AG16 (ag16-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: AG16 (ag16-il) Reynolds number: 200,000 Max Cl/Cd: 63.61 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ag16-il-200000.txt Download as CSV file: xf-ag16-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.5446 0.09185 0.08855 0.0050 1.0000 0.0412
-7.750 -0.5414 0.08787 0.08460 0.0023 1.0000 0.0427
-7.500 -0.5384 0.08344 0.08023 -0.0019 1.0000 0.0445
-7.250 -0.5224 0.07441 0.07118 -0.0216 1.0000 0.0472
-7.000 -0.5075 0.06673 0.06325 -0.0329 1.0000 0.0476
-6.750 -0.5037 0.06006 0.05670 -0.0336 1.0000 0.0491
-6.500 -0.4900 0.05741 0.05404 -0.0333 1.0000 0.0506
-6.250 -0.4729 0.05330 0.04985 -0.0361 1.0000 0.0530
-6.000 -0.4499 0.04460 0.04035 -0.0463 1.0000 0.0614
-5.750 -0.4268 0.03279 0.02798 -0.0482 1.0000 0.0316
-5.500 -0.4022 0.02834 0.02298 -0.0493 1.0000 0.0317
-5.250 -0.3763 0.02442 0.01848 -0.0497 1.0000 0.0311
-5.000 -0.3492 0.02071 0.01413 -0.0495 1.0000 0.0292
-4.750 -0.3221 0.01830 0.01132 -0.0490 1.0000 0.0291
-4.500 -0.2954 0.01656 0.00934 -0.0485 1.0000 0.0304
-4.250 -0.2689 0.01517 0.00780 -0.0479 1.0000 0.0331
-4.000 -0.2428 0.01386 0.00644 -0.0475 1.0000 0.0401
-3.750 -0.2162 0.01269 0.00524 -0.0471 1.0000 0.0505
-3.500 -0.1892 0.01158 0.00424 -0.0470 1.0000 0.0887
-3.250 -0.1626 0.01062 0.00369 -0.0472 1.0000 0.1724
-3.000 -0.1364 0.01010 0.00346 -0.0471 1.0000 0.2534
-2.750 -0.1102 0.00976 0.00330 -0.0469 1.0000 0.3197
-2.500 -0.0841 0.00946 0.00318 -0.0467 1.0000 0.3776
-2.250 -0.0580 0.00921 0.00305 -0.0465 1.0000 0.4315
-2.000 -0.0319 0.00897 0.00298 -0.0462 1.0000 0.4870
-1.750 -0.0060 0.00872 0.00295 -0.0459 1.0000 0.5495
-1.500 0.0196 0.00845 0.00293 -0.0455 1.0000 0.6192
-1.250 0.0441 0.00812 0.00292 -0.0447 1.0000 0.7068
-1.000 0.0626 0.00763 0.00293 -0.0421 1.0000 0.8658
-0.750 0.0970 0.00759 0.00288 -0.0437 0.9957 1.0000
-0.500 0.1457 0.00763 0.00281 -0.0482 0.9837 1.0000
-0.250 0.1927 0.00763 0.00271 -0.0521 0.9706 1.0000
0.000 0.2360 0.00760 0.00262 -0.0551 0.9548 1.0000
0.250 0.2724 0.00758 0.00254 -0.0564 0.9327 1.0000
0.500 0.3046 0.00757 0.00247 -0.0567 0.9080 1.0000
0.750 0.3322 0.00759 0.00241 -0.0560 0.8800 1.0000
1.000 0.3576 0.00766 0.00238 -0.0548 0.8502 1.0000
1.250 0.3827 0.00776 0.00236 -0.0536 0.8192 1.0000
1.500 0.4078 0.00790 0.00238 -0.0525 0.7873 1.0000
1.750 0.4333 0.00807 0.00242 -0.0516 0.7544 1.0000
2.000 0.4589 0.00827 0.00247 -0.0507 0.7216 1.0000
2.250 0.4848 0.00848 0.00255 -0.0499 0.6879 1.0000
2.500 0.5108 0.00872 0.00265 -0.0493 0.6542 1.0000
2.750 0.5369 0.00897 0.00280 -0.0486 0.6202 1.0000
3.000 0.5630 0.00923 0.00294 -0.0481 0.5853 1.0000
3.250 0.5892 0.00952 0.00310 -0.0476 0.5500 1.0000
3.500 0.6153 0.00983 0.00329 -0.0471 0.5144 1.0000
3.750 0.6415 0.01015 0.00354 -0.0466 0.4774 1.0000
4.000 0.6675 0.01051 0.00378 -0.0462 0.4398 1.0000
4.250 0.6934 0.01090 0.00405 -0.0458 0.4018 1.0000
4.500 0.7192 0.01131 0.00435 -0.0455 0.3633 1.0000
4.750 0.7450 0.01175 0.00469 -0.0451 0.3249 1.0000
5.000 0.7707 0.01224 0.00511 -0.0448 0.2872 1.0000
5.250 0.7961 0.01277 0.00553 -0.0445 0.2505 1.0000
5.500 0.8214 0.01335 0.00600 -0.0442 0.2138 1.0000
5.750 0.8466 0.01397 0.00654 -0.0438 0.1785 1.0000
6.000 0.8712 0.01473 0.00716 -0.0435 0.1421 1.0000
6.250 0.8953 0.01562 0.00796 -0.0431 0.1073 1.0000
6.500 0.9182 0.01680 0.00898 -0.0425 0.0786 1.0000
6.750 0.9417 0.01791 0.01012 -0.0419 0.0585 1.0000
7.000 0.9637 0.01931 0.01152 -0.0411 0.0446 1.0000
7.250 0.9859 0.02065 0.01294 -0.0402 0.0346 1.0000
7.500 1.0051 0.02302 0.01541 -0.0389 0.0293 1.0000
7.750 1.0278 0.02423 0.01676 -0.0381 0.0244 1.0000
8.000 1.0439 0.02787 0.02056 -0.0368 0.0211 1.0000
8.250 1.0651 0.02987 0.02289 -0.0357 0.0201 1.0000
8.500 1.0834 0.03273 0.02621 -0.0343 0.0194 1.0000
8.750 1.0981 0.03625 0.03019 -0.0329 0.0190 1.0000
9.000 1.1080 0.04038 0.03483 -0.0314 0.0190 1.0000
9.250 1.1120 0.04505 0.04001 -0.0298 0.0192 1.0000
9.500 1.1098 0.05004 0.04546 -0.0284 0.0195 1.0000
9.750 1.1015 0.05513 0.05092 -0.0273 0.0199 1.0000
10.000 1.0869 0.06001 0.05610 -0.0264 0.0202 1.0000
10.250 1.0676 0.06461 0.06090 -0.0262 0.0204 1.0000
10.500 1.0475 0.07006 0.06653 -0.0287 0.0206 1.0000
10.750 1.0273 0.07690 0.07352 -0.0337 0.0207 1.0000
11.500 0.9572 0.11383 0.11082 -0.0616 0.0236 1.0000
11.750 0.9248 0.13001 0.12689 -0.0698 0.0273 1.0000
12.000 0.9186 0.13652 0.13337 -0.0722 0.0291 1.0000
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Polar data table (+)
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