Apex 16 (normalized using XFOIL date021206) (apex16-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: Apex 16 (normalized using XFOIL date021206) (apex16-il) Reynolds number: 500,000 Max Cl/Cd: 92.31 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-apex16-il-500000-n5.txt Download as CSV file: xf-apex16-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: Apex 16 (normalized using XFOIL date021206)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.3345 0.08292 0.08050 -0.0783 0.9828 0.0120
-9.750 -0.3343 0.07616 0.07375 -0.0848 0.9798 0.0119
-9.500 -0.3364 0.06903 0.06657 -0.0936 0.9771 0.0118
-9.250 -0.3436 0.06397 0.06144 -0.0992 0.9710 0.0116
-9.000 -0.3461 0.05922 0.05657 -0.1049 0.9669 0.0114
-8.750 -0.3502 0.05493 0.05213 -0.1067 0.9591 0.0115
-8.500 -0.3409 0.05046 0.04746 -0.1099 0.9561 0.0114
-8.250 -0.3378 0.04660 0.04341 -0.1097 0.9487 0.0116
-8.000 -0.3239 0.04263 0.03920 -0.1109 0.9449 0.0117
-7.750 -0.3141 0.03942 0.03577 -0.1099 0.9380 0.0119
-7.500 -0.2982 0.03613 0.03224 -0.1098 0.9334 0.0120
-7.000 -0.2692 0.02922 0.02474 -0.1074 0.9219 0.0127
-6.750 -0.2488 0.02606 0.02127 -0.1071 0.9181 0.0126
-6.500 -0.2349 0.02357 0.01851 -0.1052 0.9109 0.0127
-6.250 -0.2137 0.02114 0.01580 -0.1047 0.9056 0.0128
-6.000 -0.1922 0.01988 0.01437 -0.1041 0.8993 0.0132
-5.750 -0.1687 0.01850 0.01282 -0.1035 0.8930 0.0134
-5.500 -0.1419 0.01758 0.01177 -0.1038 0.8888 0.0138
-5.250 -0.1196 0.01668 0.01076 -0.1029 0.8828 0.0141
-5.000 -0.0940 0.01582 0.00980 -0.1027 0.8777 0.0145
-4.750 -0.0675 0.01494 0.00880 -0.1027 0.8735 0.0148
-4.500 -0.0440 0.01426 0.00806 -0.1020 0.8675 0.0152
-4.250 -0.0182 0.01372 0.00745 -0.1018 0.8625 0.0160
-4.000 0.0067 0.01308 0.00673 -0.1013 0.8577 0.0164
-3.750 0.0296 0.01244 0.00603 -0.1005 0.8517 0.0166
-3.500 0.0540 0.01187 0.00538 -0.1000 0.8466 0.0170
-3.250 0.0771 0.01141 0.00487 -0.0992 0.8411 0.0173
-3.000 0.1011 0.01104 0.00444 -0.0986 0.8355 0.0178
-2.750 0.1267 0.01073 0.00406 -0.0983 0.8306 0.0182
-2.500 0.1488 0.01028 0.00354 -0.0974 0.8246 0.0187
-2.250 0.1729 0.00987 0.00305 -0.0968 0.8192 0.0198
-2.000 0.1982 0.00962 0.00276 -0.0965 0.8140 0.0213
-1.750 0.2236 0.00945 0.00256 -0.0961 0.8081 0.0229
-1.500 0.2504 0.00931 0.00235 -0.0960 0.8030 0.0240
-1.250 0.2759 0.00918 0.00219 -0.0956 0.7970 0.0256
-1.000 0.3022 0.00909 0.00204 -0.0954 0.7910 0.0277
-0.750 0.3284 0.00899 0.00193 -0.0952 0.7850 0.0375
-0.500 0.3525 0.00869 0.00185 -0.0946 0.7781 0.1318
-0.250 0.3701 0.00769 0.00167 -0.0933 0.7714 0.4425
0.250 0.4180 0.00737 0.00170 -0.0920 0.7565 0.5589
0.500 0.4427 0.00731 0.00173 -0.0915 0.7483 0.5891
0.750 0.4680 0.00730 0.00175 -0.0910 0.7404 0.6094
1.000 0.4936 0.00731 0.00176 -0.0906 0.7316 0.6200
1.250 0.5189 0.00733 0.00179 -0.0901 0.7226 0.6313
1.500 0.5442 0.00736 0.00182 -0.0897 0.7136 0.6425
1.750 0.5692 0.00738 0.00186 -0.0892 0.7035 0.6540
2.000 0.5940 0.00742 0.00191 -0.0886 0.6930 0.6658
2.250 0.6183 0.00747 0.00197 -0.0879 0.6816 0.6768
2.500 0.6423 0.00753 0.00204 -0.0872 0.6693 0.6881
2.750 0.6657 0.00761 0.00211 -0.0863 0.6556 0.7000
3.000 0.6882 0.00770 0.00219 -0.0853 0.6389 0.7123
3.250 0.7080 0.00786 0.00229 -0.0836 0.6146 0.7242
3.500 0.7269 0.00805 0.00242 -0.0819 0.5884 0.7360
3.750 0.7465 0.00822 0.00255 -0.0802 0.5673 0.7489
4.000 0.7677 0.00835 0.00270 -0.0789 0.5504 0.7627
4.250 0.7865 0.00852 0.00287 -0.0772 0.5270 0.7785
4.500 0.8009 0.00880 0.00306 -0.0745 0.4908 0.7960
4.750 0.8117 0.00916 0.00330 -0.0711 0.4487 0.8163
5.000 0.8211 0.00957 0.00357 -0.0675 0.4047 0.8367
5.250 0.8330 0.00997 0.00385 -0.0644 0.3659 0.8577
5.500 0.8466 0.01035 0.00415 -0.0618 0.3322 0.8792
5.750 0.8649 0.01075 0.00449 -0.0602 0.2941 0.9102
6.000 0.9050 0.01173 0.00517 -0.0642 0.2185 1.0000
6.250 0.9175 0.01234 0.00558 -0.0617 0.1786 1.0000
6.500 0.9293 0.01302 0.00603 -0.0590 0.1387 1.0000
6.750 0.9430 0.01362 0.00648 -0.0568 0.1098 1.0000
7.000 0.9581 0.01416 0.00691 -0.0548 0.0881 1.0000
7.250 0.9706 0.01486 0.00746 -0.0525 0.0576 1.0000
7.500 0.9826 0.01560 0.00806 -0.0501 0.0349 1.0000
7.750 0.9983 0.01615 0.00859 -0.0483 0.0278 1.0000
8.000 1.0150 0.01665 0.00911 -0.0466 0.0247 1.0000
8.250 1.0322 0.01713 0.00963 -0.0451 0.0232 1.0000
8.500 1.0485 0.01766 0.01020 -0.0436 0.0217 1.0000
8.750 1.0638 0.01827 0.01085 -0.0419 0.0201 1.0000
9.000 1.0778 0.01896 0.01159 -0.0400 0.0188 1.0000
9.250 1.0930 0.01958 0.01227 -0.0384 0.0179 1.0000
9.500 1.1086 0.02018 0.01293 -0.0369 0.0172 1.0000
9.750 1.1233 0.02085 0.01366 -0.0353 0.0164 1.0000
10.000 1.1374 0.02156 0.01443 -0.0337 0.0156 1.0000
10.250 1.1505 0.02236 0.01527 -0.0320 0.0147 1.0000
10.500 1.1625 0.02323 0.01620 -0.0303 0.0138 1.0000
10.750 1.1697 0.02446 0.01750 -0.0280 0.0129 1.0000
11.000 1.1841 0.02520 0.01832 -0.0267 0.0125 1.0000
11.250 1.1960 0.02613 0.01933 -0.0251 0.0120 1.0000
11.500 1.2073 0.02713 0.02041 -0.0235 0.0115 1.0000
11.750 1.2180 0.02820 0.02155 -0.0220 0.0109 1.0000
12.000 1.2280 0.02933 0.02276 -0.0205 0.0105 1.0000
12.250 1.2380 0.03048 0.02398 -0.0191 0.0100 1.0000
12.500 1.2483 0.03164 0.02520 -0.0178 0.0094 1.0000
12.750 1.2543 0.03318 0.02680 -0.0163 0.0090 1.0000
13.000 1.2576 0.03497 0.02868 -0.0146 0.0085 1.0000
13.250 1.2657 0.03641 0.03025 -0.0134 0.0083 1.0000
13.500 1.2753 0.03775 0.03168 -0.0125 0.0078 1.0000
13.750 1.2799 0.03958 0.03363 -0.0112 0.0076 1.0000
14.000 1.2844 0.04146 0.03561 -0.0102 0.0073 1.0000
14.250 1.2886 0.04343 0.03769 -0.0092 0.0071 1.0000
14.500 1.2923 0.04552 0.03988 -0.0084 0.0069 1.0000
14.750 1.2967 0.04760 0.04206 -0.0078 0.0066 1.0000
15.000 1.2983 0.05003 0.04460 -0.0073 0.0064 1.0000
15.250 1.2997 0.05257 0.04725 -0.0069 0.0064 1.0000
15.500 1.3013 0.05517 0.04994 -0.0067 0.0061 1.0000
15.750 1.3005 0.05815 0.05302 -0.0067 0.0059 1.0000
16.000 1.2957 0.06173 0.05672 -0.0069 0.0057 1.0000
16.250 1.2901 0.06553 0.06066 -0.0072 0.0057 1.0000
16.500 1.2833 0.06964 0.06490 -0.0079 0.0056 1.0000
16.750 1.2756 0.07404 0.06945 -0.0088 0.0055 1.0000
17.000 1.2676 0.07862 0.07418 -0.0100 0.0055 1.0000
17.250 1.2611 0.08315 0.07886 -0.0114 0.0054 1.0000
17.500 1.2508 0.08841 0.08430 -0.0133 0.0054 1.0000
17.750 1.2410 0.09381 0.08985 -0.0154 0.0054 1.0000
18.000 1.2304 0.09952 0.09571 -0.0179 0.0053 1.0000
18.250 1.2184 0.10561 0.10196 -0.0206 0.0053 1.0000
18.500 1.2051 0.11216 0.10866 -0.0238 0.0052 1.0000
18.750 1.1915 0.11896 0.11562 -0.0273 0.0052 1.0000
19.000 1.1778 0.12600 0.12281 -0.0312 0.0051 1.0000
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Polar data table (+)
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