Apex 16 (normalized using XFOIL date021206) (apex16-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: Apex 16 (normalized using XFOIL date021206) (apex16-il) Reynolds number: 1,000,000 Max Cl/Cd: 99.41 at α=3.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-apex16-il-1000000-n5.txt Download as CSV file: xf-apex16-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.3281 0.08492 0.08314 -0.0804 0.9827 0.0076
-10.250 -0.3291 0.07829 0.07654 -0.0859 0.9801 0.0078
-10.000 -0.3316 0.07031 0.06855 -0.0946 0.9777 0.0077
-9.750 -0.3534 0.06103 0.05916 -0.1055 0.9708 0.0078
-9.500 -0.3630 0.05478 0.05276 -0.1132 0.9646 0.0079
-9.250 -0.3633 0.04951 0.04729 -0.1168 0.9581 0.0080
-9.000 -0.3609 0.04481 0.04238 -0.1183 0.9510 0.0081
-8.750 -0.3502 0.04061 0.03796 -0.1191 0.9448 0.0084
-8.500 -0.3441 0.03713 0.03427 -0.1180 0.9366 0.0084
-8.250 -0.3472 0.03179 0.02857 -0.1158 0.9275 0.0087
-8.000 -0.3368 0.02867 0.02520 -0.1142 0.9205 0.0088
-7.750 -0.3231 0.02600 0.02230 -0.1128 0.9142 0.0089
-7.500 -0.3058 0.02415 0.02028 -0.1117 0.9073 0.0091
-7.250 -0.2851 0.02298 0.01897 -0.1111 0.9014 0.0093
-7.000 -0.2700 0.01979 0.01547 -0.1093 0.8934 0.0095
-6.750 -0.2501 0.01777 0.01320 -0.1082 0.8864 0.0098
-6.500 -0.2288 0.01627 0.01152 -0.1073 0.8789 0.0101
-6.250 -0.2059 0.01502 0.01009 -0.1066 0.8726 0.0105
-6.000 -0.1824 0.01421 0.00916 -0.1060 0.8664 0.0110
-5.750 -0.1589 0.01330 0.00811 -0.1055 0.8603 0.0111
-5.500 -0.1350 0.01268 0.00742 -0.1049 0.8545 0.0114
-5.250 -0.1114 0.01208 0.00673 -0.1043 0.8484 0.0117
-5.000 -0.0875 0.01158 0.00615 -0.1037 0.8428 0.0118
-4.750 -0.0640 0.01111 0.00562 -0.1031 0.8364 0.0120
-4.500 -0.0404 0.01071 0.00514 -0.1024 0.8308 0.0121
-4.250 -0.0161 0.01041 0.00480 -0.1019 0.8253 0.0123
-4.000 0.0081 0.01011 0.00445 -0.1014 0.8195 0.0124
-3.750 0.0276 0.00936 0.00361 -0.1000 0.8138 0.0130
-3.500 0.0508 0.00899 0.00318 -0.0993 0.8081 0.0135
-3.250 0.0754 0.00876 0.00290 -0.0988 0.8029 0.0140
-3.000 0.1007 0.00856 0.00268 -0.0985 0.7979 0.0145
-2.750 0.1259 0.00839 0.00247 -0.0981 0.7922 0.0151
-2.500 0.1513 0.00823 0.00226 -0.0978 0.7872 0.0156
-2.250 0.1771 0.00807 0.00207 -0.0975 0.7818 0.0162
-2.000 0.2028 0.00795 0.00191 -0.0972 0.7760 0.0168
-1.750 0.2287 0.00784 0.00176 -0.0969 0.7705 0.0172
-1.500 0.2548 0.00775 0.00165 -0.0966 0.7641 0.0178
-1.250 0.2806 0.00770 0.00156 -0.0963 0.7576 0.0182
-1.000 0.3065 0.00758 0.00140 -0.0960 0.7504 0.0198
-0.750 0.3320 0.00753 0.00131 -0.0956 0.7429 0.0228
-0.500 0.3580 0.00747 0.00125 -0.0953 0.7348 0.0270
-0.250 0.3830 0.00737 0.00122 -0.0949 0.7267 0.0666
0.000 0.4012 0.00652 0.00106 -0.0935 0.7176 0.3605
0.250 0.4244 0.00628 0.00105 -0.0928 0.7085 0.4389
0.500 0.4478 0.00614 0.00106 -0.0920 0.6985 0.4970
0.750 0.4725 0.00610 0.00108 -0.0915 0.6878 0.5261
1.000 0.4969 0.00607 0.00111 -0.0909 0.6765 0.5557
1.250 0.5215 0.00610 0.00114 -0.0903 0.6644 0.5728
1.500 0.5459 0.00616 0.00118 -0.0897 0.6514 0.5819
1.750 0.5702 0.00623 0.00123 -0.0891 0.6379 0.5913
2.000 0.5939 0.00631 0.00129 -0.0883 0.6230 0.6011
2.250 0.6171 0.00642 0.00136 -0.0875 0.6064 0.6106
2.750 0.6599 0.00674 0.00155 -0.0850 0.5594 0.6325
3.000 0.6809 0.00691 0.00166 -0.0837 0.5334 0.6435
3.250 0.7028 0.00707 0.00177 -0.0826 0.5113 0.6547
3.500 0.7220 0.00733 0.00192 -0.0810 0.4776 0.6658
3.750 0.7385 0.00769 0.00212 -0.0788 0.4325 0.6768
4.000 0.7558 0.00803 0.00232 -0.0769 0.3925 0.6887
4.250 0.7755 0.00827 0.00249 -0.0754 0.3670 0.6998
4.500 0.7916 0.00861 0.00271 -0.0732 0.3309 0.7117
4.750 0.8076 0.00894 0.00294 -0.0710 0.2954 0.7231
5.000 0.8224 0.00934 0.00319 -0.0686 0.2566 0.7357
5.250 0.8368 0.00977 0.00349 -0.0662 0.2179 0.7482
5.500 0.8518 0.01017 0.00379 -0.0639 0.1849 0.7641
5.750 0.8639 0.01069 0.00416 -0.0610 0.1429 0.7826
6.000 0.8781 0.01110 0.00451 -0.0586 0.1148 0.8051
6.250 0.8942 0.01141 0.00482 -0.0565 0.0968 0.8310
6.500 0.9086 0.01181 0.00516 -0.0541 0.0747 0.8521
7.000 0.9360 0.01272 0.00601 -0.0493 0.0277 0.9113
7.250 0.9911 0.01324 0.00660 -0.0562 0.0211 1.0000
7.500 1.0097 0.01360 0.00696 -0.0548 0.0190 1.0000
7.750 1.0286 0.01394 0.00732 -0.0534 0.0180 1.0000
8.000 1.0477 0.01427 0.00768 -0.0521 0.0174 1.0000
8.250 1.0663 0.01463 0.00806 -0.0508 0.0166 1.0000
8.500 1.0842 0.01503 0.00850 -0.0494 0.0157 1.0000
8.750 1.1016 0.01547 0.00894 -0.0479 0.0146 1.0000
9.000 1.1182 0.01596 0.00946 -0.0463 0.0135 1.0000
9.250 1.1342 0.01650 0.01003 -0.0447 0.0128 1.0000
9.500 1.1523 0.01691 0.01048 -0.0434 0.0126 1.0000
9.750 1.1696 0.01737 0.01098 -0.0421 0.0122 1.0000
10.000 1.1865 0.01786 0.01150 -0.0407 0.0118 1.0000
10.250 1.2026 0.01841 0.01211 -0.0393 0.0112 1.0000
10.500 1.2190 0.01894 0.01267 -0.0379 0.0106 1.0000
10.750 1.2351 0.01950 0.01325 -0.0366 0.0099 1.0000
11.000 1.2494 0.02018 0.01395 -0.0350 0.0091 1.0000
11.250 1.2630 0.02093 0.01474 -0.0334 0.0085 1.0000
11.500 1.2782 0.02156 0.01542 -0.0321 0.0082 1.0000
11.750 1.2925 0.02227 0.01618 -0.0307 0.0078 1.0000
12.000 1.3063 0.02303 0.01699 -0.0293 0.0074 1.0000
12.250 1.3198 0.02382 0.01782 -0.0280 0.0070 1.0000
12.500 1.3327 0.02466 0.01871 -0.0266 0.0065 1.0000
12.750 1.3445 0.02559 0.01967 -0.0252 0.0060 1.0000
13.000 1.3535 0.02677 0.02091 -0.0235 0.0055 1.0000
13.250 1.3638 0.02786 0.02206 -0.0221 0.0054 1.0000
13.500 1.3749 0.02890 0.02317 -0.0208 0.0052 1.0000
13.750 1.3832 0.03018 0.02453 -0.0193 0.0051 1.0000
14.000 1.3920 0.03147 0.02589 -0.0180 0.0049 1.0000
14.250 1.4006 0.03280 0.02730 -0.0168 0.0048 1.0000
14.500 1.4077 0.03427 0.02884 -0.0156 0.0046 1.0000
14.750 1.4142 0.03584 0.03048 -0.0144 0.0044 1.0000
15.000 1.4196 0.03756 0.03229 -0.0133 0.0043 1.0000
15.250 1.4248 0.03934 0.03416 -0.0123 0.0043 1.0000
15.500 1.4297 0.04120 0.03610 -0.0114 0.0041 1.0000
15.750 1.4324 0.04333 0.03830 -0.0105 0.0039 1.0000
16.000 1.4326 0.04579 0.04085 -0.0097 0.0037 1.0000
16.250 1.4333 0.04828 0.04345 -0.0091 0.0036 1.0000
16.500 1.4322 0.05104 0.04631 -0.0087 0.0035 1.0000
16.750 1.4265 0.05444 0.04984 -0.0084 0.0034 1.0000
17.000 1.4251 0.05745 0.05296 -0.0084 0.0034 1.0000
17.250 1.4212 0.06089 0.05651 -0.0085 0.0034 1.0000
17.500 1.4195 0.06412 0.05984 -0.0089 0.0033 1.0000
17.750 1.4161 0.06765 0.06348 -0.0094 0.0033 1.0000
18.000 1.4107 0.07157 0.06752 -0.0102 0.0032 1.0000
18.250 1.4032 0.07590 0.07197 -0.0112 0.0032 1.0000
18.500 1.3919 0.08094 0.07714 -0.0126 0.0032 1.0000
18.750 1.3816 0.08593 0.08226 -0.0142 0.0032 1.0000
19.000 1.3714 0.09108 0.08753 -0.0161 0.0031 1.0000
|
Polar data table (+)
Polar graphs
<< Back to Apex 16 (normalized using XFOIL date021206) (apex16-il)