Apex 16 (normalized using XFOIL date021206) (apex16-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: Apex 16 (normalized using XFOIL date021206) (apex16-il) Reynolds number: 100,000 Max Cl/Cd: 56.07 at α=7.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-apex16-il-100000.txt Download as CSV file: xf-apex16-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.4835 0.10083 0.09630 -0.0457 1.0000 0.0785
-8.750 -0.5077 0.09853 0.09406 -0.0447 1.0000 0.0786
-8.500 -0.5330 0.09666 0.09223 -0.0425 1.0000 0.0786
-8.250 -0.5544 0.09450 0.09006 -0.0408 1.0000 0.0786
-8.000 -0.5798 0.09277 0.08825 -0.0390 1.0000 0.0788
-7.750 -0.5994 0.09104 0.08638 -0.0372 1.0000 0.0791
-7.500 -0.5655 0.08316 0.07888 -0.0357 1.0000 0.0833
-7.250 -0.5732 0.08037 0.07609 -0.0341 1.0000 0.0853
-7.000 -0.5834 0.07743 0.07310 -0.0329 1.0000 0.0873
-6.750 -0.5928 0.07451 0.07007 -0.0320 1.0000 0.0899
-6.500 -0.6096 0.07444 0.06942 -0.0312 1.0000 0.0937
-6.250 -0.6081 0.06886 0.06384 -0.0308 1.0000 0.0957
-6.000 -0.5993 0.06458 0.05971 -0.0297 1.0000 0.0986
-5.750 -0.5931 0.06177 0.05679 -0.0289 1.0000 0.1036
-5.500 -0.5891 0.05962 0.05413 -0.0285 1.0000 0.1109
-5.250 -0.5782 0.05563 0.05025 -0.0278 1.0000 0.1156
-5.000 -0.5684 0.05337 0.04758 -0.0275 1.0000 0.1264
-4.750 -0.5566 0.05146 0.04533 -0.0270 1.0000 0.1399
-4.500 -0.5431 0.04760 0.04159 -0.0265 1.0000 0.1497
-4.250 -0.5204 0.04378 0.03762 -0.0288 0.9965 0.1753
-4.000 -0.4928 0.04082 0.03422 -0.0317 0.9911 0.2125
-3.750 -0.4632 0.03766 0.03090 -0.0339 0.9860 0.2408
-3.500 -0.4325 0.03457 0.02785 -0.0355 0.9809 0.2593
-3.250 -0.3974 0.03284 0.02574 -0.0370 0.9753 0.2655
-3.000 -0.3522 0.03157 0.02391 -0.0393 0.9706 0.2481
-2.750 -0.3014 0.03444 0.02577 -0.0385 0.9623 0.1554
-2.500 -0.2483 0.03476 0.02547 -0.0389 0.9575 0.0933
-2.250 -0.2233 0.03287 0.02353 -0.0385 0.9509 0.0894
-2.000 -0.1869 0.03180 0.02231 -0.0399 0.9457 0.0867
-1.750 -0.1539 0.03108 0.02135 -0.0402 0.9397 0.0813
-1.500 -0.1231 0.03058 0.02076 -0.0405 0.9333 0.0798
-1.250 -0.0841 0.02975 0.02001 -0.0425 0.9292 0.0802
-1.000 -0.0653 0.02900 0.01940 -0.0412 0.9212 0.0826
-0.750 -0.0304 0.02868 0.01910 -0.0428 0.9159 0.0901
-0.500 -0.0076 0.02846 0.01876 -0.0422 0.9080 0.0944
-0.250 0.0271 0.02808 0.01825 -0.0438 0.9022 0.1072
0.000 0.0525 0.02761 0.01785 -0.0437 0.8949 0.1518
0.250 0.0627 0.02607 0.01865 -0.0391 0.8889 0.7359
0.500 0.0752 0.02627 0.01911 -0.0348 0.8812 0.8166
0.750 0.0959 0.02617 0.01934 -0.0311 0.8746 0.9225
1.000 0.1798 0.02654 0.01957 -0.0426 0.8718 0.9656
1.250 0.2161 0.02674 0.01963 -0.0464 0.8623 1.0000
1.500 0.2599 0.02684 0.01955 -0.0504 0.8572 1.0000
1.750 0.2782 0.02711 0.01970 -0.0499 0.8465 1.0000
2.000 0.3131 0.02732 0.01980 -0.0519 0.8394 1.0000
2.250 0.3437 0.02753 0.01993 -0.0530 0.8310 1.0000
2.500 0.3703 0.02783 0.02016 -0.0534 0.8220 1.0000
2.750 0.4098 0.02786 0.02015 -0.0557 0.8155 1.0000
3.000 0.4326 0.02819 0.02046 -0.0553 0.8052 1.0000
3.250 0.4773 0.02801 0.02028 -0.0581 0.8001 1.0000
3.500 0.4977 0.02837 0.02063 -0.0573 0.7888 1.0000
3.750 0.5473 0.02790 0.02022 -0.0606 0.7846 1.0000
4.000 0.5673 0.02820 0.02054 -0.0595 0.7727 1.0000
4.250 0.6175 0.02751 0.01993 -0.0627 0.7687 1.0000
4.500 0.6409 0.02759 0.02009 -0.0619 0.7570 1.0000
4.750 0.7008 0.02622 0.01885 -0.0660 0.7545 1.0000
5.000 0.7250 0.02607 0.01879 -0.0650 0.7420 1.0000
5.250 0.7583 0.02544 0.01830 -0.0651 0.7304 1.0000
5.500 0.8460 0.02252 0.01560 -0.0728 0.7253 1.0000
5.750 0.8839 0.02160 0.01485 -0.0734 0.7113 1.0000
6.000 0.9221 0.02080 0.01419 -0.0742 0.6967 1.0000
6.250 0.9555 0.02020 0.01373 -0.0742 0.6798 1.0000
6.500 0.9793 0.01988 0.01356 -0.0727 0.6593 1.0000
6.750 1.0102 0.01918 0.01293 -0.0719 0.6326 1.0000
7.000 1.0335 0.01858 0.01225 -0.0696 0.5922 1.0000
7.250 1.0417 0.01858 0.01213 -0.0651 0.5445 1.0000
7.500 1.0472 0.01886 0.01228 -0.0604 0.4956 1.0000
7.750 1.0522 0.01937 0.01255 -0.0559 0.4451 1.0000
8.000 1.0535 0.02016 0.01309 -0.0512 0.3905 1.0000
8.250 1.0511 0.02125 0.01384 -0.0461 0.3306 1.0000
8.500 1.0445 0.02271 0.01487 -0.0409 0.2628 1.0000
8.750 1.0330 0.02474 0.01632 -0.0355 0.1868 1.0000
9.000 1.0199 0.02735 0.01828 -0.0303 0.1272 1.0000
9.250 1.0176 0.02951 0.02018 -0.0265 0.1011 1.0000
9.500 1.0231 0.03128 0.02185 -0.0238 0.0879 1.0000
9.750 1.0344 0.03286 0.02344 -0.0219 0.0786 1.0000
10.000 1.0528 0.03467 0.02514 -0.0208 0.0722 1.0000
10.250 1.0774 0.03625 0.02683 -0.0202 0.0665 1.0000
10.500 1.1138 0.03859 0.02908 -0.0215 0.0606 1.0000
10.750 1.1495 0.04103 0.03186 -0.0224 0.0572 1.0000
11.000 1.1742 0.04337 0.03439 -0.0223 0.0540 1.0000
11.250 1.2198 0.04872 0.03986 -0.0260 0.0505 1.0000
11.500 1.2262 0.05160 0.04315 -0.0234 0.0501 1.0000
11.750 1.2284 0.05486 0.04681 -0.0206 0.0500 1.0000
12.000 1.2243 0.05801 0.05031 -0.0172 0.0499 1.0000
12.250 1.2165 0.06123 0.05386 -0.0138 0.0499 1.0000
12.500 1.2038 0.06436 0.05730 -0.0103 0.0498 1.0000
12.750 1.1876 0.06755 0.06079 -0.0071 0.0496 1.0000
13.000 1.1698 0.07109 0.06461 -0.0044 0.0496 1.0000
13.250 1.1530 0.07524 0.06899 -0.0025 0.0498 1.0000
13.500 1.1330 0.07940 0.07338 -0.0011 0.0499 1.0000
13.750 1.1122 0.08416 0.07835 -0.0005 0.0500 1.0000
14.000 1.1010 0.09011 0.08446 -0.0007 0.0506 1.0000
14.250 1.0769 0.09423 0.08880 -0.0011 0.0509 1.0000
14.500 0.9676 0.11017 0.10534 -0.0111 0.0574 1.0000
14.750 0.9365 0.12067 0.11591 -0.0174 0.0590 1.0000
15.000 0.9219 0.12909 0.12434 -0.0217 0.0606 1.0000
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Polar data table (+)
Polar graphs
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