AG17 (ag17-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: AG17 (ag17-il) Reynolds number: 200,000 Max Cl/Cd: 64.09 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ag17-il-200000.txt Download as CSV file: xf-ag17-il-200000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.4488 0.12584 0.12243 0.0106 1.0000 0.0308
-10.500 -0.4467 0.12242 0.11903 0.0097 1.0000 0.0318
-8.250 -0.4507 0.08696 0.08380 -0.0073 1.0000 0.0372
-8.000 -0.4438 0.08203 0.07888 -0.0046 1.0000 0.0387
-7.750 -0.4379 0.07856 0.07542 -0.0043 1.0000 0.0400
-7.500 -0.4352 0.07482 0.07170 -0.0051 1.0000 0.0411
-7.250 -0.4343 0.07089 0.06781 -0.0065 1.0000 0.0425
-7.000 -0.4347 0.06674 0.06370 -0.0086 1.0000 0.0437
-6.750 -0.4324 0.06176 0.05875 -0.0130 1.0000 0.0454
-6.500 -0.4254 0.05499 0.05196 -0.0230 1.0000 0.0479
-6.250 -0.4107 0.04647 0.04307 -0.0372 1.0000 0.0493
-4.750 -0.3131 0.02593 0.02028 -0.0503 1.0000 0.0351
-4.500 -0.2858 0.02149 0.01525 -0.0506 1.0000 0.0311
-4.250 -0.2574 0.01839 0.01155 -0.0502 1.0000 0.0292
-4.000 -0.2302 0.01645 0.00932 -0.0497 1.0000 0.0296
-3.750 -0.2034 0.01499 0.00765 -0.0491 1.0000 0.0317
-3.500 -0.1767 0.01421 0.00673 -0.0485 1.0000 0.0366
-3.250 -0.1503 0.01269 0.00524 -0.0482 1.0000 0.0451
-3.000 -0.1231 0.01161 0.00418 -0.0480 1.0000 0.0658
-2.750 -0.0957 0.01045 0.00342 -0.0481 1.0000 0.1475
-2.500 -0.0691 0.00973 0.00318 -0.0483 1.0000 0.2652
-2.250 -0.0428 0.00928 0.00303 -0.0482 1.0000 0.3637
-2.000 -0.0167 0.00892 0.00294 -0.0480 1.0000 0.4505
-1.750 0.0092 0.00857 0.00288 -0.0477 1.0000 0.5361
-1.500 0.0343 0.00817 0.00284 -0.0471 1.0000 0.6371
-1.250 0.0541 0.00753 0.00279 -0.0448 1.0000 0.8064
-1.000 0.0791 0.00732 0.00269 -0.0440 1.0000 1.0000
-0.750 0.1057 0.00743 0.00269 -0.0441 1.0000 1.0000
-0.500 0.1400 0.00755 0.00270 -0.0458 0.9959 1.0000
-0.250 0.1886 0.00759 0.00263 -0.0502 0.9835 1.0000
0.000 0.2351 0.00758 0.00256 -0.0539 0.9699 1.0000
0.250 0.2766 0.00756 0.00249 -0.0565 0.9521 1.0000
0.500 0.3132 0.00753 0.00242 -0.0579 0.9301 1.0000
0.750 0.3443 0.00753 0.00236 -0.0579 0.9042 1.0000
1.000 0.3713 0.00757 0.00232 -0.0570 0.8755 1.0000
1.250 0.3964 0.00765 0.00230 -0.0557 0.8450 1.0000
1.500 0.4212 0.00776 0.00230 -0.0545 0.8120 1.0000
1.750 0.4462 0.00792 0.00234 -0.0533 0.7784 1.0000
2.000 0.4714 0.00810 0.00238 -0.0523 0.7432 1.0000
2.250 0.4967 0.00832 0.00245 -0.0513 0.7072 1.0000
2.500 0.5224 0.00855 0.00254 -0.0505 0.6690 1.0000
2.750 0.5481 0.00881 0.00268 -0.0498 0.6295 1.0000
3.000 0.5738 0.00910 0.00282 -0.0491 0.5884 1.0000
3.250 0.5996 0.00942 0.00298 -0.0485 0.5463 1.0000
3.500 0.6253 0.00977 0.00317 -0.0480 0.5035 1.0000
3.750 0.6510 0.01016 0.00339 -0.0475 0.4604 1.0000
4.000 0.6768 0.01056 0.00369 -0.0470 0.4176 1.0000
4.250 0.7025 0.01100 0.00398 -0.0466 0.3757 1.0000
4.500 0.7281 0.01147 0.00432 -0.0463 0.3357 1.0000
4.750 0.7538 0.01196 0.00469 -0.0459 0.2971 1.0000
5.000 0.7794 0.01247 0.00510 -0.0456 0.2597 1.0000
5.250 0.8048 0.01303 0.00559 -0.0453 0.2244 1.0000
5.500 0.8300 0.01364 0.00610 -0.0450 0.1898 1.0000
5.750 0.8550 0.01433 0.00669 -0.0446 0.1579 1.0000
6.000 0.8798 0.01507 0.00736 -0.0443 0.1268 1.0000
6.250 0.9040 0.01595 0.00816 -0.0438 0.1004 1.0000
6.500 0.9276 0.01698 0.00913 -0.0433 0.0781 1.0000
6.750 0.9512 0.01806 0.01026 -0.0426 0.0605 1.0000
7.000 0.9737 0.01936 0.01158 -0.0419 0.0471 1.0000
7.250 0.9962 0.02067 0.01297 -0.0411 0.0367 1.0000
7.500 1.0162 0.02293 0.01536 -0.0399 0.0308 1.0000
7.750 1.0386 0.02420 0.01674 -0.0391 0.0255 1.0000
8.000 1.0564 0.02732 0.02009 -0.0378 0.0222 1.0000
8.250 1.0769 0.02971 0.02285 -0.0366 0.0207 1.0000
8.500 1.0946 0.03280 0.02637 -0.0352 0.0197 1.0000
8.750 1.1086 0.03654 0.03060 -0.0337 0.0193 1.0000
9.000 1.1172 0.04104 0.03566 -0.0322 0.0193 1.0000
9.250 1.1190 0.04620 0.04143 -0.0306 0.0196 1.0000
9.500 1.1141 0.05165 0.04736 -0.0293 0.0201 1.0000
9.750 1.1031 0.05701 0.05310 -0.0284 0.0205 1.0000
10.000 1.0862 0.06182 0.05818 -0.0278 0.0208 1.0000
10.250 1.0662 0.06673 0.06329 -0.0290 0.0210 1.0000
10.500 1.0461 0.07299 0.06967 -0.0334 0.0212 1.0000
10.750 1.0262 0.08117 0.07800 -0.0408 0.0213 1.0000
11.000 1.0056 0.09158 0.08852 -0.0498 0.0215 1.0000
11.250 0.9837 0.10319 0.10017 -0.0579 0.0219 1.0000
11.500 0.9645 0.11325 0.11019 -0.0631 0.0226 1.0000
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Polar data table (+)
Polar graphs
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