WORTMANN FX 082-512 AIRFOIL (fx082512-il) Xfoil prediction polar at RE=50,000 Ncrit=9
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Airfoil: WORTMANN FX 082-512 AIRFOIL (fx082512-il) Reynolds number: 50,000 Max Cl/Cd: 31.2 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx082512-il-50000.txt Download as CSV file: xf-fx082512-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: WORTMANN FX 082-512 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.4087 0.11069 0.10313 -0.0221 1.0000 0.2947
-8.250 -0.4852 0.09611 0.08884 -0.0317 1.0000 0.1931
-8.000 -0.6296 0.07246 0.06587 -0.0474 1.0000 0.1585
-7.750 -0.6494 0.06238 0.05576 -0.0553 1.0000 0.1564
-7.500 -0.6505 0.04472 0.03719 -0.0798 1.0000 0.1549
-7.250 -0.6267 0.04052 0.03268 -0.0836 1.0000 0.1628
-7.000 -0.5956 0.03654 0.02821 -0.0885 1.0000 0.1728
-6.750 -0.5761 0.03563 0.02749 -0.0868 1.0000 0.1829
-6.500 -0.5533 0.03459 0.02652 -0.0863 1.0000 0.1936
-6.250 -0.5301 0.03403 0.02607 -0.0855 1.0000 0.2061
-6.000 -0.5076 0.03387 0.02601 -0.0842 1.0000 0.2184
-5.750 -0.4903 0.03498 0.02728 -0.0807 1.0000 0.2324
-5.500 -0.4733 0.03624 0.02861 -0.0770 1.0000 0.2468
-5.250 -0.4478 0.03650 0.02875 -0.0764 1.0000 0.2712
-5.000 -0.4288 0.03806 0.03028 -0.0732 1.0000 0.3007
-4.750 -0.4161 0.04026 0.03246 -0.0678 1.0000 0.3319
-4.500 -0.4066 0.04229 0.03445 -0.0615 1.0000 0.3628
-4.250 -0.3991 0.04391 0.03600 -0.0550 1.0000 0.3882
-4.000 -0.3920 0.04505 0.03709 -0.0488 1.0000 0.4102
-3.750 -0.3799 0.04589 0.03780 -0.0447 1.0000 0.4381
-3.500 -0.3811 0.04692 0.03890 -0.0359 1.0000 0.4571
-3.250 -0.3772 0.04752 0.03946 -0.0292 1.0000 0.4796
-3.000 -0.3604 0.04726 0.03905 -0.0280 1.0000 0.5017
-2.750 -0.3492 0.04699 0.03871 -0.0246 1.0000 0.5179
-2.500 -0.3325 0.04651 0.03813 -0.0234 1.0000 0.5330
-2.250 -0.3233 0.04606 0.03764 -0.0195 1.0000 0.5446
-2.000 -0.3093 0.04561 0.03712 -0.0175 1.0000 0.5613
-1.750 -0.2966 0.04508 0.03655 -0.0150 1.0000 0.5756
-1.500 -0.2816 0.04446 0.03588 -0.0135 1.0000 0.5880
-1.250 -0.2645 0.04385 0.03522 -0.0126 1.0000 0.6015
-1.000 -0.2429 0.04326 0.03455 -0.0132 1.0000 0.6141
-0.750 -0.2231 0.04262 0.03386 -0.0133 1.0000 0.6218
-0.500 -0.1909 0.04190 0.03305 -0.0172 1.0000 0.6226
-0.250 -0.1523 0.04113 0.03214 -0.0230 1.0000 0.6168
0.000 -0.1046 0.04055 0.03139 -0.0313 1.0000 0.6099
0.250 -0.0728 0.04005 0.03085 -0.0348 1.0000 0.6081
0.500 -0.0396 0.03969 0.03042 -0.0386 1.0000 0.6069
0.750 -0.0061 0.03942 0.03012 -0.0425 1.0000 0.6057
1.000 0.0279 0.03925 0.02991 -0.0465 1.0000 0.6042
1.250 0.0614 0.03919 0.02983 -0.0504 1.0000 0.6032
1.500 0.0924 0.03924 0.02988 -0.0535 1.0000 0.6040
1.750 0.1227 0.03941 0.03005 -0.0565 1.0000 0.6054
2.000 0.1528 0.03967 0.03034 -0.0596 1.0000 0.6069
2.250 0.1827 0.04003 0.03073 -0.0626 1.0000 0.6080
2.500 0.2122 0.04049 0.03123 -0.0655 1.0000 0.6090
2.750 0.2416 0.04108 0.03188 -0.0686 1.0000 0.6110
3.000 0.2647 0.04168 0.03259 -0.0700 1.0000 0.6138
3.250 0.2876 0.04241 0.03344 -0.0715 1.0000 0.6169
3.500 0.3114 0.04329 0.03443 -0.0734 1.0000 0.6202
3.750 0.4119 0.04535 0.03667 -0.0885 0.9618 0.6270
4.000 0.5179 0.04507 0.03674 -0.1009 0.9126 0.6365
4.250 0.5912 0.04437 0.03633 -0.1080 0.8826 0.6457
4.500 0.6577 0.04262 0.03494 -0.1124 0.8479 0.6546
4.750 0.7301 0.04025 0.03300 -0.1168 0.8201 0.6641
5.000 0.8157 0.03468 0.02806 -0.1186 0.7741 0.6787
5.250 0.8706 0.02937 0.02322 -0.1144 0.6923 0.6920
5.500 0.9058 0.02903 0.02026 -0.1087 0.2969 0.7030
5.750 0.9195 0.03104 0.02167 -0.1067 0.2439 0.7115
6.000 0.9457 0.03257 0.02293 -0.1064 0.2139 0.7235
6.250 0.9888 0.03399 0.02429 -0.1083 0.1901 0.7412
6.500 1.0602 0.03629 0.02635 -0.1146 0.1649 0.7701
6.750 1.1119 0.03878 0.02894 -0.1177 0.1502 0.8033
7.000 1.1415 0.04067 0.03127 -0.1169 0.1424 0.8502
7.250 1.1806 0.04388 0.03476 -0.1190 0.1350 1.0000
7.500 1.2229 0.04806 0.03937 -0.1220 0.1311 1.0000
7.750 1.2495 0.05196 0.04360 -0.1219 0.1287 1.0000
8.000 1.2698 0.05586 0.04778 -0.1208 0.1263 1.0000
8.250 1.2784 0.05997 0.05251 -0.1177 0.1285 1.0000
8.500 1.2831 0.06469 0.05777 -0.1146 0.1327 1.0000
8.750 1.2936 0.07001 0.06335 -0.1128 0.1362 1.0000
9.000 1.2727 0.07437 0.06854 -0.1073 0.1439 1.0000
9.250 1.2677 0.08012 0.07458 -0.1048 0.1497 1.0000
9.500 1.2282 0.08525 0.08026 -0.1000 0.1588 1.0000
10.000 1.0881 0.09421 0.08997 -0.0837 0.1667 1.0000
10.250 1.0229 0.10075 0.09670 -0.0830 0.1661 1.0000
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Polar data table (+)
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