WORTMANN FX L V-152 AIRFOIL (fxlv152-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: WORTMANN FX L V-152 AIRFOIL (fxlv152-il) Reynolds number: 50,000 Max Cl/Cd: 27.06 at α=8° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fxlv152-il-50000.txt Download as CSV file: xf-fxlv152-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: WORTMANN FX L V-152 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
------ -------- --------- --------- -------- -------- --------
-12.000 -0.8847 0.08625 0.07967 -0.0143 1.0005 0.1504
-11.750 -0.9100 0.07922 0.07257 -0.0170 1.0005 0.1494
-11.500 -0.9396 0.07296 0.06617 -0.0188 1.0005 0.1483
-11.250 -0.9682 0.06775 0.06077 -0.0189 1.0005 0.1475
-11.000 -0.9882 0.06293 0.05564 -0.0184 1.0005 0.1475
-10.750 -1.0014 0.05844 0.05075 -0.0175 1.0005 0.1484
-10.500 -1.0108 0.05436 0.04612 -0.0162 1.0005 0.1502
-10.250 -0.9875 0.05126 0.04312 -0.0161 1.0005 0.1570
-10.000 -0.9831 0.04787 0.03927 -0.0150 1.0005 0.1623
-9.750 -0.9650 0.04473 0.03602 -0.0146 1.0005 0.1697
-9.500 -0.9515 0.04189 0.03279 -0.0137 1.0005 0.1784
-9.250 -0.9277 0.03953 0.03050 -0.0134 1.0005 0.1913
-9.000 -0.9091 0.03752 0.02848 -0.0127 1.0005 0.2078
-8.750 -0.8925 0.03564 0.02657 -0.0118 1.0005 0.2276
-8.500 -0.8685 0.03408 0.02538 -0.0112 1.0005 0.2508
-8.250 -0.8495 0.03238 0.02373 -0.0103 1.0005 0.2759
-8.000 -0.8279 0.03078 0.02243 -0.0092 1.0005 0.3069
-7.750 -0.8088 0.02953 0.02157 -0.0076 1.0005 0.3470
-7.500 -0.7876 0.02947 0.02202 -0.0052 1.0005 0.3961
-7.250 -0.7612 0.03087 0.02374 -0.0020 1.0005 0.4489
-7.000 -0.7155 0.03492 0.02786 0.0019 1.0005 0.4901
-6.750 -0.6798 0.03784 0.03066 0.0054 1.0005 0.5230
-6.500 -0.6233 0.04263 0.03523 0.0095 1.0005 0.5488
-6.250 -0.6079 0.04307 0.03557 0.0121 1.0005 0.5773
-6.000 -0.5538 0.04584 0.03809 0.0145 1.0005 0.5989
-5.750 -0.5111 0.04697 0.03903 0.0157 1.0005 0.6210
-5.500 -0.4852 0.04702 0.03896 0.0168 1.0005 0.6420
-5.250 -0.4798 0.04670 0.03859 0.0197 1.0005 0.6599
-5.000 -0.5080 0.04596 0.03789 0.0261 1.0005 0.6740
-4.750 -0.5277 0.04519 0.03712 0.0316 1.0005 0.6899
-4.500 -0.5140 0.04513 0.03695 0.0342 1.0005 0.7086
-4.250 -0.4996 0.04493 0.03666 0.0364 1.0005 0.7274
-4.000 -0.4923 0.04446 0.03611 0.0391 1.0005 0.7452
-3.750 -0.4974 0.04366 0.03525 0.0429 1.0005 0.7614
-3.500 -0.4862 0.04313 0.03462 0.0448 1.0005 0.7777
-3.250 -0.4569 0.04274 0.03411 0.0441 1.0005 0.7925
-3.000 -0.4388 0.04212 0.03339 0.0445 1.0005 0.8058
-2.750 -0.4451 0.04116 0.03237 0.0480 1.0005 0.8180
-2.500 -0.4088 0.04056 0.03162 0.0443 0.9939 0.8300
-2.250 -0.3566 0.04012 0.03104 0.0382 0.9879 0.8400
-2.000 -0.3471 0.03939 0.03021 0.0386 0.9802 0.8510
-1.750 -0.2691 0.03928 0.02995 0.0284 0.9741 0.8616
-1.500 -0.2389 0.03889 0.02947 0.0257 0.9675 0.8718
-1.250 -0.1979 0.03864 0.02915 0.0214 0.9608 0.8825
-1.000 -0.1296 0.03848 0.02891 0.0123 0.9547 0.8935
-0.750 -0.1248 0.03826 0.02867 0.0141 0.9470 0.9035
-0.500 -0.0560 0.03812 0.02849 0.0048 0.9410 0.9125
-0.250 -0.0444 0.03808 0.02843 0.0052 0.9346 0.9207
0.000 0.0044 0.03799 0.02834 -0.0008 0.9270 0.9270
0.250 0.0544 0.03804 0.02838 -0.0071 0.9204 0.9339
0.500 0.0641 0.03813 0.02850 -0.0063 0.9126 0.9409
0.750 0.1339 0.03819 0.02861 -0.0157 0.9035 0.9476
1.000 0.1377 0.03846 0.02890 -0.0138 0.8934 0.9543
1.250 0.2098 0.03853 0.02905 -0.0235 0.8825 0.9602
1.500 0.2472 0.03878 0.02938 -0.0272 0.8715 0.9675
1.750 0.2840 0.03913 0.02982 -0.0309 0.8613 0.9740
2.000 0.3453 0.03931 0.03013 -0.0386 0.8512 0.9802
2.250 0.3619 0.04002 0.03094 -0.0392 0.8407 0.9877
2.500 0.4263 0.04023 0.03132 -0.0470 0.8295 0.9939
2.750 0.4458 0.04101 0.03221 -0.0482 0.8175 0.9995
3.000 0.4440 0.04200 0.03328 -0.0454 0.8066 0.9995
3.250 0.4729 0.04247 0.03386 -0.0463 0.7928 0.9995
3.500 0.4884 0.04300 0.03449 -0.0451 0.7772 0.9995
3.750 0.4814 0.04388 0.03543 -0.0412 0.7615 0.9995
4.000 0.4756 0.04475 0.03635 -0.0374 0.7462 0.9995
4.250 0.4788 0.04537 0.03704 -0.0345 0.7293 0.9995
4.500 0.4891 0.04569 0.03745 -0.0320 0.7103 0.9995
4.750 0.4994 0.04588 0.03772 -0.0292 0.6912 0.9995
5.000 0.4949 0.04632 0.03821 -0.0251 0.6746 0.9995
5.250 0.4891 0.04671 0.03863 -0.0208 0.6588 0.9995
5.500 0.4936 0.04695 0.03893 -0.0175 0.6414 0.9995
5.750 0.5099 0.04712 0.03918 -0.0157 0.6208 0.9995
6.000 0.5417 0.04661 0.03883 -0.0144 0.5981 0.9995
6.250 0.5914 0.04444 0.03689 -0.0124 0.5751 0.9995
6.500 0.6508 0.04023 0.03292 -0.0090 0.5516 0.9995
6.750 0.6724 0.03875 0.03157 -0.0058 0.5209 0.9995
7.000 0.7184 0.03481 0.02777 -0.0021 0.4894 0.9995
7.250 0.7613 0.03114 0.02405 0.0016 0.4466 0.9995
7.500 0.7902 0.02948 0.02203 0.0048 0.3941 0.9995
8.000 0.8317 0.03074 0.02229 0.0088 0.3058 0.9995
8.250 0.8498 0.03243 0.02385 0.0100 0.2753 0.9995
8.500 0.8710 0.03408 0.02530 0.0109 0.2504 0.9995
8.750 0.8888 0.03580 0.02698 0.0119 0.2284 0.9995
9.000 0.9066 0.03752 0.02861 0.0128 0.2080 0.9995
9.250 0.9254 0.03947 0.03053 0.0136 0.1914 0.9995
9.500 0.9448 0.04197 0.03314 0.0142 0.1796 0.9995
9.750 0.9683 0.04471 0.03583 0.0145 0.1696 0.9995
10.000 0.9753 0.04777 0.03935 0.0157 0.1629 0.9995
10.250 0.9964 0.05079 0.04233 0.0160 0.1554 0.9995
10.500 0.9911 0.05445 0.04654 0.0176 0.1523 0.9995
10.750 0.9843 0.05841 0.05089 0.0188 0.1501 0.9995
11.000 0.9713 0.06272 0.05553 0.0198 0.1490 0.9995
11.250 0.9454 0.06746 0.06054 0.0206 0.1495 0.9995
11.500 0.9082 0.07345 0.06672 0.0196 0.1511 0.9995
11.750 0.8660 0.08123 0.07460 0.0163 0.1536 0.9995
12.000 0.8336 0.08969 0.08310 0.0123 0.1555 0.9995
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