FX 74-130 WP1 (fx74130wp1-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: FX 74-130 WP1 (fx74130wp1-il) Reynolds number: 50,000 Max Cl/Cd: 23.75 at α=9.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx74130wp1-il-50000-n5.txt Download as CSV file: xf-fx74130wp1-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: FX 74-130 WP1
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.3257 0.12155 0.11503 -0.0621 0.9675 0.1109
-9.500 -0.3264 0.11863 0.11215 -0.0639 0.9642 0.1152
-9.250 -0.3503 0.11709 0.11072 -0.0704 0.9597 0.1186
-9.000 -0.3285 0.11198 0.10555 -0.0692 0.9583 0.1205
-8.750 -0.3254 0.10906 0.10264 -0.0682 0.9548 0.1223
-8.500 -0.3244 0.10616 0.09976 -0.0684 0.9514 0.1242
-8.250 -0.3247 0.10301 0.09665 -0.0698 0.9481 0.1257
-8.000 -0.3313 0.09520 0.08877 -0.0767 0.9440 0.0677
-7.750 -0.3547 0.09202 0.08565 -0.0767 0.9379 0.0587
-7.500 -0.3594 0.08859 0.08222 -0.0771 0.9341 0.0561
-7.250 -0.3631 0.08403 0.07759 -0.0797 0.9304 0.0529
-7.000 -0.3906 0.08042 0.07368 -0.0788 0.9234 0.0482
-6.750 -0.3860 0.07724 0.07050 -0.0780 0.9205 0.0471
-6.500 -0.3808 0.07369 0.06685 -0.0784 0.9176 0.0461
-6.250 -0.3804 0.07056 0.06357 -0.0775 0.9139 0.0451
-6.000 -0.3812 0.06768 0.06049 -0.0758 0.9099 0.0443
-5.750 -0.3748 0.06443 0.05699 -0.0754 0.9068 0.0433
-5.500 -0.3621 0.06082 0.05304 -0.0757 0.9041 0.0427
-5.250 -0.3443 0.05752 0.04933 -0.0765 0.9017 0.0428
-5.000 -0.3377 0.05515 0.04663 -0.0745 0.8980 0.0434
-4.750 -0.3225 0.05262 0.04367 -0.0738 0.8951 0.0444
-4.500 -0.3019 0.05013 0.04071 -0.0737 0.8926 0.0452
-4.250 -0.2768 0.04767 0.03774 -0.0740 0.8904 0.0453
-4.000 -0.2483 0.04545 0.03503 -0.0746 0.8886 0.0455
-3.750 -0.2262 0.04377 0.03289 -0.0738 0.8861 0.0459
-3.500 -0.2062 0.04239 0.03115 -0.0725 0.8834 0.0467
-3.250 -0.1826 0.04131 0.02963 -0.0716 0.8809 0.0485
-3.000 -0.1587 0.04006 0.02837 -0.0714 0.8785 0.0528
-2.750 -0.1323 0.03926 0.02737 -0.0709 0.8764 0.0571
-2.500 -0.1046 0.03857 0.02641 -0.0702 0.8745 0.0607
-2.250 -0.0857 0.03797 0.02574 -0.0688 0.8718 0.0662
-2.000 -0.0694 0.03762 0.02523 -0.0670 0.8684 0.0760
-1.750 -0.0479 0.03705 0.02463 -0.0664 0.8654 0.0910
-1.500 0.0673 0.03511 0.02587 -0.0748 0.8705 0.9991
-1.250 0.0752 0.03529 0.02577 -0.0722 0.8661 1.0000
-1.000 0.0896 0.03551 0.02569 -0.0706 0.8626 1.0000
-0.750 0.1105 0.03578 0.02568 -0.0701 0.8597 1.0000
-0.500 0.1063 0.03593 0.02570 -0.0653 0.8539 1.0000
-0.250 0.1179 0.03616 0.02571 -0.0633 0.8497 1.0000
0.000 0.1380 0.03646 0.02580 -0.0626 0.8463 1.0000
0.250 0.1408 0.03666 0.02587 -0.0591 0.8410 1.0000
0.500 0.1519 0.03692 0.02598 -0.0569 0.8360 1.0000
0.750 0.1738 0.03729 0.02618 -0.0566 0.8324 1.0000
1.000 0.1842 0.03760 0.02635 -0.0544 0.8271 1.0000
1.250 0.1999 0.03797 0.02660 -0.0532 0.8220 1.0000
1.500 0.2259 0.03844 0.02694 -0.0536 0.8183 1.0000
1.750 0.2411 0.03888 0.02729 -0.0524 0.8128 1.0000
2.000 0.2609 0.03936 0.02767 -0.0520 0.8075 1.0000
2.250 0.2901 0.03991 0.02813 -0.0530 0.8037 1.0000
2.500 0.3044 0.04043 0.02860 -0.0518 0.7973 1.0000
2.750 0.3287 0.04097 0.02910 -0.0521 0.7921 1.0000
3.000 0.3614 0.04157 0.02965 -0.0535 0.7886 1.0000
3.250 0.3721 0.04212 0.03020 -0.0519 0.7804 1.0000
3.500 0.4022 0.04270 0.03077 -0.0530 0.7758 1.0000
3.750 0.4186 0.04331 0.03141 -0.0522 0.7684 1.0000
4.000 0.4461 0.04388 0.03200 -0.0529 0.7628 1.0000
4.250 0.4665 0.04450 0.03265 -0.0527 0.7557 1.0000
4.500 0.4924 0.04506 0.03326 -0.0532 0.7493 1.0000
4.750 0.5132 0.04567 0.03393 -0.0530 0.7417 1.0000
5.000 0.5405 0.04619 0.03456 -0.0536 0.7351 1.0000
5.250 0.5593 0.04681 0.03526 -0.0531 0.7264 1.0000
5.500 0.5910 0.04721 0.03577 -0.0542 0.7204 1.0000
5.750 0.6077 0.04783 0.03650 -0.0535 0.7103 1.0000
6.000 0.6334 0.04827 0.03711 -0.0537 0.7023 1.0000
6.250 0.6603 0.04862 0.03761 -0.0541 0.6940 1.0000
6.500 0.6792 0.04915 0.03828 -0.0535 0.6832 1.0000
6.750 0.7030 0.04951 0.03881 -0.0534 0.6734 1.0000
7.000 0.7361 0.04944 0.03901 -0.0541 0.6655 1.0000
7.250 0.7555 0.04980 0.03956 -0.0534 0.6530 1.0000
7.500 0.7769 0.05001 0.03998 -0.0528 0.6404 1.0000
7.750 0.7997 0.05006 0.04026 -0.0522 0.6272 1.0000
8.000 0.8234 0.04995 0.04044 -0.0515 0.6133 1.0000
8.250 0.8485 0.04955 0.04032 -0.0507 0.5983 1.0000
8.500 0.8771 0.04861 0.03968 -0.0497 0.5821 1.0000
8.750 0.8963 0.04808 0.03943 -0.0480 0.5603 1.0000
9.000 0.9236 0.04636 0.03806 -0.0460 0.5363 1.0000
9.250 0.9427 0.04522 0.03715 -0.0433 0.4991 1.0000
9.500 0.9723 0.04299 0.03495 -0.0406 0.4351 1.0000
9.750 0.9957 0.04192 0.03317 -0.0375 0.3215 1.0000
10.000 0.9928 0.04415 0.03476 -0.0348 0.2397 1.0000
10.250 0.9874 0.04700 0.03710 -0.0326 0.1805 1.0000
10.500 0.9852 0.04985 0.03963 -0.0309 0.1405 1.0000
10.750 0.9866 0.05252 0.04209 -0.0296 0.1143 1.0000
11.000 0.9914 0.05494 0.04440 -0.0284 0.0977 1.0000
11.250 0.9994 0.05716 0.04659 -0.0272 0.0867 1.0000
11.500 1.0123 0.05899 0.04854 -0.0262 0.0764 1.0000
11.750 1.0295 0.06059 0.05029 -0.0253 0.0680 1.0000
12.000 1.0595 0.06160 0.05125 -0.0246 0.0614 1.0000
12.250 1.0871 0.06310 0.05321 -0.0240 0.0546 1.0000
12.500 1.1257 0.06485 0.05495 -0.0241 0.0496 1.0000
12.750 1.1461 0.06777 0.05845 -0.0235 0.0466 1.0000
13.000 1.1540 0.07093 0.06199 -0.0227 0.0437 1.0000
13.250 1.1580 0.07415 0.06546 -0.0221 0.0415 1.0000
13.500 1.1621 0.07774 0.06930 -0.0215 0.0401 1.0000
13.750 1.1636 0.08188 0.07368 -0.0211 0.0392 1.0000
14.000 1.1576 0.08654 0.07859 -0.0207 0.0387 1.0000
14.250 1.1423 0.09136 0.08378 -0.0205 0.0384 1.0000
14.500 1.1251 0.09653 0.08927 -0.0209 0.0383 1.0000
14.750 1.1068 0.10210 0.09513 -0.0220 0.0382 1.0000
15.000 1.0875 0.10815 0.10143 -0.0239 0.0382 1.0000
15.250 1.0682 0.11468 0.10818 -0.0266 0.0383 1.0000
15.500 1.0490 0.12181 0.11550 -0.0301 0.0384 1.0000
15.750 1.0308 0.12944 0.12328 -0.0344 0.0386 1.0000
|
Polar data table (+)
Polar graphs
<< Back to FX 74-130 WP1 (fx74130wp1-il)