MILEY M06-13-128 (miley-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: MILEY M06-13-128 (miley-il) Reynolds number: 200,000 Max Cl/Cd: 61.24 at α=10.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-miley-il-200000.txt Download as CSV file: xf-miley-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: MILEY M06-13-128
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.2988 0.12341 0.11921 -0.0068 0.6256 0.0246
-9.750 -0.2951 0.12084 0.11665 -0.0095 0.6254 0.0249
-9.500 -0.2919 0.11824 0.11411 -0.0125 0.6252 0.0252
-9.250 -0.2873 0.11539 0.11129 -0.0150 0.6250 0.0253
-9.000 -0.2831 0.11244 0.10839 -0.0176 0.6248 0.0255
-8.750 -0.2775 0.10945 0.10543 -0.0199 0.6246 0.0255
-8.500 -0.2723 0.10635 0.10238 -0.0222 0.6243 0.0256
-8.250 -0.2677 0.10316 0.09924 -0.0248 0.6239 0.0256
-8.000 -0.2596 0.09702 0.09312 -0.0230 0.6233 0.0267
-7.750 -0.2510 0.09401 0.09014 -0.0236 0.6226 0.0273
-7.500 -0.2440 0.09114 0.08730 -0.0248 0.6223 0.0279
-7.250 -0.2390 0.08816 0.08438 -0.0265 0.6221 0.0288
-7.000 -0.2364 0.08537 0.08164 -0.0284 0.6219 0.0293
-6.750 -0.2368 0.08268 0.07899 -0.0306 0.6217 0.0298
-6.500 -0.2312 0.07953 0.07587 -0.0339 0.6215 0.0305
-6.250 -0.2235 0.07619 0.07253 -0.0374 0.6212 0.0314
-6.000 -0.2136 0.07268 0.06898 -0.0411 0.6205 0.0326
-5.750 -0.2001 0.06910 0.06532 -0.0450 0.6198 0.0340
-5.500 -0.1790 0.06634 0.06223 -0.0496 0.6192 0.0357
-5.250 -0.1619 0.06396 0.05961 -0.0511 0.6189 0.0360
-5.000 -0.1546 0.05766 0.05339 -0.0524 0.6186 0.0373
-4.750 -0.1391 0.05524 0.05099 -0.0528 0.6183 0.0389
-4.500 -0.1210 0.05300 0.04865 -0.0533 0.6176 0.0411
-4.250 -0.1006 0.05061 0.04604 -0.0537 0.6167 0.0448
-4.000 -0.0793 0.04799 0.04281 -0.0535 0.6158 0.0496
-3.750 -0.0616 0.04548 0.04038 -0.0536 0.6152 0.0519
-3.500 -0.0386 0.04397 0.03878 -0.0543 0.6147 0.0571
-3.250 -0.0155 0.04203 0.03654 -0.0549 0.6140 0.0651
-3.000 0.0091 0.04158 0.03575 -0.0555 0.6126 0.0774
-2.750 0.0309 0.03959 0.03391 -0.0565 0.6120 0.0830
-2.500 0.0537 0.03879 0.03300 -0.0572 0.6111 0.0992
-2.250 0.0743 0.03807 0.03226 -0.0578 0.6094 0.1259
-1.750 0.1395 0.03336 0.02612 -0.0549 0.6076 0.0406
-1.500 0.1666 0.03313 0.02556 -0.0539 0.6056 0.0363
-1.250 0.1921 0.03195 0.02419 -0.0523 0.6035 0.0358
-1.000 0.2167 0.03076 0.02285 -0.0499 0.6017 0.0362
-0.750 0.2372 0.03118 0.02344 -0.0517 0.5992 0.0414
-0.500 0.2567 0.03217 0.02449 -0.0531 0.5964 0.0450
-0.250 0.2758 0.03278 0.02509 -0.0533 0.5942 0.0494
0.000 0.2995 0.03231 0.02456 -0.0517 0.5908 0.0654
0.250 0.4080 0.02806 0.02276 -0.0637 0.5883 1.0000
0.500 0.4242 0.03028 0.02499 -0.0662 0.5820 1.0000
0.750 0.4448 0.03088 0.02547 -0.0655 0.5782 1.0000
1.000 0.4686 0.03080 0.02522 -0.0637 0.5758 1.0000
1.250 0.4932 0.03060 0.02485 -0.0616 0.5743 1.0000
1.500 0.5179 0.03047 0.02455 -0.0594 0.5733 1.0000
1.750 0.5289 0.03284 0.02702 -0.0620 0.5625 1.0000
2.000 0.5550 0.03257 0.02662 -0.0602 0.5609 1.0000
2.250 0.5813 0.03230 0.02623 -0.0583 0.5598 1.0000
2.500 0.5909 0.03438 0.02836 -0.0596 0.5487 1.0000
2.750 0.6182 0.03404 0.02793 -0.0580 0.5473 1.0000
3.000 0.6455 0.03372 0.02752 -0.0565 0.5462 1.0000
3.250 0.6732 0.03337 0.02708 -0.0549 0.5454 1.0000
3.500 0.6820 0.03532 0.02911 -0.0559 0.5336 1.0000
3.750 0.7044 0.03560 0.02935 -0.0550 0.5299 1.0000
4.000 0.7402 0.03422 0.02787 -0.0530 0.5319 1.0000
4.250 0.7483 0.03610 0.02983 -0.0537 0.5200 1.0000
4.500 0.7781 0.03547 0.02917 -0.0524 0.5191 1.0000
4.750 0.8082 0.03478 0.02843 -0.0512 0.5184 1.0000
5.000 0.8141 0.03687 0.03061 -0.0518 0.5066 1.0000
5.250 0.8304 0.03776 0.03153 -0.0515 0.5005 1.0000
5.500 0.8741 0.03556 0.02931 -0.0497 0.5050 1.0000
5.750 0.9044 0.03487 0.02860 -0.0487 0.5044 1.0000
6.000 0.8930 0.03868 0.03254 -0.0499 0.4866 1.0000
6.250 0.9332 0.03691 0.03078 -0.0485 0.4891 1.0000
6.500 0.9691 0.03554 0.02945 -0.0474 0.4901 1.0000
6.750 1.0042 0.03424 0.02816 -0.0464 0.4909 1.0000
7.000 0.9813 0.03901 0.03306 -0.0478 0.4692 1.0000
7.250 1.0140 0.03798 0.03209 -0.0470 0.4680 1.0000
7.500 1.0475 0.03681 0.03100 -0.0461 0.4671 1.0000
7.750 1.0814 0.03553 0.02980 -0.0453 0.4664 1.0000
8.000 1.1159 0.03415 0.02849 -0.0444 0.4658 1.0000
8.250 1.1501 0.03271 0.02717 -0.0436 0.4650 1.0000
8.500 1.1461 0.03547 0.03002 -0.0442 0.4502 1.0000
8.750 1.1886 0.03317 0.02785 -0.0433 0.4512 1.0000
9.000 1.2291 0.03092 0.02572 -0.0423 0.4519 1.0000
9.250 1.2383 0.03229 0.02719 -0.0428 0.4409 1.0000
9.500 1.2798 0.02998 0.02505 -0.0420 0.4402 1.0000
9.750 1.3239 0.02734 0.02256 -0.0410 0.4394 1.0000
10.000 1.3404 0.02797 0.02331 -0.0412 0.4277 1.0000
10.250 1.3689 0.02714 0.02259 -0.0407 0.4172 1.0000
10.500 1.4227 0.02323 0.01864 -0.0393 0.4001 1.0000
10.750 1.4296 0.02401 0.01914 -0.0380 0.3636 1.0000
11.000 1.4140 0.02701 0.02193 -0.0365 0.3380 1.0000
11.250 1.4055 0.02963 0.02441 -0.0353 0.3183 1.0000
11.500 1.3942 0.03259 0.02725 -0.0343 0.2978 1.0000
11.750 1.3867 0.03526 0.02984 -0.0333 0.2808 1.0000
12.000 1.3744 0.03835 0.03278 -0.0323 0.2606 1.0000
12.250 1.3672 0.04111 0.03551 -0.0315 0.2435 1.0000
12.500 1.3585 0.04404 0.03839 -0.0308 0.2249 1.0000
12.750 1.3426 0.04780 0.04200 -0.0302 0.1980 1.0000
13.000 1.3225 0.05231 0.04626 -0.0299 0.1592 1.0000
13.250 1.2977 0.05752 0.05108 -0.0297 0.1125 1.0000
13.500 1.2702 0.06321 0.05635 -0.0295 0.0687 1.0000
13.750 1.2511 0.06823 0.06112 -0.0296 0.0406 1.0000
14.000 1.2307 0.07373 0.06649 -0.0298 0.0264 1.0000
14.250 1.2205 0.07821 0.07106 -0.0301 0.0214 1.0000
14.500 1.2044 0.08366 0.07659 -0.0307 0.0184 1.0000
14.750 1.1995 0.08765 0.08073 -0.0312 0.0173 1.0000
15.000 1.1939 0.09185 0.08505 -0.0319 0.0162 1.0000
15.250 1.1895 0.09588 0.08920 -0.0326 0.0157 1.0000
15.500 1.1841 0.10008 0.09349 -0.0333 0.0149 1.0000
15.750 1.1753 0.10476 0.09820 -0.0343 0.0133 1.0000
|
Polar data table (+)
Polar graphs
<< Back to MILEY M06-13-128 (miley-il)