Apex 16 (normalized using XFOIL date021206) (apex16-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: Apex 16 (normalized using XFOIL date021206) (apex16-il) Reynolds number: 500,000 Max Cl/Cd: 112.59 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-apex16-il-500000.txt Download as CSV file: xf-apex16-il-500000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.2641 0.08859 0.08641 -0.0648 0.9870 0.0186
-10.000 -0.2598 0.08387 0.08170 -0.0676 0.9859 0.0189
-9.750 -0.3899 0.08744 0.08521 -0.0645 0.9909 0.0178
-9.500 -0.3831 0.08222 0.07999 -0.0697 0.9885 0.0180
-9.250 -0.3773 0.07657 0.07431 -0.0765 0.9861 0.0181
-9.000 -0.3773 0.07037 0.06804 -0.0852 0.9830 0.0182
-8.750 -0.3829 0.06621 0.06381 -0.0895 0.9758 0.0183
-8.500 -0.3743 0.06168 0.05916 -0.0944 0.9723 0.0186
-8.250 -0.3708 0.05829 0.05567 -0.0958 0.9659 0.0188
-8.000 -0.3595 0.05470 0.05195 -0.0983 0.9618 0.0193
-7.750 -0.3424 0.05092 0.04799 -0.1012 0.9594 0.0200
-7.500 -0.3201 0.04724 0.04410 -0.1040 0.9579 0.0212
-7.250 -0.3038 0.04610 0.04259 -0.1015 0.9501 0.0227
-7.000 -0.2815 0.04304 0.03923 -0.1027 0.9475 0.0228
-6.750 -0.2666 0.03655 0.03257 -0.1052 0.9455 0.0237
-6.500 -0.2389 0.03416 0.03007 -0.1074 0.9440 0.0244
-6.250 -0.2237 0.03262 0.02844 -0.1062 0.9373 0.0253
-6.000 -0.1983 0.03069 0.02633 -0.1066 0.9337 0.0270
-5.750 -0.1629 0.03075 0.02605 -0.1067 0.9315 0.0298
-5.500 -0.1423 0.02568 0.02064 -0.1074 0.9291 0.0312
-5.250 -0.1276 0.02434 0.01927 -0.1055 0.9220 0.0320
-5.000 -0.1012 0.02299 0.01782 -0.1059 0.9186 0.0337
-4.750 -0.0703 0.02205 0.01670 -0.1065 0.9161 0.0373
-4.500 -0.0426 0.02316 0.01758 -0.1056 0.9117 0.0393
-4.250 -0.0251 0.01903 0.01340 -0.1050 0.9063 0.0429
-4.000 0.0039 0.01813 0.01242 -0.1055 0.9030 0.0462
-3.750 0.0396 0.01514 0.00900 -0.1050 0.9008 0.0307
-3.500 0.0623 0.01405 0.00791 -0.1039 0.8953 0.0288
-3.250 0.0874 0.01302 0.00684 -0.1033 0.8907 0.0285
-3.000 0.1149 0.01227 0.00603 -0.1033 0.8871 0.0288
-2.750 0.1368 0.01172 0.00543 -0.1022 0.8818 0.0290
-2.500 0.1619 0.01141 0.00508 -0.1017 0.8765 0.0299
-2.250 0.1861 0.01062 0.00421 -0.1012 0.8723 0.0312
-2.000 0.2080 0.01021 0.00376 -0.1001 0.8666 0.0325
-1.750 0.2336 0.00990 0.00340 -0.0998 0.8613 0.0346
-1.500 0.2628 0.00964 0.00308 -0.1001 0.8572 0.0375
-1.250 0.2860 0.00945 0.00286 -0.0992 0.8509 0.0419
-1.000 0.3102 0.00886 0.00256 -0.0987 0.8454 0.1649
-0.750 0.3258 0.00768 0.00238 -0.0970 0.8394 0.5088
-0.500 0.3501 0.00753 0.00237 -0.0963 0.8330 0.5577
-0.250 0.3783 0.00741 0.00235 -0.0964 0.8279 0.6066
0.000 0.4005 0.00735 0.00240 -0.0952 0.8204 0.6417
0.250 0.4282 0.00731 0.00239 -0.0952 0.8144 0.6663
0.500 0.4528 0.00730 0.00241 -0.0945 0.8071 0.6825
0.750 0.4803 0.00728 0.00238 -0.0945 0.8005 0.6947
1.000 0.5056 0.00727 0.00240 -0.0940 0.7930 0.7068
1.250 0.5324 0.00727 0.00239 -0.0938 0.7859 0.7195
1.500 0.5575 0.00727 0.00243 -0.0932 0.7781 0.7325
2.000 0.6081 0.00727 0.00249 -0.0922 0.7621 0.7592
2.250 0.6348 0.00728 0.00251 -0.0920 0.7544 0.7727
2.500 0.6575 0.00728 0.00259 -0.0909 0.7445 0.7870
2.750 0.6818 0.00730 0.00265 -0.0901 0.7352 0.8022
3.000 0.7058 0.00733 0.00269 -0.0893 0.7242 0.8181
3.250 0.7267 0.00735 0.00274 -0.0877 0.7081 0.8344
3.500 0.7478 0.00738 0.00279 -0.0862 0.6920 0.8507
3.750 0.7696 0.00742 0.00286 -0.0850 0.6785 0.8672
4.000 0.7911 0.00745 0.00293 -0.0836 0.6643 0.8849
4.250 0.8134 0.00749 0.00302 -0.0824 0.6490 0.9066
4.500 0.8437 0.00759 0.00316 -0.0831 0.6271 0.9351
4.750 0.8883 0.00789 0.00336 -0.0871 0.5947 0.9698
5.000 0.9185 0.00816 0.00358 -0.0880 0.5687 1.0000
5.250 0.9328 0.00843 0.00374 -0.0854 0.5398 1.0000
5.500 0.9434 0.00880 0.00394 -0.0820 0.4993 1.0000
5.750 0.9521 0.00925 0.00418 -0.0782 0.4550 1.0000
6.000 0.9572 0.00980 0.00449 -0.0738 0.4064 1.0000
6.250 0.9646 0.01038 0.00484 -0.0700 0.3605 1.0000
6.500 0.9739 0.01099 0.00525 -0.0667 0.3157 1.0000
6.750 0.9823 0.01170 0.00571 -0.0633 0.2654 1.0000
7.000 0.9909 0.01248 0.00621 -0.0601 0.2138 1.0000
7.250 0.9995 0.01331 0.00678 -0.0570 0.1665 1.0000
7.500 1.0087 0.01416 0.00739 -0.0540 0.1235 1.0000
7.750 1.0141 0.01524 0.00815 -0.0506 0.0701 1.0000
8.000 1.0207 0.01631 0.00900 -0.0473 0.0395 1.0000
8.250 1.0343 0.01700 0.00968 -0.0452 0.0340 1.0000
8.500 1.0474 0.01774 0.01046 -0.0430 0.0306 1.0000
8.750 1.0621 0.01838 0.01117 -0.0411 0.0288 1.0000
9.000 1.0755 0.01911 0.01195 -0.0392 0.0269 1.0000
9.250 1.0848 0.02009 0.01298 -0.0367 0.0250 1.0000
9.500 1.0922 0.02123 0.01420 -0.0340 0.0237 1.0000
9.750 1.1056 0.02200 0.01504 -0.0322 0.0227 1.0000
10.000 1.1179 0.02286 0.01596 -0.0304 0.0215 1.0000
10.250 1.1291 0.02381 0.01696 -0.0285 0.0202 1.0000
10.500 1.1372 0.02500 0.01820 -0.0264 0.0192 1.0000
10.750 1.1343 0.02719 0.02048 -0.0230 0.0181 1.0000
11.000 1.1473 0.02813 0.02151 -0.0215 0.0176 1.0000
11.250 1.1588 0.02922 0.02268 -0.0200 0.0169 1.0000
11.500 1.1689 0.03049 0.02403 -0.0184 0.0162 1.0000
11.750 1.1791 0.03171 0.02532 -0.0169 0.0154 1.0000
12.000 1.1884 0.03305 0.02672 -0.0154 0.0148 1.0000
12.250 1.1965 0.03459 0.02831 -0.0140 0.0143 1.0000
12.500 1.2041 0.03720 0.03101 -0.0122 0.0135 1.0000
12.750 1.2117 0.03832 0.03227 -0.0109 0.0131 1.0000
13.000 1.2197 0.03990 0.03399 -0.0096 0.0126 1.0000
13.250 1.2272 0.04175 0.03597 -0.0083 0.0123 1.0000
13.500 1.2334 0.04375 0.03812 -0.0070 0.0120 1.0000
13.750 1.2380 0.04562 0.04010 -0.0059 0.0115 1.0000
14.000 1.2420 0.04786 0.04248 -0.0047 0.0113 1.0000
14.250 1.2436 0.05010 0.04485 -0.0038 0.0110 1.0000
14.500 1.2439 0.05286 0.04778 -0.0028 0.0109 1.0000
14.750 1.2428 0.05558 0.05062 -0.0021 0.0108 1.0000
15.000 1.2416 0.05832 0.05347 -0.0016 0.0106 1.0000
15.250 1.2370 0.06175 0.05704 -0.0012 0.0104 1.0000
15.500 1.2295 0.06569 0.06115 -0.0010 0.0103 1.0000
15.750 1.2128 0.07123 0.06691 -0.0011 0.0101 1.0000
16.000 1.2022 0.07568 0.07154 -0.0019 0.0101 1.0000
16.250 1.1835 0.08169 0.07777 -0.0032 0.0101 1.0000
16.500 1.1670 0.08758 0.08384 -0.0051 0.0101 1.0000
16.750 1.1549 0.09295 0.08938 -0.0074 0.0101 1.0000
17.000 1.1331 0.10041 0.09703 -0.0107 0.0101 1.0000
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Polar data table (+)
Polar graphs
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