GOE 180 (MVA H.26) AIRFOIL (goe180-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: GOE 180 (MVA H.26) AIRFOIL (goe180-il) Reynolds number: 100,000 Max Cl/Cd: 59.47 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe180-il-100000-n5.txt Download as CSV file: xf-goe180-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 180 (MVA H.26) 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.750 -0.3435 0.09481 0.09009 -0.0284 1.0000 0.0576
-7.500 -0.3539 0.09302 0.08842 -0.0321 1.0000 0.0585
-7.250 -0.3555 0.09019 0.08566 -0.0366 1.0000 0.0589
-7.000 -0.3533 0.08692 0.08240 -0.0396 1.0000 0.0590
-6.750 -0.3518 0.08289 0.07847 -0.0340 1.0000 0.0599
-6.500 -0.3489 0.08020 0.07583 -0.0315 1.0000 0.0609
-6.250 -0.3466 0.07762 0.07329 -0.0305 1.0000 0.0620
-6.000 -0.3437 0.07495 0.07066 -0.0305 1.0000 0.0632
-5.750 -0.2908 0.06880 0.06411 -0.0507 0.9915 0.0712
-5.500 -0.2683 0.05846 0.05368 -0.0551 0.9865 0.0492
-5.250 -0.2389 0.05421 0.04931 -0.0589 0.9798 0.0458
-5.000 -0.2006 0.04811 0.04289 -0.0664 0.9727 0.0462
-4.750 -0.1617 0.04228 0.03667 -0.0727 0.9661 0.0465
-4.500 -0.1266 0.03743 0.03140 -0.0769 0.9582 0.0460
-4.250 -0.0849 0.03237 0.02557 -0.0816 0.9527 0.0477
-4.000 -0.0505 0.02911 0.02171 -0.0838 0.9441 0.0481
-3.750 -0.0110 0.02630 0.01839 -0.0867 0.9388 0.0484
-3.500 0.0223 0.02432 0.01612 -0.0882 0.9296 0.0493
-3.250 0.0597 0.02310 0.01476 -0.0904 0.9226 0.0519
-3.000 0.0942 0.02172 0.01308 -0.0916 0.9128 0.0533
-2.750 0.1298 0.02037 0.01144 -0.0928 0.9029 0.0540
-2.500 0.1671 0.01919 0.01003 -0.0944 0.8936 0.0551
-2.250 0.1999 0.01829 0.00896 -0.0950 0.8804 0.0564
-2.000 0.2321 0.01753 0.00808 -0.0955 0.8662 0.0580
-1.750 0.2634 0.01692 0.00745 -0.0960 0.8507 0.0615
-1.500 0.2940 0.01643 0.00692 -0.0962 0.8333 0.0654
-1.250 0.3226 0.01598 0.00638 -0.0959 0.8130 0.0688
-1.000 0.3520 0.01555 0.00587 -0.0958 0.7922 0.0736
-0.750 0.3812 0.01520 0.00543 -0.0956 0.7707 0.0840
-0.500 0.4098 0.01483 0.00508 -0.0954 0.7487 0.1113
-0.250 0.4385 0.01444 0.00486 -0.0954 0.7273 0.1951
0.000 0.4602 0.01297 0.00488 -0.0943 0.7070 0.6675
0.250 0.4934 0.01253 0.00463 -0.0943 0.6870 1.0000
0.500 0.5211 0.01271 0.00453 -0.0940 0.6690 1.0000
0.750 0.5483 0.01291 0.00449 -0.0937 0.6523 1.0000
1.000 0.5753 0.01312 0.00448 -0.0933 0.6361 1.0000
1.250 0.6021 0.01334 0.00451 -0.0929 0.6212 1.0000
1.750 0.6555 0.01381 0.00466 -0.0922 0.5944 1.0000
2.000 0.6821 0.01405 0.00479 -0.0919 0.5825 1.0000
2.250 0.7087 0.01430 0.00492 -0.0915 0.5712 1.0000
2.500 0.7351 0.01457 0.00506 -0.0912 0.5603 1.0000
2.750 0.7614 0.01481 0.00525 -0.0908 0.5491 1.0000
3.000 0.7878 0.01507 0.00546 -0.0905 0.5393 1.0000
3.250 0.8144 0.01535 0.00567 -0.0902 0.5311 1.0000
3.500 0.8407 0.01561 0.00595 -0.0899 0.5217 1.0000
3.750 0.8668 0.01589 0.00619 -0.0895 0.5125 1.0000
4.000 0.8926 0.01617 0.00645 -0.0891 0.5022 1.0000
4.250 0.9183 0.01644 0.00676 -0.0887 0.4917 1.0000
4.500 0.9437 0.01672 0.00704 -0.0882 0.4810 1.0000
4.750 0.9688 0.01700 0.00731 -0.0876 0.4694 1.0000
5.000 0.9935 0.01727 0.00765 -0.0870 0.4563 1.0000
5.250 1.0181 0.01755 0.00798 -0.0864 0.4431 1.0000
5.500 1.0425 0.01784 0.00832 -0.0858 0.4298 1.0000
5.750 1.0666 0.01813 0.00869 -0.0851 0.4155 1.0000
6.000 1.0905 0.01844 0.00907 -0.0844 0.4009 1.0000
6.250 1.1141 0.01877 0.00947 -0.0836 0.3848 1.0000
6.500 1.1371 0.01912 0.00988 -0.0828 0.3671 1.0000
6.750 1.1595 0.01951 0.01032 -0.0819 0.3484 1.0000
7.000 1.1818 0.01994 0.01082 -0.0810 0.3282 1.0000
7.250 1.2032 0.02043 0.01133 -0.0800 0.3095 1.0000
7.500 1.2239 0.02101 0.01191 -0.0789 0.2930 1.0000
7.750 1.2442 0.02165 0.01259 -0.0777 0.2788 1.0000
8.000 1.2642 0.02234 0.01332 -0.0766 0.2664 1.0000
8.250 1.2839 0.02308 0.01413 -0.0754 0.2555 1.0000
8.500 1.3017 0.02390 0.01497 -0.0740 0.2413 1.0000
8.750 1.3171 0.02479 0.01586 -0.0724 0.2214 1.0000
9.000 1.3305 0.02575 0.01678 -0.0706 0.1997 1.0000
9.250 1.3471 0.02650 0.01767 -0.0692 0.1793 1.0000
9.500 1.3616 0.02737 0.01859 -0.0676 0.1574 1.0000
9.750 1.3719 0.02852 0.01966 -0.0655 0.1317 1.0000
10.000 1.3771 0.03006 0.02107 -0.0629 0.1040 1.0000
10.250 1.3749 0.03204 0.02279 -0.0594 0.0595 1.0000
10.500 1.3693 0.03441 0.02499 -0.0559 0.0463 1.0000
10.750 1.3672 0.03660 0.02729 -0.0530 0.0400 1.0000
11.000 1.3618 0.03917 0.02995 -0.0504 0.0363 1.0000
11.250 1.3605 0.04154 0.03250 -0.0485 0.0334 1.0000
11.500 1.3570 0.04425 0.03539 -0.0470 0.0313 1.0000
11.750 1.3513 0.04737 0.03868 -0.0459 0.0300 1.0000
12.000 1.3430 0.05101 0.04247 -0.0453 0.0290 1.0000
12.250 1.3324 0.05517 0.04678 -0.0452 0.0282 1.0000
12.500 1.3264 0.05902 0.05082 -0.0455 0.0274 1.0000
12.750 1.3199 0.06308 0.05508 -0.0460 0.0266 1.0000
13.000 1.3128 0.06734 0.05952 -0.0467 0.0257 1.0000
13.250 1.3053 0.07174 0.06408 -0.0475 0.0249 1.0000
13.500 1.2976 0.07623 0.06872 -0.0485 0.0242 1.0000
13.750 1.2898 0.08080 0.07342 -0.0495 0.0235 1.0000
14.000 1.2823 0.08537 0.07811 -0.0506 0.0229 1.0000
14.250 1.2755 0.08984 0.08268 -0.0517 0.0223 1.0000
|
Polar data table (+)
Polar graphs
<< Back to GOE 180 (MVA H.26) AIRFOIL (goe180-il)