EPPLER 1098 AIRFOIL (e1098-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 1098 AIRFOIL (e1098-il) Reynolds number: 100,000 Max Cl/Cd: 24.89 at α=11.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e1098-il-100000-n5.txt Download as CSV file: xf-e1098-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.750 -0.3613 0.06911 0.06300 -0.1227 0.8483 0.0218
-12.500 -0.3748 0.06464 0.05830 -0.1251 0.8390 0.0217
-12.250 -0.3909 0.06046 0.05384 -0.1269 0.8305 0.0218
-12.000 -0.4023 0.05687 0.05004 -0.1280 0.8230 0.0219
-11.500 -0.4150 0.05104 0.04377 -0.1288 0.8096 0.0221
-11.250 -0.4132 0.04895 0.04157 -0.1289 0.8041 0.0228
-11.000 -0.4132 0.04689 0.03935 -0.1285 0.7978 0.0232
-10.750 -0.4102 0.04499 0.03728 -0.1281 0.7927 0.0238
-10.500 -0.4070 0.04320 0.03529 -0.1275 0.7880 0.0246
-10.250 -0.4026 0.04124 0.03308 -0.1266 0.7829 0.0250
-10.000 -0.3944 0.03943 0.03101 -0.1256 0.7788 0.0255
-9.750 -0.3805 0.03761 0.02891 -0.1248 0.7755 0.0260
-9.500 -0.3618 0.03597 0.02703 -0.1242 0.7722 0.0266
-9.250 -0.3394 0.03455 0.02540 -0.1238 0.7687 0.0273
-9.000 -0.3138 0.03331 0.02401 -0.1234 0.7657 0.0281
-8.750 -0.2902 0.03222 0.02292 -0.1229 0.7630 0.0293
-8.500 -0.2718 0.03136 0.02201 -0.1221 0.7604 0.0309
-8.250 -0.2545 0.03061 0.02118 -0.1212 0.7576 0.0330
-8.000 -0.2384 0.02996 0.02044 -0.1199 0.7541 0.0352
-7.750 -0.2278 0.02912 0.01965 -0.1182 0.7509 0.0372
-7.500 -0.2191 0.02841 0.01891 -0.1163 0.7480 0.0393
-7.250 -0.2102 0.02774 0.01815 -0.1144 0.7455 0.0416
-7.000 -0.1994 0.02704 0.01734 -0.1129 0.7434 0.0454
-6.750 -0.1916 0.02642 0.01676 -0.1110 0.7405 0.0505
-6.500 -0.1821 0.02579 0.01613 -0.1093 0.7378 0.0580
-6.250 -0.1723 0.02506 0.01546 -0.1076 0.7352 0.0717
-6.000 -0.1643 0.02407 0.01469 -0.1060 0.7329 0.1071
-5.750 -0.1608 0.02245 0.01366 -0.1046 0.7307 0.2107
-5.500 -0.1532 0.02137 0.01371 -0.1026 0.7289 0.3983
-5.250 -0.1311 0.02196 0.01435 -0.1014 0.7264 0.4797
-5.000 -0.1091 0.02274 0.01502 -0.1003 0.7237 0.5191
-4.750 -0.0858 0.02417 0.01644 -0.0981 0.7215 0.5503
-4.500 -0.0619 0.02520 0.01741 -0.0962 0.7196 0.5677
-4.250 -0.0380 0.02557 0.01764 -0.0954 0.7178 0.5786
-4.000 -0.0129 0.02582 0.01776 -0.0948 0.7163 0.5853
-3.750 0.0125 0.02571 0.01746 -0.0951 0.7148 0.5925
-3.500 0.0393 0.02582 0.01744 -0.0948 0.7135 0.5961
-3.250 0.0593 0.02596 0.01750 -0.0940 0.7110 0.6006
-3.000 0.0785 0.02591 0.01731 -0.0939 0.7081 0.6068
-2.750 0.0994 0.02615 0.01750 -0.0930 0.7059 0.6093
-2.500 0.1218 0.02630 0.01757 -0.0925 0.7040 0.6122
-2.250 0.1458 0.02636 0.01754 -0.0924 0.7023 0.6157
-2.000 0.1720 0.02631 0.01735 -0.0930 0.7007 0.6196
-1.750 0.1999 0.02622 0.01712 -0.0938 0.6993 0.6231
-1.500 0.2275 0.02624 0.01706 -0.0940 0.6981 0.6252
-1.250 0.2366 0.02689 0.01775 -0.0918 0.6944 0.6275
-1.000 0.2508 0.02739 0.01824 -0.0905 0.6913 0.6302
-0.750 0.2720 0.02763 0.01842 -0.0902 0.6887 0.6333
-0.500 0.2978 0.02773 0.01841 -0.0907 0.6868 0.6363
-0.250 0.3246 0.02782 0.01843 -0.0912 0.6852 0.6388
0.000 0.3512 0.02795 0.01854 -0.0913 0.6839 0.6408
0.250 0.3802 0.02802 0.01856 -0.0919 0.6827 0.6431
0.500 0.3600 0.02988 0.02054 -0.0861 0.6746 0.6454
0.750 0.3826 0.03018 0.02080 -0.0860 0.6721 0.6479
1.000 0.4109 0.03029 0.02086 -0.0866 0.6704 0.6505
1.250 0.4418 0.03034 0.02084 -0.0877 0.6691 0.6537
1.500 0.4714 0.03039 0.02089 -0.0882 0.6679 0.6558
2.000 0.4625 0.03302 0.02363 -0.0808 0.6551 0.6604
2.250 0.4950 0.03299 0.02359 -0.0818 0.6539 0.6630
2.500 0.5293 0.03293 0.02351 -0.0831 0.6528 0.6658
3.000 0.5271 0.03580 0.02645 -0.0774 0.6391 0.6712
3.250 0.5600 0.03561 0.02630 -0.0781 0.6380 0.6739
4.000 0.5747 0.03964 0.03043 -0.0727 0.6171 0.6836
4.250 0.6388 0.03772 0.02855 -0.0762 0.6221 0.6866
4.750 0.6551 0.03989 0.03086 -0.0729 0.6083 0.6928
5.250 0.6793 0.04170 0.03277 -0.0707 0.5947 0.7009
5.500 0.7124 0.04131 0.03247 -0.0712 0.5931 0.7048
6.000 0.7399 0.04283 0.03412 -0.0692 0.5793 0.7137
6.250 0.7750 0.04223 0.03362 -0.0698 0.5777 0.7182
6.750 0.8050 0.04345 0.03501 -0.0680 0.5635 0.7280
7.250 0.8121 0.04621 0.03796 -0.0646 0.5420 0.7386
7.500 0.8383 0.04605 0.03792 -0.0645 0.5373 0.7460
7.750 0.8708 0.04529 0.03730 -0.0646 0.5349 0.7532
8.000 0.8738 0.04682 0.03892 -0.0631 0.5229 0.7610
8.250 0.9060 0.04597 0.03824 -0.0631 0.5204 0.7697
8.500 0.9103 0.04737 0.03976 -0.0616 0.5082 0.7788
9.000 0.9471 0.04770 0.04040 -0.0600 0.4933 0.8026
9.250 0.9564 0.04861 0.04147 -0.0587 0.4822 0.8183
9.500 0.9845 0.04761 0.04068 -0.0579 0.4780 0.8426
9.750 0.9924 0.04829 0.04157 -0.0560 0.4663 0.8868
10.000 1.0087 0.04824 0.04164 -0.0551 0.4560 1.0000
10.250 1.0427 0.04719 0.04064 -0.0553 0.4485 1.0000
10.500 1.0634 0.04743 0.04094 -0.0550 0.4353 1.0000
10.750 1.0875 0.04731 0.04085 -0.0547 0.4219 1.0000
11.000 1.1132 0.04701 0.04056 -0.0544 0.4075 1.0000
11.250 1.1382 0.04677 0.04031 -0.0540 0.3915 1.0000
11.500 1.1613 0.04673 0.04024 -0.0535 0.3743 1.0000
11.750 1.1782 0.04733 0.04081 -0.0529 0.3561 1.0000
12.000 1.1916 0.04832 0.04177 -0.0521 0.3375 1.0000
12.250 1.2039 0.04943 0.04283 -0.0513 0.3193 1.0000
12.500 1.2147 0.05070 0.04405 -0.0505 0.3013 1.0000
12.750 1.2240 0.05217 0.04547 -0.0498 0.2843 1.0000
13.000 1.2308 0.05395 0.04725 -0.0490 0.2675 1.0000
13.250 1.2363 0.05593 0.04922 -0.0484 0.2511 1.0000
13.500 1.2406 0.05806 0.05135 -0.0477 0.2349 1.0000
13.750 1.2440 0.06035 0.05363 -0.0472 0.2190 1.0000
14.000 1.2464 0.06282 0.05608 -0.0467 0.2035 1.0000
14.250 1.2479 0.06544 0.05869 -0.0463 0.1883 1.0000
14.500 1.2491 0.06817 0.06143 -0.0460 0.1740 1.0000
14.750 1.2499 0.07102 0.06428 -0.0459 0.1604 1.0000
15.000 1.2503 0.07399 0.06726 -0.0458 0.1477 1.0000
15.250 1.2497 0.07714 0.07042 -0.0458 0.1358 1.0000
15.500 1.2481 0.08049 0.07379 -0.0460 0.1242 1.0000
15.750 1.2448 0.08415 0.07743 -0.0463 0.1126 1.0000
16.000 1.2410 0.08799 0.08128 -0.0469 0.1011 1.0000
16.250 1.2377 0.09185 0.08518 -0.0475 0.0900 1.0000
16.500 1.2340 0.09586 0.08922 -0.0484 0.0798 1.0000
16.750 1.2297 0.10003 0.09343 -0.0494 0.0706 1.0000
17.000 1.2240 0.10449 0.09791 -0.0506 0.0626 1.0000
17.250 1.2195 0.10886 0.10235 -0.0519 0.0552 1.0000
17.500 1.2147 0.11336 0.10693 -0.0534 0.0486 1.0000
17.750 1.2067 0.11844 0.11201 -0.0552 0.0436 1.0000
18.000 1.2024 0.12300 0.11669 -0.0570 0.0385 1.0000
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