Apex 16 (normalized using XFOIL date021206) (apex16-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: Apex 16 (normalized using XFOIL date021206) (apex16-il) Reynolds number: 1,000,000 Max Cl/Cd: 123.64 at α=3.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-apex16-il-1000000.txt Download as CSV file: xf-apex16-il-1000000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.3287 0.08450 0.08282 -0.0774 0.9879 0.0131
-9.750 -0.3241 0.07665 0.07496 -0.0864 0.9863 0.0132
-9.500 -0.3221 0.06988 0.06813 -0.0954 0.9847 0.0132
-9.250 -0.3277 0.06456 0.06273 -0.1017 0.9797 0.0132
-9.000 -0.3298 0.05991 0.05797 -0.1069 0.9750 0.0132
-8.750 -0.3219 0.05505 0.05296 -0.1111 0.9726 0.0132
-8.500 -0.3131 0.05091 0.04866 -0.1134 0.9690 0.0133
-8.250 -0.3179 0.04383 0.04133 -0.1154 0.9629 0.0135
-8.000 -0.3008 0.04122 0.03861 -0.1174 0.9602 0.0138
-7.750 -0.2789 0.03873 0.03600 -0.1195 0.9578 0.0141
-7.500 -0.2673 0.03688 0.03405 -0.1183 0.9506 0.0143
-7.250 -0.2477 0.03475 0.03176 -0.1187 0.9458 0.0148
-7.000 -0.2299 0.03258 0.02943 -0.1182 0.9398 0.0157
-6.750 -0.2044 0.03084 0.02745 -0.1164 0.9337 0.0173
-6.500 -0.1837 0.02852 0.02487 -0.1160 0.9284 0.0174
-6.250 -0.1703 0.02651 0.02265 -0.1138 0.9209 0.0174
-6.000 -0.1601 0.02179 0.01762 -0.1124 0.9148 0.0183
-5.750 -0.1411 0.02076 0.01651 -0.1113 0.9086 0.0186
-5.500 -0.1187 0.01966 0.01529 -0.1107 0.9032 0.0192
-5.250 -0.0949 0.01855 0.01405 -0.1103 0.8982 0.0201
-5.000 -0.0682 0.01899 0.01436 -0.1095 0.8926 0.0226
-4.750 -0.0480 0.01579 0.01080 -0.1083 0.8873 0.0235
-4.500 -0.0232 0.01244 0.00723 -0.1071 0.8823 0.0183
-4.250 0.0007 0.01160 0.00631 -0.1064 0.8766 0.0182
-4.000 0.0259 0.01095 0.00562 -0.1061 0.8717 0.0187
-3.750 0.0478 0.01030 0.00493 -0.1050 0.8658 0.0188
-3.500 0.0711 0.00980 0.00439 -0.1043 0.8601 0.0192
-3.250 0.0952 0.00942 0.00396 -0.1037 0.8549 0.0199
-3.000 0.1184 0.00908 0.00359 -0.1029 0.8489 0.0205
-2.750 0.1429 0.00874 0.00318 -0.1024 0.8436 0.0209
-2.500 0.1672 0.00847 0.00287 -0.1018 0.8380 0.0215
-2.250 0.1919 0.00823 0.00257 -0.1012 0.8323 0.0220
-2.000 0.2187 0.00813 0.00243 -0.1011 0.8270 0.0228
-1.750 0.2418 0.00775 0.00198 -0.1003 0.8209 0.0247
-1.500 0.2680 0.00760 0.00179 -0.1000 0.8152 0.0267
-1.250 0.2939 0.00750 0.00166 -0.0997 0.8093 0.0286
-1.000 0.3198 0.00739 0.00151 -0.0994 0.8028 0.0330
-0.750 0.3420 0.00684 0.00137 -0.0986 0.7965 0.2022
-0.500 0.3594 0.00597 0.00123 -0.0970 0.7895 0.4566
-0.250 0.3848 0.00586 0.00121 -0.0967 0.7832 0.5031
0.000 0.4095 0.00574 0.00122 -0.0961 0.7763 0.5419
0.250 0.4348 0.00568 0.00123 -0.0957 0.7696 0.5833
0.500 0.4600 0.00561 0.00126 -0.0952 0.7628 0.6131
0.750 0.4857 0.00561 0.00128 -0.0948 0.7556 0.6315
1.000 0.5114 0.00560 0.00130 -0.0945 0.7482 0.6475
1.250 0.5371 0.00562 0.00132 -0.0941 0.7405 0.6594
1.500 0.5629 0.00563 0.00135 -0.0937 0.7321 0.6712
1.750 0.5881 0.00566 0.00138 -0.0933 0.7234 0.6831
2.000 0.6131 0.00568 0.00142 -0.0927 0.7134 0.6945
2.250 0.6378 0.00572 0.00147 -0.0922 0.7024 0.7058
2.500 0.6606 0.00578 0.00151 -0.0911 0.6855 0.7174
2.750 0.6823 0.00588 0.00156 -0.0899 0.6663 0.7296
3.000 0.7048 0.00595 0.00163 -0.0888 0.6488 0.7420
3.250 0.7275 0.00604 0.00172 -0.0878 0.6340 0.7547
3.500 0.7499 0.00613 0.00182 -0.0868 0.6190 0.7683
3.750 0.7715 0.00624 0.00193 -0.0855 0.6025 0.7834
4.000 0.7903 0.00641 0.00207 -0.0837 0.5791 0.8011
4.250 0.8101 0.00656 0.00221 -0.0821 0.5566 0.8202
4.500 0.8287 0.00674 0.00236 -0.0803 0.5325 0.8380
4.750 0.8454 0.00697 0.00252 -0.0780 0.5000 0.8550
5.000 0.8584 0.00726 0.00270 -0.0750 0.4613 0.8729
5.250 0.8711 0.00755 0.00290 -0.0720 0.4235 0.8937
5.500 0.8917 0.00802 0.00326 -0.0710 0.3689 0.9356
5.750 0.9361 0.00889 0.00380 -0.0757 0.2932 1.0000
6.000 0.9466 0.00944 0.00412 -0.0725 0.2463 1.0000
6.250 0.9565 0.01006 0.00449 -0.0693 0.1983 1.0000
6.500 0.9686 0.01064 0.00487 -0.0665 0.1588 1.0000
6.750 0.9810 0.01122 0.00527 -0.0639 0.1249 1.0000
7.000 0.9947 0.01177 0.00568 -0.0615 0.0962 1.0000
7.250 1.0023 0.01265 0.00627 -0.0581 0.0496 1.0000
7.500 1.0144 0.01334 0.00683 -0.0555 0.0292 1.0000
7.750 1.0302 0.01384 0.00733 -0.0536 0.0248 1.0000
8.000 1.0481 0.01424 0.00776 -0.0520 0.0233 1.0000
8.250 1.0660 0.01465 0.00821 -0.0505 0.0221 1.0000
8.500 1.0827 0.01513 0.00869 -0.0489 0.0205 1.0000
8.750 1.0968 0.01577 0.00938 -0.0468 0.0188 1.0000
9.000 1.1119 0.01636 0.01002 -0.0450 0.0178 1.0000
9.250 1.1292 0.01681 0.01051 -0.0436 0.0172 1.0000
9.500 1.1452 0.01736 0.01110 -0.0420 0.0163 1.0000
9.750 1.1609 0.01792 0.01169 -0.0404 0.0155 1.0000
10.000 1.1746 0.01861 0.01243 -0.0386 0.0147 1.0000
10.250 1.1787 0.01992 0.01383 -0.0354 0.0135 1.0000
10.500 1.1962 0.02041 0.01435 -0.0343 0.0132 1.0000
10.750 1.2130 0.02095 0.01493 -0.0331 0.0124 1.0000
11.000 1.2274 0.02165 0.01568 -0.0316 0.0118 1.0000
11.250 1.2423 0.02233 0.01638 -0.0303 0.0112 1.0000
11.500 1.2528 0.02332 0.01741 -0.0285 0.0106 1.0000
11.750 1.2525 0.02508 0.01928 -0.0254 0.0099 1.0000
12.000 1.2672 0.02583 0.02008 -0.0243 0.0097 1.0000
12.250 1.2770 0.02694 0.02126 -0.0226 0.0095 1.0000
12.500 1.2882 0.02798 0.02237 -0.0212 0.0090 1.0000
12.750 1.3009 0.02891 0.02336 -0.0201 0.0086 1.0000
13.000 1.3125 0.02993 0.02442 -0.0189 0.0082 1.0000
13.250 1.3204 0.03128 0.02584 -0.0175 0.0080 1.0000
13.500 1.3264 0.03283 0.02746 -0.0160 0.0078 1.0000
13.750 1.3248 0.03504 0.02976 -0.0140 0.0074 1.0000
14.000 1.3213 0.03753 0.03237 -0.0121 0.0073 1.0000
14.250 1.3263 0.03934 0.03428 -0.0109 0.0071 1.0000
14.500 1.3274 0.04157 0.03662 -0.0097 0.0071 1.0000
14.750 1.3319 0.04353 0.03868 -0.0088 0.0069 1.0000
15.000 1.3390 0.04530 0.04053 -0.0083 0.0068 1.0000
15.250 1.3425 0.04749 0.04282 -0.0077 0.0065 1.0000
15.500 1.3413 0.05024 0.04569 -0.0070 0.0064 1.0000
15.750 1.3479 0.05223 0.04776 -0.0069 0.0062 1.0000
16.000 1.3471 0.05509 0.05072 -0.0067 0.0061 1.0000
16.250 1.3465 0.05806 0.05379 -0.0067 0.0059 1.0000
16.500 1.3445 0.06127 0.05711 -0.0068 0.0058 1.0000
16.750 1.3385 0.06505 0.06101 -0.0071 0.0058 1.0000
17.000 1.3382 0.06828 0.06432 -0.0078 0.0057 1.0000
17.250 1.3331 0.07221 0.06836 -0.0086 0.0056 1.0000
17.500 1.3205 0.07726 0.07357 -0.0096 0.0057 1.0000
17.750 1.3137 0.08174 0.07813 -0.0110 0.0055 1.0000
18.000 1.3061 0.08644 0.08293 -0.0126 0.0054 1.0000
18.250 1.2942 0.09190 0.08853 -0.0145 0.0054 1.0000
18.500 1.2831 0.09746 0.09421 -0.0168 0.0053 1.0000
18.750 1.2653 0.10424 0.10113 -0.0196 0.0053 1.0000
|
Polar data table (+)
Polar graphs
<< Back to Apex 16 (normalized using XFOIL date021206) (apex16-il)