AG16 (ag16-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: AG16 (ag16-il) Reynolds number: 100,000 Max Cl/Cd: 48.63 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ag16-il-100000.txt Download as CSV file: xf-ag16-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: AG16
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
------ -------- --------- --------- -------- -------- --------
-10.250 -0.5723 0.13095 0.12599 0.0211 1.0000 0.0699
-10.000 -0.5752 0.12823 0.12332 0.0171 1.0000 0.0723
-9.750 -0.5816 0.12581 0.12098 0.0117 1.0000 0.0731
-9.500 -0.5659 0.11965 0.11482 0.0150 1.0000 0.0758
-9.250 -0.5556 0.11617 0.11134 0.0155 1.0000 0.0806
-9.000 -0.5557 0.11294 0.10816 0.0124 1.0000 0.0846
-8.750 -0.5641 0.11027 0.10558 0.0059 1.0000 0.0862
-8.500 -0.5538 0.10495 0.10029 0.0074 1.0000 0.0886
-8.250 -0.5419 0.10136 0.09665 0.0086 1.0000 0.0925
-8.000 -0.5397 0.09789 0.09322 0.0060 1.0000 0.0968
-7.750 -0.5512 0.09425 0.08976 -0.0090 1.0000 0.0999
-7.500 -0.5385 0.08971 0.08519 -0.0012 1.0000 0.1023
-7.250 -0.5272 0.08630 0.08180 -0.0006 1.0000 0.1067
-7.000 -0.5233 0.07958 0.07508 -0.0199 1.0000 0.1140
-6.750 -0.5113 0.07681 0.07238 -0.0119 1.0000 0.1167
-6.250 -0.4851 0.06750 0.06304 -0.0211 1.0000 0.1305
-6.000 -0.4229 0.05057 0.04645 -0.0236 1.0000 0.1438
-5.750 -0.4128 0.03013 0.02482 -0.0447 1.0000 0.0745
-5.500 -0.3930 0.02326 0.01739 -0.0463 1.0000 0.0582
-5.250 -0.3721 0.01874 0.01239 -0.0473 1.0000 0.0548
-5.000 -0.3481 0.01501 0.00796 -0.0478 1.0000 0.0530
-4.750 -0.3232 0.01291 0.00536 -0.0477 1.0000 0.0572
-4.500 -0.2968 0.01103 0.00287 -0.0472 1.0000 0.0601
-4.250 -0.2719 0.00870 0.00041 -0.0468 1.0000 0.0643
-4.000 -0.2482 0.01825 0.00938 -0.0483 1.0000 0.0766
-3.750 -0.2218 0.01666 0.00779 -0.0477 1.0000 0.0974
-3.500 -0.1955 0.01513 0.00653 -0.0474 1.0000 0.1523
-3.250 -0.1697 0.01396 0.00586 -0.0473 1.0000 0.2513
-3.000 -0.1445 0.01329 0.00553 -0.0469 1.0000 0.3445
-2.750 -0.1196 0.01281 0.00528 -0.0463 1.0000 0.4185
-2.500 -0.0951 0.01239 0.00506 -0.0455 1.0000 0.4871
-2.250 -0.0713 0.01198 0.00483 -0.0444 1.0000 0.5563
-2.000 -0.0483 0.01152 0.00464 -0.0431 1.0000 0.6304
-1.750 -0.0268 0.01101 0.00445 -0.0412 1.0000 0.7224
-1.500 -0.0078 0.01023 0.00418 -0.0379 1.0000 0.9191
-1.250 0.0220 0.01020 0.00386 -0.0390 1.0000 1.0000
-1.000 0.0490 0.01028 0.00373 -0.0393 1.0000 1.0000
-0.750 0.0753 0.01040 0.00368 -0.0395 1.0000 1.0000
-0.500 0.1011 0.01056 0.00371 -0.0397 1.0000 1.0000
-0.250 0.1265 0.01076 0.00381 -0.0399 1.0000 1.0000
0.000 0.1514 0.01101 0.00397 -0.0401 1.0000 1.0000
0.250 0.1757 0.01133 0.00423 -0.0405 1.0000 1.0000
0.500 0.2148 0.01167 0.00454 -0.0437 0.9925 1.0000
0.750 0.2734 0.01185 0.00471 -0.0502 0.9726 1.0000
1.000 0.3316 0.01189 0.00477 -0.0562 0.9535 1.0000
1.250 0.3791 0.01185 0.00478 -0.0595 0.9292 1.0000
1.500 0.4183 0.01180 0.00478 -0.0609 0.9019 1.0000
1.750 0.4500 0.01178 0.00475 -0.0605 0.8724 1.0000
2.000 0.4761 0.01183 0.00477 -0.0590 0.8394 1.0000
2.250 0.5006 0.01192 0.00479 -0.0572 0.8060 1.0000
2.500 0.5245 0.01206 0.00486 -0.0554 0.7714 1.0000
2.750 0.5483 0.01226 0.00501 -0.0536 0.7361 1.0000
3.000 0.5724 0.01250 0.00516 -0.0521 0.6992 1.0000
3.250 0.5966 0.01278 0.00532 -0.0506 0.6623 1.0000
3.500 0.6211 0.01311 0.00553 -0.0493 0.6244 1.0000
3.750 0.6457 0.01347 0.00583 -0.0481 0.5847 1.0000
4.000 0.6703 0.01386 0.00611 -0.0471 0.5444 1.0000
4.250 0.6949 0.01430 0.00644 -0.0460 0.5032 1.0000
4.500 0.7193 0.01479 0.00681 -0.0451 0.4614 1.0000
4.750 0.7437 0.01533 0.00722 -0.0442 0.4191 1.0000
5.000 0.7679 0.01593 0.00774 -0.0434 0.3767 1.0000
5.250 0.7919 0.01660 0.00828 -0.0426 0.3346 1.0000
5.500 0.8157 0.01734 0.00891 -0.0419 0.2919 1.0000
5.750 0.8391 0.01818 0.00964 -0.0412 0.2493 1.0000
6.000 0.8621 0.01917 0.01051 -0.0405 0.2071 1.0000
6.250 0.8845 0.02038 0.01158 -0.0397 0.1671 1.0000
6.500 0.9062 0.02178 0.01285 -0.0389 0.1320 1.0000
6.750 0.9280 0.02354 0.01448 -0.0380 0.1050 1.0000
7.000 0.9503 0.02519 0.01626 -0.0371 0.0836 1.0000
7.250 0.9725 0.02733 0.01844 -0.0360 0.0696 1.0000
7.500 0.9946 0.02976 0.02107 -0.0350 0.0591 1.0000
7.750 1.0155 0.03294 0.02440 -0.0340 0.0525 1.0000
8.000 1.0358 0.03516 0.02703 -0.0329 0.0460 1.0000
8.250 1.0536 0.03888 0.03098 -0.0319 0.0433 1.0000
8.500 1.0652 0.04464 0.03725 -0.0307 0.0423 1.0000
8.750 1.0736 0.04926 0.04245 -0.0294 0.0420 1.0000
9.000 1.0775 0.05358 0.04739 -0.0280 0.0414 1.0000
9.250 1.0758 0.05830 0.05264 -0.0270 0.0410 1.0000
9.500 1.0686 0.06333 0.05814 -0.0264 0.0409 1.0000
9.750 1.0570 0.06845 0.06356 -0.0262 0.0411 1.0000
10.000 1.0412 0.07340 0.06863 -0.0263 0.0414 1.0000
10.250 1.0253 0.07879 0.07413 -0.0274 0.0419 1.0000
10.500 0.9588 0.09663 0.09241 -0.0456 0.0511 1.0000
10.750 0.9480 0.10453 0.10028 -0.0498 0.0526 1.0000
11.000 0.9514 0.10873 0.10450 -0.0492 0.0547 1.0000
11.250 0.7442 0.13207 0.12782 -0.0522 0.1303 1.0000
11.500 0.7191 0.13644 0.13212 -0.0566 0.1270 1.0000
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Polar data table (+)
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