MRC-16 (mrc-16-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: MRC-16 (mrc-16-il) Reynolds number: 200,000 Max Cl/Cd: 71.07 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mrc-16-il-200000-n5.txt Download as CSV file: xf-mrc-16-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: MRC-16
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.3940 0.10114 0.09743 -0.0487 1.0000 0.0196
-11.000 -0.4025 0.09536 0.09171 -0.0511 1.0000 0.0195
-10.500 -0.6196 0.04916 0.04502 -0.0757 0.9939 0.0176
-10.250 -0.6222 0.04456 0.04007 -0.0782 0.9839 0.0177
-10.000 -0.6152 0.04119 0.03642 -0.0794 0.9756 0.0179
-9.750 -0.6004 0.03815 0.03308 -0.0810 0.9704 0.0182
-9.500 -0.5888 0.03560 0.03023 -0.0808 0.9618 0.0185
-9.250 -0.5699 0.03301 0.02729 -0.0816 0.9568 0.0190
-9.000 -0.5548 0.03083 0.02478 -0.0809 0.9487 0.0195
-8.750 -0.5336 0.02874 0.02231 -0.0810 0.9432 0.0204
-8.500 -0.5139 0.02686 0.01995 -0.0804 0.9366 0.0213
-8.250 -0.4913 0.02550 0.01848 -0.0802 0.9302 0.0220
-8.000 -0.4649 0.02439 0.01725 -0.0806 0.9258 0.0227
-7.750 -0.4437 0.02338 0.01610 -0.0797 0.9180 0.0234
-7.500 -0.4186 0.02229 0.01481 -0.0795 0.9124 0.0243
-7.250 -0.3945 0.02127 0.01361 -0.0790 0.9062 0.0254
-7.000 -0.3709 0.02039 0.01259 -0.0784 0.8993 0.0266
-6.750 -0.3448 0.01969 0.01187 -0.0784 0.8943 0.0280
-6.500 -0.3223 0.01908 0.01119 -0.0776 0.8863 0.0296
-6.250 -0.2971 0.01836 0.01034 -0.0771 0.8803 0.0311
-6.000 -0.2740 0.01766 0.00958 -0.0763 0.8731 0.0327
-5.750 -0.2497 0.01713 0.00902 -0.0758 0.8663 0.0349
-5.500 -0.2246 0.01666 0.00846 -0.0753 0.8600 0.0378
-5.250 -0.2012 0.01611 0.00788 -0.0746 0.8523 0.0406
-5.000 -0.1755 0.01566 0.00737 -0.0742 0.8464 0.0443
-4.750 -0.1519 0.01525 0.00692 -0.0734 0.8382 0.0490
-4.500 -0.1259 0.01485 0.00646 -0.0731 0.8321 0.0551
-4.250 -0.1019 0.01447 0.00610 -0.0724 0.8239 0.0629
-4.000 -0.0762 0.01410 0.00570 -0.0720 0.8174 0.0743
-3.750 -0.0517 0.01376 0.00539 -0.0715 0.8094 0.0909
-3.500 -0.0264 0.01337 0.00507 -0.0710 0.8024 0.1175
-3.250 -0.0025 0.01296 0.00482 -0.0705 0.7945 0.1611
-3.000 0.0213 0.01246 0.00456 -0.0699 0.7872 0.2311
-2.750 0.0437 0.01195 0.00437 -0.0691 0.7792 0.3200
-2.500 0.0661 0.01146 0.00420 -0.0682 0.7717 0.4168
-2.250 0.0877 0.01104 0.00411 -0.0670 0.7636 0.5100
-2.000 0.1102 0.01070 0.00404 -0.0657 0.7560 0.5965
-1.750 0.1332 0.01048 0.00404 -0.0645 0.7479 0.6696
-1.500 0.1578 0.01035 0.00403 -0.0634 0.7402 0.7308
-1.250 0.1828 0.01029 0.00407 -0.0623 0.7319 0.7814
-1.000 0.2095 0.01029 0.00409 -0.0615 0.7242 0.8221
-0.750 0.2368 0.01034 0.00414 -0.0610 0.7156 0.8522
-0.500 0.2652 0.01039 0.00412 -0.0607 0.7079 0.8757
-0.250 0.2947 0.01047 0.00416 -0.0608 0.6988 0.8941
0.000 0.3255 0.01055 0.00415 -0.0612 0.6908 0.9098
0.250 0.3559 0.01063 0.00417 -0.0616 0.6816 0.9239
0.500 0.3899 0.01071 0.00417 -0.0627 0.6729 0.9348
0.750 0.4240 0.01080 0.00417 -0.0640 0.6637 0.9445
1.000 0.4558 0.01088 0.00420 -0.0648 0.6544 0.9551
1.250 0.4934 0.01097 0.00419 -0.0669 0.6454 0.9615
1.500 0.5271 0.01106 0.00423 -0.0682 0.6352 0.9700
1.750 0.5659 0.01114 0.00424 -0.0707 0.6254 0.9752
2.000 0.6005 0.01123 0.00426 -0.0723 0.6155 0.9824
2.250 0.6384 0.01130 0.00430 -0.0746 0.6047 0.9873
2.500 0.6740 0.01140 0.00434 -0.0765 0.5943 0.9931
3.000 0.7384 0.01159 0.00445 -0.0790 0.5725 1.0000
3.250 0.7593 0.01171 0.00454 -0.0778 0.5623 1.0000
3.500 0.7799 0.01185 0.00462 -0.0765 0.5522 1.0000
3.750 0.8004 0.01199 0.00473 -0.0752 0.5412 1.0000
4.000 0.8208 0.01214 0.00487 -0.0739 0.5307 1.0000
4.250 0.8410 0.01231 0.00500 -0.0726 0.5203 1.0000
4.500 0.8612 0.01249 0.00515 -0.0712 0.5093 1.0000
4.750 0.8813 0.01267 0.00532 -0.0698 0.4982 1.0000
5.000 0.9013 0.01287 0.00550 -0.0684 0.4875 1.0000
5.250 0.9209 0.01309 0.00569 -0.0669 0.4762 1.0000
5.500 0.9407 0.01330 0.00590 -0.0655 0.4646 1.0000
5.750 0.9604 0.01354 0.00613 -0.0641 0.4530 1.0000
6.000 0.9800 0.01379 0.00637 -0.0626 0.4413 1.0000
6.250 0.9993 0.01407 0.00661 -0.0612 0.4293 1.0000
6.500 1.0190 0.01434 0.00689 -0.0598 0.4165 1.0000
6.750 1.0385 0.01464 0.00719 -0.0584 0.4039 1.0000
7.000 1.0577 0.01495 0.00750 -0.0570 0.3910 1.0000
7.250 1.0764 0.01529 0.00783 -0.0555 0.3778 1.0000
7.500 1.0946 0.01566 0.00820 -0.0540 0.3643 1.0000
7.750 1.1122 0.01605 0.00858 -0.0524 0.3505 1.0000
8.000 1.1291 0.01647 0.00899 -0.0507 0.3364 1.0000
8.250 1.1452 0.01692 0.00942 -0.0489 0.3220 1.0000
8.500 1.1595 0.01740 0.00989 -0.0468 0.3075 1.0000
9.000 1.1861 0.01849 0.01096 -0.0426 0.2777 1.0000
9.250 1.1989 0.01912 0.01157 -0.0405 0.2624 1.0000
9.500 1.2111 0.01982 0.01226 -0.0385 0.2468 1.0000
9.750 1.2227 0.02058 0.01302 -0.0365 0.2309 1.0000
10.000 1.2336 0.02143 0.01384 -0.0346 0.2151 1.0000
10.250 1.2437 0.02235 0.01475 -0.0326 0.1993 1.0000
10.500 1.2532 0.02337 0.01574 -0.0308 0.1836 1.0000
10.750 1.2618 0.02448 0.01683 -0.0289 0.1683 1.0000
11.000 1.2696 0.02569 0.01803 -0.0271 0.1534 1.0000
11.250 1.2767 0.02700 0.01932 -0.0254 0.1391 1.0000
11.500 1.2830 0.02843 0.02073 -0.0238 0.1254 1.0000
11.750 1.2887 0.02995 0.02224 -0.0222 0.1126 1.0000
12.000 1.2936 0.03159 0.02387 -0.0207 0.1007 1.0000
12.250 1.2979 0.03334 0.02563 -0.0194 0.0899 1.0000
12.500 1.3011 0.03524 0.02754 -0.0181 0.0801 1.0000
12.750 1.3033 0.03729 0.02959 -0.0169 0.0713 1.0000
13.000 1.3056 0.03939 0.03173 -0.0158 0.0635 1.0000
13.250 1.3074 0.04159 0.03397 -0.0149 0.0568 1.0000
13.500 1.3071 0.04407 0.03649 -0.0141 0.0512 1.0000
13.750 1.3083 0.04650 0.03899 -0.0134 0.0462 1.0000
14.000 1.3069 0.04926 0.04181 -0.0129 0.0422 1.0000
14.250 1.3069 0.05198 0.04462 -0.0125 0.0386 1.0000
14.500 1.3035 0.05518 0.04787 -0.0123 0.0357 1.0000
14.750 1.3027 0.05815 0.05096 -0.0122 0.0332 1.0000
15.000 1.3000 0.06143 0.05434 -0.0123 0.0310 1.0000
15.250 1.2946 0.06515 0.05814 -0.0126 0.0294 1.0000
15.500 1.2911 0.06872 0.06182 -0.0130 0.0278 1.0000
15.750 1.2874 0.07239 0.06562 -0.0135 0.0263 1.0000
16.000 1.2820 0.07636 0.06969 -0.0142 0.0250 1.0000
16.250 1.2746 0.08073 0.07414 -0.0152 0.0240 1.0000
16.500 1.2675 0.08511 0.07863 -0.0162 0.0231 1.0000
16.750 1.2623 0.08929 0.08295 -0.0172 0.0222 1.0000
17.000 1.2561 0.09368 0.08746 -0.0184 0.0214 1.0000
17.250 1.2495 0.09823 0.09212 -0.0198 0.0207 1.0000
17.500 1.2422 0.10293 0.09695 -0.0213 0.0201 1.0000
17.750 1.2340 0.10782 0.10193 -0.0231 0.0196 1.0000
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Polar data table (+)
Polar graphs
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