FX S 02/1-158 AIRFOIL (fxs21158-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: FX S 02/1-158 AIRFOIL (fxs21158-il) Reynolds number: 200,000 Max Cl/Cd: 76.76 at α=9° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fxs21158-il-200000.txt Download as CSV file: xf-fxs21158-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: FX S 02/1-158 AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-11.500 -0.3452 0.11767 0.11447 -0.0359 1.0000 0.0425
-11.250 -0.3484 0.11260 0.10945 -0.0396 1.0000 0.0428
-11.000 -0.3506 0.10730 0.10421 -0.0428 1.0000 0.0429
-10.750 -0.3521 0.10161 0.09858 -0.0428 1.0000 0.0439
-10.500 -0.3337 0.10139 0.09838 -0.0395 1.0000 0.0464
-10.250 -0.3311 0.09781 0.09486 -0.0407 1.0000 0.0488
-10.000 -0.2244 0.07446 0.07130 -0.0662 0.8070 0.0684
-9.750 -0.2439 0.06593 0.06270 -0.0717 0.7867 0.0682
-9.500 -0.2556 0.05993 0.05657 -0.0747 0.7634 0.0686
-9.250 -0.2352 0.06127 0.05772 -0.0710 0.7296 0.0819
-9.000 -0.3754 0.05236 0.04872 -0.0912 0.8123 0.0393
-8.750 -0.3983 0.04628 0.04210 -0.0929 0.7776 0.0365
-8.500 -0.4027 0.04227 0.03759 -0.0929 0.7506 0.0373
-8.250 -0.3984 0.03923 0.03400 -0.0925 0.7291 0.0403
-8.000 -0.3930 0.03630 0.03037 -0.0923 0.7118 0.0446
-7.000 -0.3143 0.02993 0.02260 -0.0913 0.6603 0.0555
-6.750 -0.2903 0.02824 0.02058 -0.0909 0.6510 0.0554
-6.500 -0.2639 0.02745 0.01954 -0.0905 0.6416 0.0544
-6.250 -0.2392 0.02507 0.01696 -0.0902 0.6350 0.0537
-6.000 -0.2135 0.02352 0.01522 -0.0899 0.6274 0.0533
-5.750 -0.1874 0.02235 0.01383 -0.0895 0.6215 0.0533
-5.500 -0.1612 0.02134 0.01271 -0.0892 0.6148 0.0535
-5.250 -0.1351 0.02051 0.01175 -0.0888 0.6090 0.0538
-5.000 -0.1089 0.01985 0.01098 -0.0884 0.6035 0.0544
-4.750 -0.0847 0.01875 0.00994 -0.0880 0.5979 0.0562
-4.500 -0.0592 0.01808 0.00924 -0.0878 0.5935 0.0580
-4.250 -0.0333 0.01752 0.00864 -0.0877 0.5889 0.0593
-4.000 -0.0067 0.01699 0.00807 -0.0877 0.5842 0.0613
-3.750 0.0206 0.01655 0.00751 -0.0879 0.5802 0.0646
-3.500 0.0481 0.01599 0.00684 -0.0882 0.5767 0.0716
-3.250 0.0719 0.01387 0.00617 -0.0895 0.5729 0.4094
-3.000 0.1002 0.01457 0.00677 -0.0890 0.5692 0.4856
-2.750 0.1280 0.01502 0.00714 -0.0886 0.5660 0.5060
-2.500 0.1559 0.01540 0.00740 -0.0883 0.5633 0.5199
-2.250 0.1828 0.01591 0.00794 -0.0877 0.5599 0.5408
-2.000 0.2092 0.01635 0.00842 -0.0869 0.5567 0.5574
-1.750 0.2362 0.01662 0.00869 -0.0864 0.5538 0.5681
-1.500 0.2643 0.01670 0.00867 -0.0864 0.5512 0.5738
-1.250 0.2927 0.01682 0.00867 -0.0866 0.5490 0.5776
-1.000 0.3208 0.01686 0.00870 -0.0868 0.5461 0.5817
-0.750 0.3495 0.01692 0.00868 -0.0872 0.5433 0.5860
-0.500 0.3773 0.01695 0.00870 -0.0873 0.5406 0.5888
-0.250 0.4054 0.01704 0.00875 -0.0874 0.5383 0.5925
0.000 0.4341 0.01716 0.00878 -0.0877 0.5361 0.5972
0.250 0.4623 0.01731 0.00887 -0.0879 0.5336 0.6020
0.500 0.4890 0.01740 0.00904 -0.0878 0.5301 0.6066
0.750 0.5169 0.01750 0.00913 -0.0880 0.5269 0.6111
1.000 0.5457 0.01758 0.00912 -0.0884 0.5240 0.6146
1.250 0.5741 0.01764 0.00914 -0.0886 0.5216 0.6168
1.500 0.6019 0.01778 0.00928 -0.0888 0.5189 0.6190
1.750 0.6290 0.01788 0.00945 -0.0889 0.5155 0.6214
2.000 0.6568 0.01798 0.00956 -0.0891 0.5123 0.6244
2.250 0.6852 0.01808 0.00963 -0.0894 0.5095 0.6277
2.500 0.7138 0.01821 0.00970 -0.0897 0.5073 0.6305
2.750 0.7417 0.01841 0.00993 -0.0899 0.5053 0.6330
3.000 0.7679 0.01861 0.01026 -0.0899 0.5023 0.6359
3.250 0.7949 0.01879 0.01051 -0.0900 0.4993 0.6392
3.500 0.8228 0.01896 0.01070 -0.0903 0.4966 0.6432
3.750 0.8508 0.01905 0.01081 -0.0904 0.4941 0.6467
4.000 0.8793 0.01921 0.01096 -0.0907 0.4919 0.6504
4.250 0.9046 0.01947 0.01136 -0.0906 0.4885 0.6544
4.500 0.9313 0.01958 0.01155 -0.0906 0.4841 0.6589
4.750 0.9595 0.01942 0.01140 -0.0906 0.4798 0.6631
5.000 0.9868 0.01942 0.01141 -0.0906 0.4751 0.6686
5.250 1.0125 0.01939 0.01149 -0.0903 0.4691 0.6745
5.500 1.0406 0.01926 0.01141 -0.0903 0.4650 0.6802
5.750 1.0691 0.01941 0.01156 -0.0906 0.4623 0.6873
6.000 1.0923 0.01961 0.01202 -0.0901 0.4583 0.6941
6.500 1.1447 0.01980 0.01248 -0.0899 0.4518 0.7127
6.750 1.1726 0.01982 0.01260 -0.0899 0.4492 0.7253
7.000 1.1950 0.01977 0.01280 -0.0891 0.4428 0.7419
7.250 1.2211 0.01882 0.01191 -0.0883 0.4318 0.7675
7.750 1.2677 0.01774 0.01133 -0.0864 0.4122 1.0000
8.000 1.2945 0.01768 0.01127 -0.0864 0.4057 1.0000
8.250 1.3168 0.01766 0.01138 -0.0856 0.3931 1.0000
8.500 1.3395 0.01770 0.01153 -0.0849 0.3793 1.0000
8.750 1.3621 0.01783 0.01175 -0.0842 0.3657 1.0000
9.000 1.3824 0.01801 0.01192 -0.0831 0.3471 1.0000
9.250 1.3901 0.01876 0.01237 -0.0804 0.2881 1.0000
9.500 1.3794 0.02068 0.01386 -0.0756 0.2249 1.0000
9.750 1.3574 0.02292 0.01582 -0.0696 0.1775 1.0000
10.000 1.3397 0.02523 0.01801 -0.0651 0.1413 1.0000
10.250 1.3178 0.02843 0.02111 -0.0619 0.1230 1.0000
10.500 1.2984 0.03224 0.02486 -0.0604 0.0964 1.0000
10.750 1.2834 0.03616 0.02875 -0.0597 0.0861 1.0000
11.250 1.2560 0.04436 0.03692 -0.0591 0.0547 1.0000
11.500 1.2482 0.04798 0.04060 -0.0590 0.0425 1.0000
11.750 1.2340 0.05234 0.04493 -0.0590 0.0351 1.0000
12.000 1.2220 0.05654 0.04920 -0.0590 0.0286 1.0000
12.250 1.2049 0.06150 0.05422 -0.0592 0.0236 1.0000
12.500 1.2031 0.06486 0.05770 -0.0594 0.0203 1.0000
12.750 1.1994 0.06854 0.06146 -0.0598 0.0179 1.0000
13.000 1.1939 0.07251 0.06550 -0.0603 0.0165 1.0000
13.250 1.1920 0.07614 0.06922 -0.0608 0.0154 1.0000
13.500 1.1921 0.07956 0.07274 -0.0614 0.0146 1.0000
13.750 1.1939 0.08279 0.07603 -0.0619 0.0134 1.0000
14.000 1.1956 0.08604 0.07933 -0.0626 0.0124 1.0000
14.250 1.1946 0.08973 0.08307 -0.0634 0.0116 1.0000
14.500 1.1925 0.09357 0.08698 -0.0641 0.0112 1.0000
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