AG17 (ag17-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: AG17 (ag17-il) Reynolds number: 1,000,000 Max Cl/Cd: 95.42 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ag17-il-1000000.txt Download as CSV file: xf-ag17-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.5563 0.09382 0.09229 0.0125 1.0000 0.0077
-8.000 -0.5529 0.08972 0.08819 0.0101 1.0000 0.0079
-7.750 -0.5495 0.08551 0.08400 0.0073 1.0000 0.0081
-7.500 -0.5447 0.08097 0.07949 0.0033 1.0000 0.0084
-7.250 -0.5334 0.07549 0.07401 -0.0031 1.0000 0.0087
-7.000 -0.5168 0.06983 0.06835 -0.0103 1.0000 0.0092
-6.750 -0.4959 0.06406 0.06256 -0.0180 1.0000 0.0095
-5.750 -0.4065 0.01880 0.01525 -0.0505 1.0000 0.0059
-5.500 -0.3803 0.01718 0.01338 -0.0505 1.0000 0.0057
-5.250 -0.3545 0.01292 0.00849 -0.0507 1.0000 0.0060
-5.000 -0.3284 0.01145 0.00686 -0.0505 1.0000 0.0068
-4.750 -0.3021 0.01090 0.00624 -0.0502 1.0000 0.0074
-4.500 -0.2758 0.01022 0.00548 -0.0498 1.0000 0.0079
-4.250 -0.2496 0.00953 0.00470 -0.0494 1.0000 0.0083
-4.000 -0.2234 0.00900 0.00410 -0.0490 1.0000 0.0088
-3.750 -0.1976 0.00873 0.00378 -0.0485 1.0000 0.0095
-3.500 -0.1691 0.00816 0.00313 -0.0486 0.9994 0.0098
-3.250 -0.1324 0.00728 0.00210 -0.0503 0.9962 0.0137
-3.000 -0.0960 0.00687 0.00169 -0.0520 0.9921 0.0245
-2.750 -0.0610 0.00650 0.00145 -0.0536 0.9849 0.0567
-2.500 -0.0268 0.00617 0.00127 -0.0550 0.9748 0.1003
-2.250 0.0056 0.00586 0.00112 -0.0560 0.9598 0.1528
-2.000 0.0341 0.00561 0.00101 -0.0560 0.9390 0.2099
-1.750 0.0600 0.00541 0.00092 -0.0553 0.9139 0.2676
-1.500 0.0859 0.00530 0.00085 -0.0547 0.8870 0.3141
-1.250 0.1121 0.00521 0.00079 -0.0542 0.8588 0.3637
-1.000 0.1388 0.00514 0.00075 -0.0538 0.8300 0.4135
-0.750 0.1657 0.00510 0.00072 -0.0534 0.8009 0.4588
-0.500 0.1928 0.00504 0.00070 -0.0532 0.7710 0.5166
-0.250 0.2199 0.00496 0.00070 -0.0529 0.7414 0.5812
0.000 0.2469 0.00486 0.00071 -0.0527 0.7120 0.6570
0.250 0.2729 0.00463 0.00074 -0.0522 0.6828 0.7752
0.750 0.3252 0.00440 0.00073 -0.0509 0.6217 1.0000
1.000 0.3529 0.00456 0.00075 -0.0508 0.5895 1.0000
1.250 0.3806 0.00473 0.00079 -0.0506 0.5572 1.0000
1.500 0.4083 0.00490 0.00083 -0.0506 0.5242 1.0000
1.750 0.4360 0.00510 0.00089 -0.0505 0.4908 1.0000
2.000 0.4637 0.00529 0.00095 -0.0504 0.4583 1.0000
2.250 0.4913 0.00550 0.00103 -0.0503 0.4246 1.0000
2.500 0.5188 0.00572 0.00112 -0.0502 0.3926 1.0000
2.750 0.5464 0.00594 0.00123 -0.0501 0.3609 1.0000
3.000 0.5738 0.00618 0.00135 -0.0501 0.3293 1.0000
3.250 0.6013 0.00641 0.00147 -0.0500 0.3014 1.0000
3.500 0.6287 0.00666 0.00161 -0.0499 0.2721 1.0000
3.750 0.6560 0.00691 0.00176 -0.0498 0.2458 1.0000
4.000 0.6832 0.00718 0.00194 -0.0497 0.2183 1.0000
4.250 0.7105 0.00745 0.00212 -0.0496 0.1943 1.0000
4.500 0.7376 0.00773 0.00232 -0.0495 0.1717 1.0000
4.750 0.7645 0.00806 0.00254 -0.0494 0.1465 1.0000
5.000 0.7914 0.00839 0.00279 -0.0493 0.1235 1.0000
5.250 0.8182 0.00871 0.00305 -0.0491 0.1039 1.0000
5.500 0.8449 0.00907 0.00333 -0.0490 0.0851 1.0000
5.750 0.8714 0.00946 0.00364 -0.0488 0.0672 1.0000
6.000 0.8978 0.00986 0.00397 -0.0486 0.0513 1.0000
6.250 0.9240 0.01029 0.00433 -0.0484 0.0381 1.0000
6.500 0.9502 0.01070 0.00473 -0.0482 0.0287 1.0000
6.750 0.9763 0.01114 0.00516 -0.0480 0.0210 1.0000
7.000 1.0020 0.01169 0.00571 -0.0477 0.0140 1.0000
7.250 1.0268 0.01250 0.00655 -0.0472 0.0085 1.0000
7.500 1.0527 0.01291 0.00700 -0.0469 0.0070 1.0000
7.750 1.0770 0.01376 0.00792 -0.0464 0.0052 1.0000
8.000 1.1006 0.01477 0.00909 -0.0457 0.0047 1.0000
8.250 1.1250 0.01547 0.00992 -0.0453 0.0045 1.0000
8.500 1.1488 0.01628 0.01084 -0.0447 0.0042 1.0000
8.750 1.1721 0.01715 0.01183 -0.0441 0.0040 1.0000
9.000 1.1951 0.01805 0.01284 -0.0435 0.0037 1.0000
9.250 1.2178 0.01892 0.01381 -0.0430 0.0034 1.0000
9.500 1.2399 0.01986 0.01485 -0.0424 0.0032 1.0000
9.750 1.2564 0.02187 0.01706 -0.0412 0.0028 1.0000
10.000 1.2597 0.02640 0.02211 -0.0387 0.0025 1.0000
10.250 1.2764 0.02801 0.02392 -0.0377 0.0025 1.0000
10.500 1.2884 0.03027 0.02643 -0.0363 0.0024 1.0000
10.750 1.2954 0.03306 0.02950 -0.0347 0.0024 1.0000
11.000 1.2965 0.03629 0.03305 -0.0329 0.0024 1.0000
11.250 1.2906 0.03978 0.03682 -0.0309 0.0024 1.0000
11.500 1.2752 0.04334 0.04061 -0.0288 0.0024 1.0000
11.750 1.2578 0.04806 0.04554 -0.0296 0.0024 1.0000
12.000 1.2404 0.05442 0.05212 -0.0338 0.0024 1.0000
12.250 1.2220 0.06277 0.06066 -0.0406 0.0024 1.0000
12.500 1.2018 0.07262 0.07065 -0.0483 0.0025 1.0000
12.750 1.1780 0.08341 0.08158 -0.0556 0.0025 1.0000
13.000 1.1530 0.09421 0.09249 -0.0619 0.0025 1.0000
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Polar data table (+)
Polar graphs
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