0.04342 0.03781 -0.0557 0.2460 1.0000
13.250 1.3289 0.04607 0.04036 -0.0545 0.2267 1.0000
13.500 1.3261 0.04875 0.04296 -0.0534 0.2073 1.0000
13.750 1.3237 0.05150 0.04564 -0.0525 0.1874 1.0000
14.000 1.3213 0.05434 0.04839 -0.0518 0.1695 1.0000
14.250 1.3196 0.05718 0.05116 -0.0511 0.1537 1.0000
14.500 1.3203 0.05987 0.05381 -0.0507 0.1394 1.0000
14.750 1.3202 0.06271 0.05663 -0.0503 0.1263 1.0000
15.000 1.3213 0.06548 0.05939 -0.0500 0.1143 1.0000
15.250 1.3216 0.06839 0.06231 -0.0498 0.1023 1.0000
15.500 1.3218 0.07139 0.06531 -0.0497 0.0908 1.0000
15.750 1.3202 0.07468 0.06859 -0.0497 0.0787 1.0000
16.000 1.3154 0.07847 0.07233 -0.0498 0.0654 1.0000
16.250 1.3079 0.08269 0.07650 -0.0500 0.0507 1.0000
16.500 1.2960 0.08763 0.08137 -0.0504 0.0384 1.0000
16.750 1.2854 0.09256 0.08630 -0.0510 0.0317 1.0000
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