AG19 (ag19-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: AG19 (ag19-il) Reynolds number: 100,000 Max Cl/Cd: 48.61 at α=4° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ag19-il-100000-n5.txt Download as CSV file: xf-ag19-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: AG19
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.5320 0.10933 0.10441 0.0143 1.0000 0.0369
-8.250 -0.5300 0.10654 0.10169 0.0097 1.0000 0.0384
-8.000 -0.5267 0.10350 0.09871 0.0052 1.0000 0.0388
-7.750 -0.5203 0.09994 0.09521 0.0005 1.0000 0.0391
-7.500 -0.5093 0.09571 0.09100 -0.0055 1.0000 0.0392
-7.250 -0.5072 0.09098 0.08632 0.0031 1.0000 0.0421
-7.000 -0.4975 0.08741 0.08278 0.0012 1.0000 0.0439
-6.750 -0.4864 0.08339 0.07879 -0.0026 1.0000 0.0451
-6.500 -0.4732 0.07905 0.07446 -0.0073 1.0000 0.0458
-6.250 -0.4576 0.07441 0.06982 -0.0126 1.0000 0.0462
-6.000 -0.4394 0.06938 0.06477 -0.0183 1.0000 0.0455
-5.750 -0.4080 0.05969 0.05487 -0.0295 1.0000 0.0257
-5.500 -0.3871 0.05459 0.04967 -0.0336 1.0000 0.0245
-5.250 -0.3619 0.04900 0.04390 -0.0384 1.0000 0.0234
-5.000 -0.3341 0.04318 0.03781 -0.0429 1.0000 0.0224
-4.750 -0.3049 0.03750 0.03172 -0.0466 1.0000 0.0216
-4.500 -0.2753 0.03241 0.02605 -0.0491 1.0000 0.0210
-4.250 -0.2457 0.02815 0.02119 -0.0506 1.0000 0.0207
-4.000 -0.2166 0.02482 0.01727 -0.0513 1.0000 0.0209
-3.750 -0.1883 0.02230 0.01424 -0.0514 1.0000 0.0219
-3.500 -0.1605 0.02064 0.01217 -0.0512 1.0000 0.0253
-3.250 -0.1329 0.01906 0.01022 -0.0508 1.0000 0.0274
-3.000 -0.1063 0.01716 0.00818 -0.0505 1.0000 0.0299
-2.750 -0.0798 0.01601 0.00694 -0.0501 1.0000 0.0342
-2.500 -0.0534 0.01511 0.00594 -0.0498 1.0000 0.0444
-2.250 -0.0266 0.01421 0.00500 -0.0494 1.0000 0.0595
-2.000 0.0001 0.01337 0.00432 -0.0493 1.0000 0.0997
-1.750 0.0264 0.01257 0.00394 -0.0493 1.0000 0.1972
-1.500 0.0523 0.01184 0.00375 -0.0493 1.0000 0.3492
-1.250 0.0777 0.01106 0.00361 -0.0489 1.0000 0.5490
-1.000 0.0960 0.00991 0.00341 -0.0459 1.0000 1.0000
-0.750 0.1221 0.00998 0.00327 -0.0457 1.0000 1.0000
-0.500 0.1478 0.01007 0.00320 -0.0454 1.0000 1.0000
-0.250 0.1861 0.01017 0.00314 -0.0478 0.9887 1.0000
0.000 0.2292 0.01025 0.00305 -0.0509 0.9713 1.0000
0.250 0.2690 0.01031 0.00300 -0.0532 0.9506 1.0000
0.500 0.3077 0.01035 0.00297 -0.0552 0.9282 1.0000
0.750 0.3430 0.01040 0.00294 -0.0563 0.9021 1.0000
1.000 0.3756 0.01047 0.00292 -0.0567 0.8733 1.0000
1.250 0.4048 0.01055 0.00293 -0.0564 0.8408 1.0000
1.500 0.4322 0.01067 0.00294 -0.0556 0.8064 1.0000
1.750 0.4583 0.01083 0.00302 -0.0546 0.7692 1.0000
2.000 0.4839 0.01101 0.00307 -0.0535 0.7298 1.0000
2.250 0.5094 0.01124 0.00316 -0.0525 0.6873 1.0000
2.500 0.5348 0.01151 0.00327 -0.0515 0.6415 1.0000
2.750 0.5600 0.01183 0.00341 -0.0506 0.5918 1.0000
3.000 0.5850 0.01220 0.00364 -0.0497 0.5400 1.0000
3.250 0.6099 0.01263 0.00386 -0.0489 0.4885 1.0000
3.500 0.6350 0.01309 0.00413 -0.0482 0.4392 1.0000
3.750 0.6601 0.01359 0.00445 -0.0476 0.3936 1.0000
4.000 0.6854 0.01410 0.00482 -0.0472 0.3521 1.0000
4.250 0.7106 0.01464 0.00530 -0.0467 0.3137 1.0000
4.500 0.7360 0.01518 0.00576 -0.0463 0.2784 1.0000
4.750 0.7612 0.01576 0.00626 -0.0459 0.2460 1.0000
5.000 0.7864 0.01635 0.00682 -0.0455 0.2156 1.0000
5.250 0.8115 0.01699 0.00742 -0.0452 0.1877 1.0000
5.500 0.8363 0.01768 0.00815 -0.0448 0.1620 1.0000
5.750 0.8610 0.01842 0.00891 -0.0444 0.1398 1.0000
6.000 0.8855 0.01921 0.00972 -0.0439 0.1188 1.0000
6.250 0.9096 0.02010 0.01067 -0.0434 0.1022 1.0000
6.500 0.9332 0.02106 0.01164 -0.0430 0.0857 1.0000
6.750 0.9564 0.02217 0.01282 -0.0424 0.0728 1.0000
7.000 0.9791 0.02333 0.01407 -0.0418 0.0598 1.0000
7.250 1.0018 0.02458 0.01558 -0.0411 0.0496 1.0000
7.500 1.0237 0.02602 0.01721 -0.0404 0.0404 1.0000
7.750 1.0438 0.02784 0.01919 -0.0395 0.0341 1.0000
8.000 1.0642 0.02966 0.02128 -0.0386 0.0288 1.0000
8.250 1.0823 0.03177 0.02358 -0.0378 0.0244 1.0000
8.500 1.1001 0.03451 0.02676 -0.0365 0.0219 1.0000
8.750 1.1155 0.03755 0.03022 -0.0354 0.0201 1.0000
9.000 1.1294 0.04010 0.03305 -0.0345 0.0182 1.0000
9.500 1.1423 0.04745 0.04123 -0.0325 0.0155 1.0000
9.750 1.1413 0.05189 0.04619 -0.0316 0.0149 1.0000
10.000 1.1330 0.05672 0.05145 -0.0310 0.0147 1.0000
10.250 1.1177 0.06143 0.05648 -0.0308 0.0146 1.0000
10.500 1.0994 0.06679 0.06207 -0.0329 0.0147 1.0000
10.750 1.0808 0.07368 0.06916 -0.0382 0.0149 1.0000
11.000 1.0619 0.08258 0.07820 -0.0458 0.0152 1.0000
11.250 1.0431 0.09250 0.08819 -0.0534 0.0158 1.0000
11.500 1.0249 0.10206 0.09776 -0.0593 0.0163 1.0000
|
Polar data table (+)
Polar graphs
<< Back to AG19 (ag19-il)