AG17 (ag17-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: AG17 (ag17-il) Reynolds number: 200,000 Max Cl/Cd: 60.36 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ag17-il-200000-n5.txt Download as CSV file: xf-ag17-il-200000-n5.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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.4448 0.10014 0.09678 0.0040 1.0000 0.0136
-9.000 -0.4444 0.09580 0.09246 0.0028 1.0000 0.0129
-8.750 -0.5515 0.10356 0.10009 0.0134 1.0000 0.0142
-8.250 -0.5456 0.09518 0.09173 0.0094 1.0000 0.0124
-8.000 -0.5441 0.09042 0.08704 0.0067 1.0000 0.0116
-7.750 -0.5477 0.08304 0.07974 0.0013 1.0000 0.0103
-7.500 -0.5396 0.07758 0.07432 -0.0038 1.0000 0.0099
-7.000 -0.5159 0.06602 0.06274 -0.0169 1.0000 0.0095
-6.750 -0.4995 0.05809 0.05475 -0.0262 1.0000 0.0094
-6.500 -0.4792 0.04837 0.04482 -0.0358 1.0000 0.0093
-6.250 -0.4583 0.03874 0.03474 -0.0429 1.0000 0.0092
-6.000 -0.4352 0.03165 0.02698 -0.0469 1.0000 0.0093
-5.750 -0.4111 0.02659 0.02123 -0.0490 1.0000 0.0103
-5.500 -0.3866 0.02527 0.01972 -0.0496 1.0000 0.0116
-5.250 -0.3606 0.02280 0.01682 -0.0499 1.0000 0.0124
-5.000 -0.3339 0.02013 0.01365 -0.0500 1.0000 0.0126
-4.750 -0.3072 0.01811 0.01127 -0.0498 1.0000 0.0130
-4.500 -0.2806 0.01651 0.00939 -0.0495 1.0000 0.0136
-4.250 -0.2541 0.01520 0.00789 -0.0491 1.0000 0.0145
-4.000 -0.2276 0.01417 0.00671 -0.0488 1.0000 0.0156
-3.750 -0.2013 0.01311 0.00553 -0.0486 1.0000 0.0187
-3.500 -0.1749 0.01255 0.00492 -0.0483 1.0000 0.0235
-3.250 -0.1481 0.01181 0.00409 -0.0480 1.0000 0.0302
-3.000 -0.1216 0.01128 0.00358 -0.0478 1.0000 0.0493
-2.750 -0.0952 0.01074 0.00322 -0.0476 1.0000 0.0880
-2.500 -0.0689 0.01027 0.00297 -0.0476 1.0000 0.1431
-2.250 -0.0426 0.00987 0.00277 -0.0476 1.0000 0.2077
-2.000 -0.0076 0.00950 0.00263 -0.0493 0.9935 0.2820
-1.750 0.0294 0.00919 0.00251 -0.0514 0.9824 0.3509
-1.500 0.0655 0.00889 0.00241 -0.0532 0.9692 0.4202
-1.250 0.1005 0.00861 0.00231 -0.0546 0.9535 0.4902
-1.000 0.1337 0.00832 0.00223 -0.0555 0.9344 0.5629
-0.750 0.1646 0.00799 0.00216 -0.0558 0.9129 0.6487
-0.500 0.1894 0.00757 0.00208 -0.0544 0.8879 0.7705
-0.250 0.2212 0.00720 0.00192 -0.0541 0.8607 1.0000
0.000 0.2483 0.00728 0.00184 -0.0535 0.8312 1.0000
0.250 0.2747 0.00739 0.00178 -0.0528 0.8006 1.0000
0.500 0.3009 0.00752 0.00175 -0.0521 0.7692 1.0000
0.750 0.3272 0.00768 0.00173 -0.0514 0.7377 1.0000
1.000 0.3535 0.00786 0.00173 -0.0508 0.7060 1.0000
1.250 0.3800 0.00804 0.00175 -0.0503 0.6731 1.0000
1.500 0.4064 0.00825 0.00179 -0.0498 0.6397 1.0000
1.750 0.4330 0.00847 0.00187 -0.0493 0.6053 1.0000
2.000 0.4595 0.00871 0.00194 -0.0489 0.5704 1.0000
2.250 0.4861 0.00896 0.00204 -0.0485 0.5347 1.0000
2.500 0.5126 0.00923 0.00217 -0.0482 0.4993 1.0000
2.750 0.5391 0.00952 0.00234 -0.0479 0.4635 1.0000
3.000 0.5657 0.00983 0.00252 -0.0476 0.4284 1.0000
3.250 0.5922 0.01015 0.00271 -0.0473 0.3940 1.0000
3.500 0.6187 0.01048 0.00293 -0.0471 0.3603 1.0000
3.750 0.6451 0.01084 0.00317 -0.0468 0.3273 1.0000
4.250 0.6979 0.01160 0.00378 -0.0464 0.2653 1.0000
4.500 0.7241 0.01200 0.00411 -0.0462 0.2362 1.0000
4.750 0.7503 0.01243 0.00447 -0.0460 0.2085 1.0000
5.000 0.7763 0.01288 0.00486 -0.0458 0.1816 1.0000
5.250 0.8022 0.01336 0.00533 -0.0455 0.1564 1.0000
5.500 0.8279 0.01389 0.00580 -0.0453 0.1319 1.0000
5.750 0.8535 0.01443 0.00632 -0.0450 0.1104 1.0000
6.000 0.8788 0.01503 0.00688 -0.0447 0.0894 1.0000
6.250 0.9039 0.01568 0.00751 -0.0444 0.0717 1.0000
6.500 0.9285 0.01642 0.00826 -0.0441 0.0558 1.0000
6.750 0.9530 0.01720 0.00907 -0.0437 0.0439 1.0000
7.000 0.9769 0.01807 0.00996 -0.0432 0.0330 1.0000
7.250 1.0010 0.01890 0.01092 -0.0427 0.0257 1.0000
7.500 1.0240 0.01995 0.01207 -0.0421 0.0199 1.0000
7.750 1.0464 0.02112 0.01336 -0.0414 0.0162 1.0000
8.000 1.0671 0.02258 0.01499 -0.0406 0.0133 1.0000
8.250 1.0893 0.02365 0.01623 -0.0400 0.0111 1.0000
8.500 1.1095 0.02508 0.01789 -0.0392 0.0098 1.0000
8.750 1.1261 0.02720 0.02021 -0.0381 0.0089 1.0000
9.000 1.1412 0.02969 0.02297 -0.0368 0.0084 1.0000
9.250 1.1570 0.03194 0.02554 -0.0356 0.0080 1.0000
9.500 1.1702 0.03458 0.02853 -0.0343 0.0077 1.0000
9.750 1.1800 0.03761 0.03195 -0.0329 0.0075 1.0000
10.000 1.1856 0.04100 0.03574 -0.0314 0.0073 1.0000
10.250 1.1865 0.04456 0.03970 -0.0300 0.0071 1.0000
10.500 1.1828 0.04814 0.04361 -0.0288 0.0069 1.0000
10.750 1.1719 0.05170 0.04745 -0.0275 0.0067 1.0000
11.000 1.1570 0.05621 0.05222 -0.0282 0.0067 1.0000
11.250 1.1410 0.06193 0.05819 -0.0315 0.0067 1.0000
11.500 1.1208 0.06992 0.06642 -0.0376 0.0069 1.0000
11.750 1.0998 0.07954 0.07623 -0.0454 0.0071 1.0000
12.000 1.0772 0.09037 0.08721 -0.0533 0.0073 1.0000
12.250 1.0540 0.10158 0.09851 -0.0604 0.0075 1.0000
12.500 1.0295 0.11312 0.11010 -0.0668 0.0078 1.0000
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Polar data table (+)
Polar graphs
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