AH 82-150 A (ah82150a-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: AH 82-150 A (ah82150a-il) Reynolds number: 100,000 Max Cl/Cd: 42.5 at α=9.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ah82150a-il-100000.txt Download as CSV file: xf-ah82150a-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: AH 82-150 A
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.2600 0.10319 0.09914 -0.0698 0.9649 0.1237
-9.750 -0.2287 0.09926 0.09516 -0.0687 0.9621 0.1312
-9.500 -0.2453 0.09482 0.09077 -0.0734 0.9592 0.1377
-9.250 -0.2242 0.09011 0.08603 -0.0745 0.9574 0.1435
-9.000 -0.3369 0.09551 0.09130 -0.0688 0.9703 0.1305
-8.750 -0.3503 0.09197 0.08781 -0.0721 0.9632 0.1363
-8.500 -0.3863 0.08680 0.08267 -0.0801 0.9556 0.1379
-8.250 -0.3544 0.08423 0.08010 -0.0772 0.9532 0.1492
-8.000 -0.3845 0.08107 0.07697 -0.0789 0.9455 0.1504
-7.750 -0.4233 0.07874 0.07457 -0.0782 0.9364 0.1520
-7.500 -0.4057 0.07567 0.07154 -0.0771 0.9333 0.1620
-7.250 -0.4438 0.07352 0.06915 -0.0774 0.9261 0.1673
-6.000 -0.4501 0.04801 0.04110 -0.0703 0.9044 0.0829
-5.750 -0.4259 0.04490 0.03766 -0.0704 0.9018 0.0792
-5.500 -0.3957 0.04250 0.03460 -0.0714 0.8995 0.0807
-5.250 -0.3885 0.04104 0.03280 -0.0684 0.8954 0.0810
-5.000 -0.3692 0.03929 0.03066 -0.0672 0.8919 0.0813
-4.750 -0.3442 0.03699 0.02818 -0.0675 0.8893 0.0843
-4.500 -0.3131 0.03589 0.02696 -0.0685 0.8866 0.0899
-4.250 -0.2823 0.03488 0.02565 -0.0689 0.8836 0.0937
-4.000 -0.2718 0.03427 0.02489 -0.0662 0.8795 0.0968
-3.750 -0.2514 0.03360 0.02430 -0.0655 0.8764 0.1043
-3.500 -0.2219 0.03294 0.02354 -0.0658 0.8731 0.1111
-3.250 -0.1854 0.03228 0.02296 -0.0674 0.8703 0.1237
-3.000 -0.1823 0.03209 0.02292 -0.0640 0.8660 0.1333
-2.750 -0.1647 0.03173 0.02263 -0.0628 0.8620 0.1530
-2.500 -0.1401 0.02979 0.02205 -0.0635 0.8587 0.3416
-2.250 -0.1430 0.03096 0.02476 -0.0533 0.8556 0.7638
-2.000 -0.1542 0.03174 0.02551 -0.0458 0.8505 0.7909
-1.750 -0.1522 0.03248 0.02618 -0.0396 0.8462 0.8195
-1.500 -0.1450 0.03312 0.02674 -0.0337 0.8425 0.8493
-1.250 -0.1482 0.03351 0.02705 -0.0273 0.8378 0.8735
-1.000 0.1383 0.03581 0.02869 -0.0669 0.8374 0.9777
-0.750 0.1641 0.03607 0.02883 -0.0681 0.8319 0.9839
-0.500 0.2137 0.03606 0.02867 -0.0731 0.8283 0.9870
-0.250 0.2302 0.03649 0.02904 -0.0728 0.8220 0.9912
0.000 0.2544 0.03678 0.02925 -0.0736 0.8163 0.9944
0.250 0.3019 0.03677 0.02913 -0.0779 0.8128 0.9962
0.500 0.3030 0.03748 0.02982 -0.0753 0.8044 0.9998
0.750 0.3317 0.03760 0.02988 -0.0761 0.7994 1.0000
1.000 0.3222 0.03826 0.03053 -0.0711 0.7910 1.0000
1.250 0.3452 0.03842 0.03064 -0.0709 0.7853 1.0000
1.500 0.3403 0.03900 0.03122 -0.0666 0.7769 1.0000
1.750 0.3613 0.03917 0.03135 -0.0661 0.7708 1.0000
2.000 0.3568 0.03970 0.03188 -0.0618 0.7620 1.0000
2.250 0.3803 0.03981 0.03197 -0.0615 0.7561 1.0000
2.500 0.3717 0.04036 0.03252 -0.0567 0.7466 1.0000
2.750 0.3987 0.04041 0.03254 -0.0568 0.7412 1.0000
3.000 0.3858 0.04095 0.03309 -0.0514 0.7309 1.0000
3.250 0.4192 0.04086 0.03299 -0.0522 0.7261 1.0000
3.500 0.4022 0.04136 0.03350 -0.0463 0.7150 1.0000
3.750 0.4393 0.04121 0.03335 -0.0475 0.7111 1.0000
4.000 0.4236 0.04171 0.03386 -0.0420 0.6994 1.0000
4.250 0.4625 0.04158 0.03374 -0.0434 0.6955 1.0000
4.500 0.4647 0.04223 0.03441 -0.0410 0.6842 1.0000
4.750 0.4772 0.04298 0.03519 -0.0401 0.6741 1.0000
5.000 0.5165 0.04286 0.03512 -0.0418 0.6693 1.0000
5.250 0.5299 0.04375 0.03604 -0.0413 0.6584 1.0000
5.500 0.5727 0.04346 0.03584 -0.0433 0.6545 1.0000
5.750 0.5858 0.04446 0.03689 -0.0429 0.6430 1.0000
6.000 0.6310 0.04396 0.03648 -0.0449 0.6398 1.0000
6.250 0.6438 0.04505 0.03763 -0.0445 0.6279 1.0000
6.500 0.6913 0.04428 0.03700 -0.0465 0.6252 1.0000
6.750 0.7036 0.04541 0.03821 -0.0461 0.6129 1.0000
7.000 0.7508 0.04447 0.03741 -0.0479 0.6101 1.0000
7.250 0.7654 0.04547 0.03853 -0.0475 0.5982 1.0000
7.500 0.7805 0.04650 0.03966 -0.0472 0.5865 1.0000
7.750 0.8288 0.04514 0.03848 -0.0488 0.5835 1.0000
8.250 0.8704 0.04623 0.03987 -0.0485 0.5627 1.0000
8.500 0.9554 0.04112 0.03510 -0.0512 0.5679 1.0000
8.750 1.0919 0.02763 0.02199 -0.0537 0.5530 1.0000
9.000 1.1039 0.02673 0.02113 -0.0507 0.5207 1.0000
9.250 1.1173 0.02629 0.02060 -0.0481 0.4771 1.0000
9.500 1.1226 0.02685 0.02090 -0.0450 0.4200 1.0000
9.750 1.1089 0.02894 0.02242 -0.0407 0.3355 1.0000
10.000 1.0848 0.03232 0.02507 -0.0365 0.2338 1.0000
10.250 1.0585 0.03645 0.02831 -0.0330 0.1310 1.0000
10.500 1.0419 0.04023 0.03152 -0.0304 0.0819 1.0000
10.750 1.0364 0.04325 0.03443 -0.0287 0.0670 1.0000
11.000 1.0347 0.04600 0.03720 -0.0273 0.0608 1.0000
11.250 1.0371 0.04842 0.03974 -0.0262 0.0564 1.0000
11.500 1.0378 0.05101 0.04232 -0.0250 0.0530 1.0000
11.750 1.0473 0.05285 0.04419 -0.0237 0.0504 1.0000
12.000 1.0631 0.05426 0.04567 -0.0228 0.0470 1.0000
12.250 1.0815 0.05559 0.04695 -0.0220 0.0437 1.0000
12.500 1.1445 0.05580 0.04699 -0.0217 0.0409 1.0000
12.750 1.1893 0.05762 0.04908 -0.0218 0.0402 1.0000
13.000 1.2272 0.06057 0.05234 -0.0221 0.0401 1.0000
13.250 1.2429 0.06387 0.05597 -0.0214 0.0400 1.0000
13.500 1.2474 0.06729 0.05973 -0.0204 0.0398 1.0000
13.750 1.2447 0.07078 0.06354 -0.0193 0.0395 1.0000
14.000 1.2405 0.07468 0.06774 -0.0183 0.0396 1.0000
14.250 1.2304 0.07871 0.07207 -0.0174 0.0396 1.0000
14.500 1.2200 0.08318 0.07682 -0.0169 0.0398 1.0000
14.750 1.2073 0.08792 0.08182 -0.0167 0.0401 1.0000
15.000 1.1959 0.09327 0.08739 -0.0170 0.0406 1.0000
15.250 1.1972 0.09863 0.09295 -0.0174 0.0416 1.0000
15.500 1.1755 0.10250 0.09709 -0.0180 0.0421 1.0000
15.750 1.1445 0.10819 0.10310 -0.0200 0.0428 1.0000
16.000 1.1041 0.11619 0.11143 -0.0240 0.0434 1.0000
16.250 1.0533 0.12791 0.12349 -0.0312 0.0449 1.0000
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