MB253515 15.0% smoothed (mb253515sm-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: MB253515 15.0% smoothed (mb253515sm-il) Reynolds number: 200,000 Max Cl/Cd: 68.32 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mb253515sm-il-200000-n5.txt Download as CSV file: xf-mb253515sm-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.250 -0.4386 0.10042 0.09685 -0.0490 1.0000 0.0172
-12.000 -0.5743 0.06367 0.05982 -0.0712 1.0000 0.0158
-11.750 -0.6016 0.05781 0.05379 -0.0739 1.0000 0.0158
-11.500 -0.6259 0.05334 0.04914 -0.0744 1.0000 0.0157
-11.250 -0.6464 0.05007 0.04574 -0.0733 1.0000 0.0158
-11.000 -0.6619 0.04781 0.04340 -0.0709 1.0000 0.0159
-10.750 -0.6803 0.04584 0.04132 -0.0671 1.0000 0.0160
-10.500 -0.6849 0.04486 0.04032 -0.0643 0.9943 0.0162
-10.250 -0.6742 0.04267 0.03795 -0.0651 0.9775 0.0166
-10.000 -0.6554 0.04086 0.03594 -0.0666 0.9643 0.0173
-9.750 -0.6385 0.03856 0.03337 -0.0676 0.9508 0.0182
-9.500 -0.6236 0.03544 0.02981 -0.0679 0.9374 0.0193
-9.250 -0.6081 0.03207 0.02583 -0.0677 0.9245 0.0205
-9.000 -0.5875 0.02970 0.02302 -0.0678 0.9127 0.0215
-8.750 -0.5624 0.02850 0.02172 -0.0686 0.9019 0.0224
-8.500 -0.5397 0.02772 0.02081 -0.0685 0.8899 0.0238
-8.250 -0.5178 0.02648 0.01933 -0.0680 0.8786 0.0250
-8.000 -0.4955 0.02519 0.01775 -0.0674 0.8684 0.0264
-7.750 -0.4730 0.02437 0.01664 -0.0666 0.8586 0.0278
-7.500 -0.4508 0.02292 0.01507 -0.0661 0.8489 0.0293
-7.250 -0.4277 0.02200 0.01407 -0.0656 0.8404 0.0305
-7.000 -0.4049 0.02120 0.01317 -0.0649 0.8315 0.0316
-6.750 -0.3822 0.02056 0.01241 -0.0642 0.8235 0.0335
-6.500 -0.3591 0.01993 0.01164 -0.0635 0.8154 0.0350
-6.250 -0.3362 0.01928 0.01088 -0.0627 0.8078 0.0360
-6.000 -0.3135 0.01870 0.01018 -0.0619 0.8004 0.0367
-5.750 -0.2944 0.01777 0.00924 -0.0606 0.7934 0.0384
-5.500 -0.2740 0.01722 0.00866 -0.0594 0.7861 0.0401
-5.250 -0.2531 0.01674 0.00809 -0.0583 0.7797 0.0416
-5.000 -0.2324 0.01629 0.00758 -0.0571 0.7727 0.0428
-4.500 -0.1892 0.01556 0.00666 -0.0550 0.7601 0.0456
-4.250 -0.1662 0.01528 0.00625 -0.0542 0.7542 0.0471
-4.000 -0.1444 0.01490 0.00581 -0.0531 0.7484 0.0506
-3.750 -0.1215 0.01461 0.00546 -0.0523 0.7422 0.0544
-3.500 -0.0974 0.01437 0.00511 -0.0516 0.7372 0.0592
-3.250 -0.0754 0.01402 0.00481 -0.0506 0.7309 0.0744
-3.000 -0.0658 0.01270 0.00437 -0.0479 0.7253 0.2770
-2.750 -0.0496 0.01206 0.00417 -0.0460 0.7202 0.3917
-2.500 -0.0324 0.01160 0.00407 -0.0441 0.7141 0.4828
-2.250 -0.0129 0.01129 0.00402 -0.0423 0.7091 0.5606
-2.000 0.0073 0.01108 0.00406 -0.0406 0.7038 0.6336
-1.750 0.0295 0.01099 0.00412 -0.0393 0.6980 0.6864
-1.500 0.0548 0.01096 0.00408 -0.0386 0.6931 0.7138
-1.250 0.0796 0.01095 0.00409 -0.0378 0.6861 0.7372
-1.000 0.1043 0.01094 0.00405 -0.0369 0.6786 0.7632
-0.750 0.1296 0.01094 0.00408 -0.0362 0.6703 0.7841
-0.500 0.1560 0.01095 0.00403 -0.0358 0.6635 0.7981
-0.250 0.1821 0.01097 0.00403 -0.0354 0.6569 0.8112
0.000 0.2086 0.01100 0.00402 -0.0350 0.6506 0.8242
0.250 0.2367 0.01104 0.00403 -0.0350 0.6450 0.8358
0.500 0.2642 0.01108 0.00407 -0.0349 0.6383 0.8472
0.750 0.2923 0.01113 0.00407 -0.0350 0.6328 0.8589
1.000 0.3195 0.01118 0.00413 -0.0348 0.6259 0.8712
1.250 0.3503 0.01125 0.00418 -0.0354 0.6195 0.8814
1.500 0.3810 0.01133 0.00425 -0.0360 0.6128 0.8912
1.750 0.4095 0.01140 0.00430 -0.0362 0.6058 0.9016
2.000 0.4436 0.01149 0.00439 -0.0376 0.5985 0.9085
2.250 0.4732 0.01157 0.00445 -0.0381 0.5909 0.9176
2.500 0.5079 0.01168 0.00456 -0.0397 0.5833 0.9236
2.750 0.5376 0.01177 0.00463 -0.0402 0.5751 0.9322
3.000 0.5732 0.01188 0.00476 -0.0420 0.5660 0.9372
3.250 0.6043 0.01199 0.00484 -0.0429 0.5577 0.9446
3.500 0.6385 0.01210 0.00498 -0.0444 0.5475 0.9498
3.750 0.6726 0.01223 0.00511 -0.0460 0.5372 0.9550
4.000 0.7029 0.01236 0.00523 -0.0468 0.5268 0.9619
4.250 0.7376 0.01250 0.00539 -0.0485 0.5150 0.9664
4.500 0.7674 0.01266 0.00556 -0.0492 0.5027 0.9735
4.750 0.8020 0.01282 0.00573 -0.0510 0.4896 0.9779
5.000 0.8332 0.01300 0.00594 -0.0521 0.4768 0.9842
5.250 0.8669 0.01320 0.00613 -0.0538 0.4631 0.9889
5.500 0.8990 0.01343 0.00637 -0.0552 0.4490 0.9943
5.750 0.9327 0.01366 0.00662 -0.0570 0.4356 0.9992
6.000 0.9497 0.01390 0.00686 -0.0552 0.4246 1.0000
6.250 0.9633 0.01413 0.00711 -0.0528 0.4138 1.0000
6.500 0.9757 0.01440 0.00737 -0.0501 0.4012 1.0000
6.750 0.9853 0.01475 0.00765 -0.0469 0.3842 1.0000
7.000 0.9929 0.01515 0.00795 -0.0434 0.3651 1.0000
7.250 1.0007 0.01556 0.00832 -0.0399 0.3449 1.0000
7.500 1.0082 0.01600 0.00869 -0.0364 0.3266 1.0000
7.750 1.0152 0.01646 0.00910 -0.0329 0.3092 1.0000
8.000 1.0198 0.01693 0.00952 -0.0289 0.2916 1.0000
8.250 1.0225 0.01740 0.00996 -0.0246 0.2703 1.0000
8.500 1.0224 0.01806 0.01051 -0.0201 0.2422 1.0000
8.750 1.0162 0.01912 0.01132 -0.0151 0.1980 1.0000
9.000 0.9939 0.02125 0.01289 -0.0088 0.1160 1.0000
9.250 0.9757 0.02360 0.01485 -0.0038 0.0571 1.0000
9.500 0.9746 0.02518 0.01636 -0.0010 0.0401 1.0000
9.750 0.9771 0.02664 0.01785 0.0013 0.0321 1.0000
10.000 0.9829 0.02795 0.01924 0.0031 0.0279 1.0000
10.250 0.9864 0.02950 0.02085 0.0049 0.0254 1.0000
10.500 0.9892 0.03116 0.02261 0.0065 0.0235 1.0000
10.750 0.9937 0.03278 0.02434 0.0079 0.0221 1.0000
11.000 0.9976 0.03449 0.02614 0.0091 0.0203 1.0000
11.250 0.9993 0.03645 0.02818 0.0102 0.0191 1.0000
11.500 0.9957 0.03895 0.03076 0.0114 0.0181 1.0000
11.750 0.9954 0.04125 0.03315 0.0123 0.0178 1.0000
12.000 0.9954 0.04360 0.03562 0.0131 0.0173 1.0000
12.250 0.9951 0.04607 0.03822 0.0138 0.0167 1.0000
12.500 0.9951 0.04859 0.04084 0.0143 0.0163 1.0000
12.750 0.9952 0.05116 0.04350 0.0147 0.0158 1.0000
13.000 0.9957 0.05373 0.04616 0.0151 0.0154 1.0000
13.250 0.9982 0.05618 0.04868 0.0152 0.0145 1.0000
13.500 0.9995 0.05876 0.05133 0.0154 0.0143 1.0000
13.750 1.0010 0.06140 0.05401 0.0154 0.0136 1.0000
14.000 1.0022 0.06403 0.05670 0.0156 0.0132 1.0000
14.250 1.0036 0.06655 0.05926 0.0160 0.0128 1.0000
14.500 1.0087 0.06873 0.06151 0.0164 0.0125 1.0000
14.750 1.0143 0.07095 0.06386 0.0166 0.0122 1.0000
15.000 1.0205 0.07310 0.06611 0.0169 0.0120 1.0000
15.250 1.0267 0.07526 0.06839 0.0172 0.0117 1.0000
15.500 1.0322 0.07760 0.07085 0.0174 0.0114 1.0000
15.750 1.0372 0.08003 0.07341 0.0175 0.0112 1.0000
16.000 1.0409 0.08270 0.07621 0.0175 0.0110 1.0000
16.250 1.0421 0.08579 0.07944 0.0169 0.0106 1.0000
16.500 1.0423 0.08910 0.08289 0.0161 0.0103 1.0000
16.750 1.0431 0.09237 0.08631 0.0156 0.0103 1.0000
17.000 1.0409 0.09612 0.09019 0.0143 0.0100 1.0000
17.250 1.0381 0.10002 0.09423 0.0130 0.0098 1.0000
17.500 1.0364 0.10375 0.09800 0.0113 0.0094 1.0000
17.750 1.0314 0.10821 0.10267 0.0099 0.0094 1.0000
18.000 1.0276 0.11244 0.10700 0.0081 0.0093 1.0000
18.250 1.0210 0.11725 0.11195 0.0061 0.0091 1.0000
18.500 1.0132 0.12239 0.11724 0.0038 0.0090 1.0000
18.750 1.0039 0.12805 0.12307 0.0010 0.0090 1.0000
19.000 0.9921 0.13435 0.12955 -0.0023 0.0090 1.0000
19.250 0.9794 0.14107 0.13645 -0.0060 0.0090 1.0000
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Polar data table (+)
Polar graphs
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