EPPLER 1098 AIRFOIL (e1098-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 1098 AIRFOIL (e1098-il) Reynolds number: 100,000 Max Cl/Cd: 29.84 at α=12.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e1098-il-100000.txt Download as CSV file: xf-e1098-il-100000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.500 -0.1853 0.12099 0.11648 -0.0972 0.9442 0.1363
-12.250 -0.1586 0.11646 0.11190 -0.0994 0.9383 0.1423
-12.000 -0.1918 0.11178 0.10727 -0.1095 0.9316 0.1523
-11.750 -0.1337 0.10742 0.10279 -0.1081 0.9280 0.1565
-11.500 -0.1076 0.07690 0.07233 -0.1270 0.8979 0.0922
-11.250 -0.1785 0.06186 0.05718 -0.1353 0.8957 0.0779
-11.000 -0.2716 0.06696 0.06203 -0.1398 0.9064 0.0773
-10.750 -0.3095 0.05014 0.04478 -0.1394 0.8829 0.0680
-10.500 -0.3017 0.04620 0.04078 -0.1391 0.8782 0.0663
-10.250 -0.3553 0.05446 0.04863 -0.1420 0.8823 0.0642
-10.000 -0.3695 0.05271 0.04673 -0.1391 0.8748 0.0631
-9.750 -0.3770 0.05028 0.04402 -0.1372 0.8693 0.0621
-9.500 -0.3838 0.04823 0.04168 -0.1347 0.8640 0.0610
-9.250 -0.3897 0.04669 0.03987 -0.1317 0.8584 0.0606
-9.000 -0.3876 0.04458 0.03738 -0.1296 0.8545 0.0596
-8.750 -0.3794 0.04228 0.03457 -0.1279 0.8517 0.0582
-8.500 -0.3861 0.04183 0.03390 -0.1234 0.8465 0.0575
-8.250 -0.3791 0.04078 0.03260 -0.1207 0.8426 0.0571
-8.000 -0.3585 0.03906 0.03066 -0.1199 0.8398 0.0574
-7.750 -0.3294 0.03723 0.02871 -0.1202 0.8379 0.0586
-7.500 -0.2972 0.03571 0.02709 -0.1207 0.8363 0.0608
-7.250 -0.3315 0.03728 0.02869 -0.1120 0.8311 0.0604
-7.000 -0.3477 0.03796 0.02935 -0.1058 0.8278 0.0610
-6.750 -0.3463 0.03794 0.02928 -0.1021 0.8252 0.0634
-6.500 -0.3271 0.03747 0.02866 -0.1009 0.8233 0.0670
-6.250 -0.3029 0.03631 0.02771 -0.1002 0.8220 0.0720
-6.000 -0.2888 0.03597 0.02738 -0.0982 0.8208 0.0775
-5.750 -0.3296 0.03742 0.02882 -0.0889 0.8200 0.0754
-5.500 -0.3438 0.03794 0.02932 -0.0833 0.8189 0.0778
-5.250 -0.3427 0.03795 0.02934 -0.0801 0.8191 0.0824
-5.000 -0.3353 0.03781 0.02924 -0.0781 0.8196 0.0929
-4.750 -0.3274 0.03727 0.02886 -0.0765 0.8199 0.1122
-4.500 -0.3235 0.03516 0.02914 -0.0757 0.8201 0.5087
-4.250 -0.3506 0.03610 0.03006 -0.0695 0.8302 0.5141
-4.000 -0.3406 0.03874 0.03270 -0.0648 0.8336 0.5645
-3.750 -0.4618 0.04022 0.03170 -0.0478 0.9413 0.0972
-3.500 -0.4403 0.03684 0.03091 -0.0501 0.9375 0.4802
-3.250 -0.4178 0.04003 0.03404 -0.0467 0.9304 0.5781
-3.000 -0.4046 0.04165 0.03565 -0.0429 0.9242 0.6021
-2.750 -0.3853 0.04321 0.03714 -0.0402 0.9166 0.6243
-2.500 -0.3706 0.04678 0.04084 -0.0339 0.9129 0.6564
-2.250 -0.3767 0.04704 0.04119 -0.0256 0.9028 0.6759
-2.000 -0.3575 0.04916 0.04325 -0.0218 0.8984 0.7017
-1.750 -0.3537 0.04889 0.04293 -0.0175 0.8902 0.7102
-1.500 -0.3229 0.04944 0.04327 -0.0195 0.8850 0.7181
-1.250 -0.2885 0.05104 0.04470 -0.0213 0.8821 0.7239
-1.000 -0.2778 0.04991 0.04345 -0.0205 0.8718 0.7291
-0.750 -0.2430 0.05090 0.04426 -0.0231 0.8681 0.7335
-0.500 -0.2326 0.05059 0.04388 -0.0215 0.8597 0.7369
-0.250 -0.1992 0.05135 0.04450 -0.0239 0.8540 0.7408
0.000 -0.1564 0.05308 0.04604 -0.0285 0.8515 0.7448
0.250 -0.1488 0.05211 0.04500 -0.0272 0.8407 0.7475
0.500 -0.1124 0.05348 0.04628 -0.0297 0.8369 0.7501
0.750 -0.1046 0.05312 0.04587 -0.0281 0.8273 0.7527
1.000 -0.0679 0.05428 0.04691 -0.0311 0.8225 0.7555
1.250 -0.0533 0.05449 0.04706 -0.0310 0.8140 0.7582
1.500 -0.0176 0.05551 0.04797 -0.0342 0.8081 0.7612
1.750 0.0026 0.05630 0.04870 -0.0348 0.8021 0.7633
2.000 0.0272 0.05683 0.04920 -0.0355 0.7934 0.7655
2.250 0.0684 0.05879 0.05110 -0.0388 0.7902 0.7686
2.500 0.0732 0.05842 0.05071 -0.0371 0.7784 0.7712
2.750 0.1171 0.06041 0.05263 -0.0410 0.7749 0.7741
3.000 0.1236 0.06029 0.05248 -0.0400 0.7631 0.7765
3.250 0.1664 0.06225 0.05442 -0.0433 0.7595 0.7793
3.500 0.1692 0.06212 0.05431 -0.0413 0.7474 0.7820
4.000 0.2197 0.06421 0.05638 -0.0434 0.7310 0.7888
4.250 0.2340 0.06510 0.05727 -0.0436 0.7206 0.7919
4.500 0.2773 0.06652 0.05869 -0.0462 0.7141 0.7953
4.750 0.2858 0.06697 0.05918 -0.0451 0.7013 0.7985
5.000 0.3049 0.06780 0.06003 -0.0453 0.6890 0.8025
5.250 0.3912 0.06498 0.05712 -0.0484 0.6499 0.8088
5.500 0.4176 0.06513 0.05732 -0.0485 0.6394 0.8133
5.750 0.4360 0.06560 0.05784 -0.0482 0.6269 0.8180
6.000 0.4910 0.06531 0.05757 -0.0509 0.6217 0.8241
6.250 0.4994 0.06596 0.05829 -0.0498 0.6094 0.8291
6.500 0.5129 0.06683 0.05921 -0.0494 0.5980 0.8352
6.750 0.5581 0.06634 0.05880 -0.0508 0.5934 0.8430
7.000 0.5667 0.06732 0.05985 -0.0499 0.5812 0.8507
7.250 0.6133 0.06652 0.05913 -0.0511 0.5779 0.8605
7.500 0.6200 0.06757 0.06027 -0.0502 0.5654 0.8699
7.750 0.6319 0.06835 0.06118 -0.0494 0.5544 0.8814
8.000 0.6704 0.06748 0.06044 -0.0497 0.5501 0.8986
8.250 0.6794 0.06832 0.06144 -0.0488 0.5385 0.9231
8.500 0.7066 0.06844 0.06172 -0.0501 0.5291 1.0000
8.750 0.7495 0.06811 0.06145 -0.0527 0.5227 1.0000
9.000 0.8062 0.06654 0.05993 -0.0556 0.5202 1.0000
9.250 0.8210 0.06775 0.06121 -0.0563 0.5075 1.0000
9.500 0.8378 0.06877 0.06228 -0.0568 0.4956 1.0000
9.750 0.8881 0.06671 0.06029 -0.0581 0.4927 1.0000
10.250 0.9407 0.06613 0.05987 -0.0582 0.4746 1.0000
10.500 0.9705 0.06519 0.05903 -0.0580 0.4658 1.0000
10.750 1.0246 0.06142 0.05541 -0.0582 0.4638 1.0000
11.000 1.0825 0.05690 0.05103 -0.0583 0.4627 1.0000
11.250 1.1008 0.05670 0.05093 -0.0573 0.4503 1.0000
11.500 1.1727 0.05077 0.04519 -0.0578 0.4484 1.0000
11.750 1.2084 0.04883 0.04335 -0.0573 0.4352 1.0000
12.000 1.2585 0.04568 0.04026 -0.0573 0.4201 1.0000
12.250 1.2908 0.04446 0.03901 -0.0567 0.3992 1.0000
12.500 1.3152 0.04407 0.03856 -0.0558 0.3757 1.0000
12.750 1.3264 0.04497 0.03937 -0.0544 0.3522 1.0000
13.000 1.3411 0.04560 0.03981 -0.0532 0.3284 1.0000
13.250 1.3375 0.04792 0.04210 -0.0515 0.3068 1.0000
13.500 1.3403 0.04972 0.04377 -0.0501 0.2855 1.0000
13.750 1.3392 0.05199 0.04596 -0.0487 0.2653 1.0000
14.000 1.3365 0.05452 0.04844 -0.0475 0.2463 1.0000
14.250 1.3351 0.05700 0.05084 -0.0464 0.2283 1.0000
14.500 1.3345 0.05946 0.05321 -0.0455 0.2111 1.0000
14.750 1.3308 0.06235 0.05604 -0.0447 0.1949 1.0000
15.000 1.3249 0.06558 0.05926 -0.0440 0.1797 1.0000
15.250 1.3178 0.06905 0.06273 -0.0436 0.1651 1.0000
15.500 1.3102 0.07273 0.06639 -0.0434 0.1511 1.0000
15.750 1.3026 0.07654 0.07018 -0.0434 0.1377 1.0000
16.000 1.2947 0.08052 0.07414 -0.0436 0.1248 1.0000
16.250 1.2867 0.08464 0.07823 -0.0439 0.1122 1.0000
16.500 1.2781 0.08896 0.08251 -0.0443 0.1000 1.0000
16.750 1.2688 0.09354 0.08708 -0.0450 0.0882 1.0000
17.000 1.2586 0.09841 0.09198 -0.0458 0.0770 1.0000
17.250 1.2508 0.10302 0.09662 -0.0467 0.0668 1.0000
17.500 1.2451 0.10737 0.10098 -0.0476 0.0581 1.0000
17.750 1.2440 0.11091 0.10445 -0.0482 0.0515 1.0000
18.000 1.2449 0.11436 0.10799 -0.0489 0.0467 1.0000
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Polar data table (+)
Polar graphs
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