AG36 (ag36-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: AG36 (ag36-il) Reynolds number: 1,000,000 Max Cl/Cd: 103 at α=3.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ag36-il-1000000.txt Download as CSV file: xf-ag36-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: AG36
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.4449 0.06978 0.06832 -0.0170 1.0000 0.0128
-9.750 -0.4490 0.06520 0.06376 -0.0189 1.0000 0.0129
-9.500 -0.4561 0.06021 0.05879 -0.0215 1.0000 0.0129
-9.250 -0.4693 0.05363 0.05223 -0.0276 1.0000 0.0129
-9.000 -0.4721 0.04672 0.04527 -0.0342 1.0000 0.0130
-8.750 -0.4764 0.03774 0.03617 -0.0401 1.0000 0.0130
-8.500 -0.4749 0.03160 0.02989 -0.0420 1.0000 0.0132
-8.250 -0.5242 0.02585 0.02289 -0.0440 1.0000 0.0106
-8.000 -0.5149 0.01946 0.01573 -0.0422 1.0000 0.0107
-7.750 -0.4963 0.01724 0.01316 -0.0408 1.0000 0.0109
-7.500 -0.4644 0.01530 0.01092 -0.0420 0.9983 0.0112
-7.250 -0.4310 0.01391 0.00931 -0.0433 0.9963 0.0115
-7.000 -0.3962 0.01321 0.00849 -0.0447 0.9946 0.0121
-6.750 -0.3641 0.01184 0.00692 -0.0457 0.9919 0.0127
-6.500 -0.3314 0.01076 0.00574 -0.0469 0.9888 0.0135
-6.250 -0.2976 0.01027 0.00522 -0.0481 0.9853 0.0142
-6.000 -0.2654 0.00980 0.00470 -0.0489 0.9801 0.0149
-5.750 -0.2344 0.00935 0.00420 -0.0495 0.9725 0.0157
-5.500 -0.2052 0.00902 0.00381 -0.0495 0.9625 0.0165
-5.250 -0.1781 0.00842 0.00313 -0.0492 0.9505 0.0181
-5.000 -0.1518 0.00817 0.00285 -0.0486 0.9353 0.0198
-4.750 -0.1258 0.00796 0.00257 -0.0479 0.9173 0.0215
-4.500 -0.0997 0.00773 0.00225 -0.0472 0.8948 0.0235
-4.250 -0.0739 0.00752 0.00194 -0.0465 0.8668 0.0278
-4.000 -0.0470 0.00741 0.00171 -0.0460 0.8445 0.0330
-3.500 0.0077 0.00705 0.00138 -0.0456 0.8094 0.0763
-3.250 0.0352 0.00681 0.00126 -0.0455 0.7927 0.1280
-3.000 0.0627 0.00655 0.00116 -0.0454 0.7755 0.1968
-2.750 0.0901 0.00630 0.00109 -0.0454 0.7569 0.2749
-2.500 0.1175 0.00608 0.00104 -0.0454 0.7360 0.3564
-2.250 0.1447 0.00580 0.00100 -0.0453 0.7096 0.4637
-2.000 0.1706 0.00537 0.00096 -0.0451 0.6597 0.6359
-1.750 0.1940 0.00504 0.00098 -0.0442 0.6143 0.8100
-1.500 0.2139 0.00484 0.00103 -0.0419 0.5933 0.9380
-1.250 0.2532 0.00489 0.00102 -0.0442 0.5759 0.9934
-1.000 0.2857 0.00498 0.00102 -0.0453 0.5620 1.0000
-0.750 0.3131 0.00508 0.00103 -0.0451 0.5500 1.0000
-0.500 0.3406 0.00516 0.00105 -0.0450 0.5389 1.0000
-0.250 0.3684 0.00524 0.00107 -0.0450 0.5284 1.0000
0.000 0.3961 0.00533 0.00110 -0.0449 0.5185 1.0000
0.250 0.4239 0.00542 0.00113 -0.0449 0.5079 1.0000
0.500 0.4519 0.00549 0.00118 -0.0449 0.4974 1.0000
0.750 0.4799 0.00558 0.00122 -0.0449 0.4863 1.0000
1.000 0.5078 0.00567 0.00127 -0.0450 0.4744 1.0000
1.250 0.5358 0.00576 0.00132 -0.0450 0.4595 1.0000
1.500 0.5636 0.00588 0.00138 -0.0451 0.4421 1.0000
1.750 0.5913 0.00603 0.00145 -0.0451 0.4220 1.0000
2.000 0.6190 0.00618 0.00154 -0.0451 0.4024 1.0000
2.250 0.6463 0.00638 0.00165 -0.0451 0.3781 1.0000
2.500 0.6737 0.00658 0.00177 -0.0452 0.3545 1.0000
2.750 0.7009 0.00682 0.00191 -0.0452 0.3283 1.0000
3.000 0.7279 0.00708 0.00207 -0.0452 0.3032 1.0000
3.250 0.7550 0.00733 0.00224 -0.0452 0.2797 1.0000
3.500 0.7819 0.00761 0.00242 -0.0452 0.2540 1.0000
3.750 0.8085 0.00793 0.00263 -0.0452 0.2259 1.0000
4.000 0.8346 0.00833 0.00287 -0.0452 0.1933 1.0000
4.250 0.8610 0.00868 0.00313 -0.0452 0.1682 1.0000
4.500 0.8873 0.00903 0.00339 -0.0451 0.1456 1.0000
4.750 0.9133 0.00943 0.00367 -0.0451 0.1235 1.0000
5.000 0.9392 0.00981 0.00397 -0.0450 0.1033 1.0000
5.250 0.9649 0.01024 0.00431 -0.0449 0.0837 1.0000
5.500 0.9903 0.01069 0.00467 -0.0448 0.0652 1.0000
5.750 1.0153 0.01119 0.00508 -0.0446 0.0478 1.0000
6.000 1.0397 0.01178 0.00556 -0.0444 0.0311 1.0000
6.250 1.0642 0.01233 0.00608 -0.0441 0.0212 1.0000
6.500 1.0887 0.01288 0.00662 -0.0438 0.0159 1.0000
6.750 1.1126 0.01351 0.00726 -0.0434 0.0125 1.0000
7.000 1.1372 0.01399 0.00780 -0.0432 0.0110 1.0000
7.250 1.1612 0.01454 0.00838 -0.0428 0.0098 1.0000
7.500 1.1828 0.01545 0.00939 -0.0421 0.0085 1.0000
7.750 1.2065 0.01597 0.00998 -0.0418 0.0081 1.0000
8.000 1.2294 0.01659 0.01067 -0.0413 0.0075 1.0000
8.250 1.2517 0.01726 0.01140 -0.0408 0.0071 1.0000
8.500 1.2729 0.01803 0.01223 -0.0402 0.0067 1.0000
8.750 1.2897 0.01932 0.01365 -0.0390 0.0062 1.0000
9.000 1.3047 0.02074 0.01522 -0.0375 0.0059 1.0000
9.250 1.3248 0.02148 0.01605 -0.0368 0.0057 1.0000
9.500 1.3428 0.02239 0.01706 -0.0358 0.0056 1.0000
9.750 1.3586 0.02349 0.01826 -0.0346 0.0054 1.0000
10.000 1.3725 0.02470 0.01959 -0.0332 0.0053 1.0000
10.250 1.3845 0.02600 0.02101 -0.0316 0.0052 1.0000
10.500 1.3939 0.02738 0.02252 -0.0297 0.0051 1.0000
10.750 1.3983 0.02881 0.02407 -0.0271 0.0050 1.0000
11.000 1.4006 0.03039 0.02579 -0.0246 0.0049 1.0000
11.250 1.4014 0.03224 0.02777 -0.0225 0.0049 1.0000
11.500 1.4013 0.03436 0.03003 -0.0210 0.0048 1.0000
11.750 1.3997 0.03687 0.03267 -0.0200 0.0048 1.0000
12.000 1.3968 0.03980 0.03574 -0.0197 0.0047 1.0000
12.250 1.3927 0.04313 0.03922 -0.0200 0.0047 1.0000
12.500 1.3868 0.04700 0.04324 -0.0209 0.0046 1.0000
12.750 1.3790 0.05146 0.04785 -0.0224 0.0046 1.0000
13.000 1.3701 0.05646 0.05301 -0.0247 0.0046 1.0000
13.250 1.3584 0.06202 0.05872 -0.0272 0.0046 1.0000
13.500 1.3444 0.06807 0.06492 -0.0300 0.0046 1.0000
13.750 1.3277 0.07461 0.07161 -0.0330 0.0046 1.0000
14.000 1.3091 0.08169 0.07884 -0.0364 0.0046 1.0000
14.250 1.2891 0.08928 0.08657 -0.0400 0.0046 1.0000
14.500 1.2686 0.09734 0.09477 -0.0439 0.0046 1.0000
14.750 1.2460 0.10608 0.10366 -0.0482 0.0047 1.0000
15.000 1.2229 0.11532 0.11304 -0.0528 0.0047 1.0000
15.250 1.2000 0.12481 0.12266 -0.0575 0.0047 1.0000
15.500 1.1761 0.13486 0.13284 -0.0626 0.0048 1.0000
15.750 1.1482 0.14650 0.14463 -0.0686 0.0049 1.0000
16.000 1.1148 0.16044 0.15873 -0.0758 0.0050 1.0000
16.250 0.8634 0.14771 0.14607 -0.0485 0.0055 1.0000
|
Polar data table (+)
Polar graphs
<< Back to AG36 (ag36-il)