MB253515 15.0% smoothed (mb253515sm-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: MB253515 15.0% smoothed (mb253515sm-il) Reynolds number: 100,000 Max Cl/Cd: 49.01 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mb253515sm-il-100000-n5.txt Download as CSV file: xf-mb253515sm-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: MB253515 15.0% smoothed
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
------ -------- --------- --------- -------- -------- --------
-11.500 -0.4230 0.09564 0.09070 -0.0535 1.0000 0.0313
-11.250 -0.4413 0.08642 0.08155 -0.0587 1.0000 0.0310
-10.750 -0.5538 0.06523 0.05991 -0.0716 1.0000 0.0281
-10.500 -0.5746 0.06232 0.05693 -0.0698 1.0000 0.0280
-10.250 -0.5963 0.06011 0.05466 -0.0665 1.0000 0.0280
-10.000 -0.6233 0.05871 0.05323 -0.0609 1.0000 0.0280
-9.750 -0.6444 0.05690 0.05133 -0.0563 0.9968 0.0280
-9.500 -0.6402 0.05237 0.04649 -0.0579 0.9827 0.0286
-9.250 -0.6195 0.05003 0.04414 -0.0600 0.9738 0.0301
-9.000 -0.6047 0.04726 0.04111 -0.0610 0.9629 0.0314
-8.750 -0.5916 0.04412 0.03756 -0.0613 0.9519 0.0325
-8.500 -0.5764 0.04091 0.03387 -0.0613 0.9419 0.0334
-8.250 -0.5560 0.03807 0.03047 -0.0616 0.9338 0.0347
-8.000 -0.5384 0.03639 0.02817 -0.0606 0.9230 0.0366
-7.750 -0.5122 0.03347 0.02507 -0.0617 0.9167 0.0383
-7.500 -0.4877 0.03164 0.02304 -0.0617 0.9077 0.0395
-7.250 -0.4590 0.03010 0.02128 -0.0625 0.9011 0.0416
-7.000 -0.4334 0.02886 0.01982 -0.0624 0.8922 0.0443
-6.750 -0.4035 0.02751 0.01819 -0.0628 0.8854 0.0461
-6.500 -0.3757 0.02643 0.01687 -0.0629 0.8773 0.0473
-6.250 -0.3468 0.02485 0.01534 -0.0636 0.8709 0.0502
-6.000 -0.3225 0.02394 0.01441 -0.0632 0.8624 0.0527
-5.750 -0.2971 0.02306 0.01345 -0.0629 0.8555 0.0545
-5.500 -0.2757 0.02235 0.01266 -0.0619 0.8471 0.0562
-5.250 -0.2535 0.02171 0.01188 -0.0609 0.8401 0.0581
-5.000 -0.2336 0.02118 0.01124 -0.0596 0.8320 0.0609
-4.750 -0.2134 0.02052 0.01052 -0.0585 0.8253 0.0649
-4.500 -0.1934 0.02007 0.00996 -0.0571 0.8175 0.0688
-4.250 -0.1694 0.01963 0.00934 -0.0564 0.8117 0.0732
-4.000 -0.1507 0.01915 0.00887 -0.0549 0.8037 0.0818
-3.500 -0.1256 0.01690 0.00803 -0.0503 0.7902 0.3583
-3.250 -0.1109 0.01621 0.00792 -0.0477 0.7843 0.4933
-3.000 -0.0926 0.01596 0.00802 -0.0455 0.7780 0.5885
-2.750 -0.0705 0.01591 0.00809 -0.0439 0.7717 0.6493
-2.500 -0.0451 0.01593 0.00818 -0.0425 0.7671 0.7069
-2.250 -0.0243 0.01612 0.00842 -0.0405 0.7599 0.7500
-2.000 0.0025 0.01622 0.00845 -0.0397 0.7546 0.7779
-1.750 0.0315 0.01635 0.00849 -0.0395 0.7490 0.7978
-1.500 0.0585 0.01643 0.00849 -0.0391 0.7426 0.8126
-1.250 0.0889 0.01646 0.00840 -0.0394 0.7378 0.8267
-1.000 0.1149 0.01658 0.00845 -0.0390 0.7309 0.8406
-0.750 0.1474 0.01665 0.00842 -0.0396 0.7250 0.8523
-0.500 0.1799 0.01672 0.00840 -0.0404 0.7183 0.8631
-0.250 0.2105 0.01676 0.00836 -0.0408 0.7105 0.8745
0.000 0.2402 0.01679 0.00830 -0.0410 0.7031 0.8863
0.250 0.2775 0.01685 0.00829 -0.0428 0.6953 0.8946
0.500 0.3106 0.01691 0.00828 -0.0438 0.6882 0.9043
0.750 0.3444 0.01697 0.00829 -0.0451 0.6808 0.9134
1.000 0.3808 0.01702 0.00828 -0.0469 0.6740 0.9207
1.250 0.4140 0.01708 0.00832 -0.0481 0.6663 0.9291
1.500 0.4517 0.01711 0.00829 -0.0503 0.6596 0.9353
1.750 0.4862 0.01717 0.00835 -0.0519 0.6514 0.9428
2.000 0.5212 0.01719 0.00835 -0.0536 0.6442 0.9498
2.250 0.5560 0.01723 0.00840 -0.0553 0.6358 0.9570
2.500 0.5900 0.01727 0.00843 -0.0569 0.6276 0.9641
2.750 0.6248 0.01728 0.00845 -0.0586 0.6193 0.9711
3.000 0.6593 0.01733 0.00854 -0.0604 0.6098 0.9778
3.250 0.6939 0.01732 0.00852 -0.0620 0.6016 0.9847
3.500 0.7294 0.01735 0.00862 -0.0641 0.5909 0.9911
3.750 0.7647 0.01739 0.00870 -0.0662 0.5805 0.9977
4.000 0.7895 0.01741 0.00874 -0.0660 0.5713 1.0000
4.250 0.8041 0.01753 0.00891 -0.0638 0.5609 1.0000
4.500 0.8190 0.01766 0.00907 -0.0617 0.5507 1.0000
4.750 0.8353 0.01776 0.00918 -0.0597 0.5410 1.0000
5.000 0.8501 0.01792 0.00939 -0.0575 0.5303 1.0000
5.250 0.8646 0.01811 0.00962 -0.0553 0.5193 1.0000
5.500 0.8801 0.01829 0.00983 -0.0531 0.5087 1.0000
5.750 0.8968 0.01847 0.01000 -0.0512 0.4984 1.0000
6.000 0.9112 0.01873 0.01033 -0.0489 0.4871 1.0000
6.250 0.9266 0.01900 0.01067 -0.0468 0.4765 1.0000
6.500 0.9432 0.01927 0.01095 -0.0448 0.4665 1.0000
6.750 0.9592 0.01957 0.01130 -0.0428 0.4564 1.0000
7.000 0.9747 0.01992 0.01172 -0.0408 0.4464 1.0000
7.250 0.9921 0.02025 0.01209 -0.0390 0.4377 1.0000
7.500 1.0069 0.02061 0.01253 -0.0368 0.4269 1.0000
7.750 1.0184 0.02097 0.01291 -0.0341 0.4128 1.0000
8.000 1.0252 0.02134 0.01323 -0.0305 0.3939 1.0000
8.250 1.0270 0.02181 0.01365 -0.0261 0.3717 1.0000
8.500 1.0263 0.02237 0.01409 -0.0215 0.3500 1.0000
8.750 1.0250 0.02299 0.01470 -0.0169 0.3303 1.0000
9.000 1.0249 0.02373 0.01541 -0.0128 0.3102 1.0000
9.250 1.0243 0.02463 0.01633 -0.0091 0.2869 1.0000
9.500 1.0205 0.02583 0.01745 -0.0054 0.2543 1.0000
9.750 1.0090 0.02765 0.01899 -0.0013 0.1998 1.0000
10.000 0.9843 0.03074 0.02142 0.0029 0.1138 1.0000
10.250 0.9650 0.03399 0.02422 0.0061 0.0675 1.0000
10.500 0.9562 0.03668 0.02681 0.0083 0.0529 1.0000
10.750 0.9535 0.03900 0.02922 0.0099 0.0461 1.0000
11.000 0.9485 0.04163 0.03191 0.0113 0.0420 1.0000
11.250 0.9448 0.04426 0.03466 0.0123 0.0391 1.0000
11.500 0.9419 0.04691 0.03745 0.0131 0.0360 1.0000
11.750 0.9383 0.04973 0.04040 0.0137 0.0346 1.0000
12.000 0.9314 0.05302 0.04377 0.0141 0.0328 1.0000
12.250 0.9233 0.05655 0.04739 0.0144 0.0315 1.0000
12.500 0.9207 0.05962 0.05061 0.0145 0.0307 1.0000
12.750 0.9187 0.06265 0.05378 0.0146 0.0296 1.0000
13.000 0.9184 0.06548 0.05672 0.0148 0.0287 1.0000
13.250 0.9201 0.06807 0.05942 0.0150 0.0275 1.0000
13.500 0.9239 0.07038 0.06177 0.0153 0.0264 1.0000
13.750 0.9272 0.07267 0.06403 0.0155 0.0248 1.0000
14.000 0.9386 0.07385 0.06525 0.0166 0.0238 1.0000
14.250 0.9528 0.07486 0.06635 0.0177 0.0229 1.0000
14.500 0.9685 0.07581 0.06739 0.0190 0.0221 1.0000
14.750 0.9833 0.07707 0.06876 0.0200 0.0214 1.0000
15.000 0.9945 0.07890 0.07072 0.0206 0.0206 1.0000
15.250 1.0023 0.08119 0.07318 0.0208 0.0200 1.0000
15.500 1.0057 0.08396 0.07605 0.0205 0.0192 1.0000
15.750 1.0105 0.08664 0.07882 0.0203 0.0186 1.0000
16.000 1.0177 0.08926 0.08151 0.0205 0.0180 1.0000
16.250 1.0149 0.09317 0.08563 0.0197 0.0177 1.0000
16.500 1.0098 0.09748 0.09018 0.0186 0.0176 1.0000
16.750 1.0045 0.10187 0.09478 0.0172 0.0175 1.0000
17.000 0.9950 0.10703 0.10018 0.0152 0.0174 1.0000
17.250 0.9841 0.11253 0.10590 0.0128 0.0174 1.0000
17.500 0.9723 0.11837 0.11195 0.0101 0.0174 1.0000
17.750 0.9591 0.12466 0.11844 0.0068 0.0174 1.0000
18.000 0.9456 0.13127 0.12523 0.0032 0.0174 1.0000
18.250 0.9287 0.13895 0.13310 -0.0012 0.0174 1.0000
18.500 0.9145 0.14636 0.14066 -0.0056 0.0176 1.0000
18.750 0.9001 0.15416 0.14859 -0.0103 0.0177 1.0000
19.000 0.8826 0.16329 0.15783 -0.0158 0.0178 1.0000
19.250 0.8672 0.17257 0.16718 -0.0212 0.0179 1.0000
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Polar data table (+)
Polar graphs
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