AG18 (ag18-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: AG18 (ag18-il) Reynolds number: 200,000 Max Cl/Cd: 65.13 at α=3.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ag18-il-200000.txt Download as CSV file: xf-ag18-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: AG18
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
------ -------- --------- --------- -------- -------- --------
-7.750 -0.5240 0.09492 0.09154 0.0095 1.0000 0.0315
-7.500 -0.5188 0.09136 0.08802 0.0074 1.0000 0.0326
-7.250 -0.5133 0.08768 0.08438 0.0045 1.0000 0.0337
-7.000 -0.5035 0.08345 0.08017 -0.0003 1.0000 0.0352
-6.750 -0.4854 0.07821 0.07495 -0.0103 1.0000 0.0373
-6.500 -0.4560 0.07188 0.06852 -0.0242 1.0000 0.0383
-6.250 -0.4331 0.06600 0.06248 -0.0317 1.0000 0.0385
-6.000 -0.4302 0.05971 0.05630 -0.0318 1.0000 0.0400
-5.750 -0.4160 0.05695 0.05356 -0.0317 1.0000 0.0419
-5.500 -0.3944 0.05284 0.04937 -0.0352 1.0000 0.0448
-5.250 -0.3544 0.04523 0.04101 -0.0460 1.0000 0.0517
-5.000 -0.3433 0.04293 0.03909 -0.0441 1.0000 0.0563
-4.750 -0.3123 0.03762 0.03321 -0.0488 1.0000 0.0660
-4.500 -0.2906 0.03492 0.03054 -0.0490 1.0000 0.0693
-4.000 -0.2229 0.02219 0.01619 -0.0514 1.0000 0.0345
-3.750 -0.1930 0.01838 0.01166 -0.0512 1.0000 0.0300
-3.500 -0.1651 0.01625 0.00914 -0.0506 1.0000 0.0293
-3.250 -0.1381 0.01471 0.00742 -0.0501 1.0000 0.0308
-3.000 -0.1114 0.01373 0.00635 -0.0496 1.0000 0.0357
-2.750 -0.0846 0.01244 0.00500 -0.0492 1.0000 0.0424
-2.500 -0.0573 0.01144 0.00399 -0.0489 1.0000 0.0567
-2.250 -0.0294 0.01038 0.00321 -0.0490 1.0000 0.1203
-2.000 -0.0021 0.00938 0.00293 -0.0495 1.0000 0.2872
-1.750 0.0242 0.00877 0.00285 -0.0495 1.0000 0.4410
-1.500 0.0496 0.00818 0.00280 -0.0490 1.0000 0.5931
-1.250 0.0684 0.00712 0.00267 -0.0461 1.0000 1.0000
-1.000 0.0952 0.00719 0.00257 -0.0460 1.0000 1.0000
-0.750 0.1219 0.00728 0.00253 -0.0460 1.0000 1.0000
-0.500 0.1483 0.00740 0.00255 -0.0460 1.0000 1.0000
-0.250 0.1829 0.00752 0.00256 -0.0478 0.9955 1.0000
0.000 0.2314 0.00755 0.00252 -0.0521 0.9828 1.0000
0.250 0.2774 0.00754 0.00245 -0.0557 0.9687 1.0000
0.500 0.3170 0.00752 0.00240 -0.0578 0.9485 1.0000
0.750 0.3535 0.00750 0.00233 -0.0591 0.9263 1.0000
1.000 0.3835 0.00750 0.00228 -0.0589 0.8990 1.0000
1.250 0.4095 0.00756 0.00225 -0.0578 0.8682 1.0000
1.500 0.4343 0.00765 0.00225 -0.0564 0.8356 1.0000
1.750 0.4589 0.00779 0.00228 -0.0551 0.8010 1.0000
2.000 0.4836 0.00796 0.00231 -0.0539 0.7643 1.0000
2.250 0.5086 0.00817 0.00237 -0.0528 0.7250 1.0000
2.500 0.5337 0.00841 0.00245 -0.0518 0.6832 1.0000
2.750 0.5590 0.00868 0.00255 -0.0509 0.6377 1.0000
3.000 0.5843 0.00900 0.00271 -0.0501 0.5888 1.0000
3.250 0.6096 0.00936 0.00287 -0.0494 0.5378 1.0000
3.500 0.6349 0.00977 0.00307 -0.0488 0.4860 1.0000
3.750 0.6603 0.01022 0.00331 -0.0483 0.4364 1.0000
4.000 0.6859 0.01068 0.00360 -0.0479 0.3897 1.0000
4.250 0.7115 0.01116 0.00396 -0.0475 0.3462 1.0000
4.500 0.7371 0.01166 0.00432 -0.0471 0.3063 1.0000
4.750 0.7626 0.01219 0.00472 -0.0468 0.2683 1.0000
5.000 0.7881 0.01273 0.00516 -0.0465 0.2330 1.0000
5.250 0.8135 0.01332 0.00564 -0.0462 0.1991 1.0000
5.500 0.8388 0.01396 0.00624 -0.0459 0.1682 1.0000
5.750 0.8637 0.01467 0.00687 -0.0455 0.1405 1.0000
6.000 0.8885 0.01544 0.00759 -0.0451 0.1161 1.0000
6.250 0.9124 0.01641 0.00847 -0.0446 0.0957 1.0000
6.500 0.9370 0.01722 0.00934 -0.0441 0.0772 1.0000
6.750 0.9607 0.01827 0.01041 -0.0435 0.0620 1.0000
7.000 0.9837 0.01948 0.01171 -0.0428 0.0492 1.0000
7.250 1.0065 0.02081 0.01313 -0.0420 0.0389 1.0000
7.500 1.0272 0.02291 0.01537 -0.0409 0.0323 1.0000
7.750 1.0494 0.02432 0.01689 -0.0401 0.0268 1.0000
8.000 1.0684 0.02712 0.01998 -0.0389 0.0231 1.0000
8.250 1.0885 0.02970 0.02293 -0.0377 0.0212 1.0000
8.500 1.1060 0.03281 0.02648 -0.0363 0.0200 1.0000
8.750 1.1199 0.03657 0.03073 -0.0349 0.0194 1.0000
9.000 1.1279 0.04132 0.03606 -0.0333 0.0194 1.0000
9.250 1.1273 0.04709 0.04246 -0.0317 0.0198 1.0000
9.500 1.1200 0.05296 0.04883 -0.0306 0.0201 1.0000
9.750 1.1058 0.05879 0.05506 -0.0301 0.0206 1.0000
10.000 1.0857 0.06391 0.06045 -0.0300 0.0210 1.0000
10.250 1.0636 0.06976 0.06649 -0.0329 0.0213 1.0000
10.500 1.0427 0.07752 0.07442 -0.0398 0.0216 1.0000
10.750 1.0213 0.08833 0.08534 -0.0498 0.0219 1.0000
11.000 0.9979 0.10122 0.09825 -0.0590 0.0225 1.0000
11.250 0.9791 0.11176 0.10875 -0.0645 0.0232 1.0000
11.500 0.9654 0.12008 0.11703 -0.0684 0.0239 1.0000
11.750 0.9396 0.13666 0.13352 -0.0765 0.0306 1.0000
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Polar data table (+)
Polar graphs
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