AG17 (ag17-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: AG17 (ag17-il) Reynolds number: 50,000 Max Cl/Cd: 34.56 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ag17-il-50000.txt Download as CSV file: xf-ag17-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: AG17
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.5525 0.11587 0.10926 0.0146 1.0000 0.1833
-8.250 -0.5338 0.11018 0.10355 0.0163 1.0000 0.1916
-8.000 -0.5478 0.10947 0.10299 0.0118 1.0000 0.1973
-7.750 -0.5321 0.10450 0.09802 0.0133 1.0000 0.2097
-7.500 -0.5217 0.10040 0.09396 0.0138 1.0000 0.2212
-7.250 -0.5152 0.09681 0.09043 0.0135 1.0000 0.2323
-7.000 -0.5113 0.09353 0.08723 0.0128 1.0000 0.2437
-6.750 -0.5065 0.09023 0.08399 0.0116 1.0000 0.2563
-6.500 -0.4994 0.08676 0.08059 0.0103 1.0000 0.2696
-6.250 -0.4904 0.08319 0.07707 0.0096 1.0000 0.2840
-6.000 -0.4804 0.07961 0.07354 0.0091 1.0000 0.2997
-5.500 -0.4617 0.07270 0.06673 0.0067 1.0000 0.3376
-5.250 -0.4485 0.06906 0.06307 0.0073 1.0000 0.3561
-5.000 -0.3695 0.04711 0.03965 -0.0438 1.0000 0.1285
-4.750 -0.3395 0.04090 0.03285 -0.0472 1.0000 0.1143
-4.500 -0.3118 0.03639 0.02793 -0.0487 1.0000 0.1107
-4.250 -0.2812 0.03254 0.02329 -0.0502 1.0000 0.1144
-4.000 -0.2536 0.02936 0.01974 -0.0505 1.0000 0.1201
-3.750 -0.2236 0.02645 0.01627 -0.0504 1.0000 0.1263
-3.500 -0.1962 0.02428 0.01393 -0.0501 1.0000 0.1472
-3.250 -0.1683 0.02209 0.01163 -0.0494 1.0000 0.1750
-3.000 -0.1420 0.02029 0.00999 -0.0486 1.0000 0.2395
-2.750 -0.1172 0.01861 0.00894 -0.0474 1.0000 0.3640
-2.500 -0.0966 0.01714 0.00824 -0.0449 1.0000 0.5228
-2.250 -0.0820 0.01582 0.00757 -0.0405 1.0000 0.6752
-2.000 -0.0582 0.01408 0.00647 -0.0370 1.0000 1.0000
-1.750 -0.0244 0.01402 0.00568 -0.0395 1.0000 1.0000
-1.500 0.0034 0.01403 0.00524 -0.0400 1.0000 1.0000
-1.250 0.0299 0.01407 0.00493 -0.0401 1.0000 1.0000
-1.000 0.0558 0.01413 0.00467 -0.0401 1.0000 1.0000
-0.750 0.0813 0.01421 0.00453 -0.0400 1.0000 1.0000
-0.500 0.1064 0.01433 0.00446 -0.0398 1.0000 1.0000
-0.250 0.1311 0.01447 0.00446 -0.0397 1.0000 1.0000
0.000 0.1555 0.01466 0.00450 -0.0396 1.0000 1.0000
0.250 0.1796 0.01488 0.00464 -0.0395 1.0000 1.0000
0.500 0.2036 0.01515 0.00485 -0.0395 1.0000 1.0000
0.750 0.2272 0.01549 0.00514 -0.0397 1.0000 1.0000
1.000 0.2503 0.01589 0.00553 -0.0399 1.0000 1.0000
1.250 0.2727 0.01638 0.00602 -0.0402 1.0000 1.0000
1.500 0.2944 0.01698 0.00663 -0.0408 1.0000 1.0000
1.750 0.3152 0.01771 0.00740 -0.0415 1.0000 1.0000
2.000 0.3350 0.01861 0.00835 -0.0425 1.0000 1.0000
2.250 0.4128 0.01953 0.00952 -0.0537 0.9686 1.0000
2.500 0.4950 0.01987 0.01016 -0.0640 0.9270 1.0000
2.750 0.5564 0.01983 0.01039 -0.0687 0.8837 1.0000
3.000 0.5975 0.01973 0.01055 -0.0687 0.8395 1.0000
3.250 0.6271 0.01970 0.01061 -0.0663 0.7950 1.0000
3.500 0.6510 0.01976 0.01068 -0.0628 0.7504 1.0000
3.750 0.6727 0.02000 0.01089 -0.0594 0.7031 1.0000
4.000 0.6943 0.02032 0.01122 -0.0561 0.6550 1.0000
4.250 0.7159 0.02080 0.01160 -0.0531 0.6052 1.0000
4.500 0.7379 0.02135 0.01199 -0.0504 0.5566 1.0000
4.750 0.7600 0.02210 0.01263 -0.0481 0.5055 1.0000
5.000 0.7824 0.02296 0.01335 -0.0461 0.4563 1.0000
5.250 0.8048 0.02395 0.01426 -0.0442 0.4081 1.0000
5.500 0.8273 0.02511 0.01528 -0.0426 0.3616 1.0000
5.750 0.8497 0.02644 0.01654 -0.0411 0.3167 1.0000
6.000 0.8722 0.02799 0.01801 -0.0397 0.2758 1.0000
6.250 0.8949 0.02975 0.01966 -0.0384 0.2394 1.0000
6.500 0.9166 0.03157 0.02154 -0.0372 0.2048 1.0000
6.750 0.9393 0.03420 0.02437 -0.0360 0.1795 1.0000
7.000 0.9598 0.03650 0.02689 -0.0349 0.1543 1.0000
7.250 0.9806 0.04012 0.03093 -0.0337 0.1398 1.0000
7.500 0.9993 0.04308 0.03412 -0.0327 0.1237 1.0000
7.750 1.0136 0.04761 0.03924 -0.0317 0.1154 1.0000
8.000 1.0246 0.05283 0.04506 -0.0309 0.1116 1.0000
8.250 1.0363 0.05742 0.04984 -0.0302 0.1058 1.0000
8.500 1.0334 0.06355 0.05664 -0.0304 0.1044 1.0000
8.750 1.0268 0.06987 0.06338 -0.0312 0.1041 1.0000
9.000 1.0173 0.07624 0.07003 -0.0325 0.1048 1.0000
9.250 1.0074 0.08253 0.07646 -0.0341 0.1058 1.0000
9.500 0.9960 0.08892 0.08298 -0.0363 0.1080 1.0000
|
Polar data table (+)
Polar graphs
<< Back to AG17 (ag17-il)