AH21 9% version (Andrew Hollom) (ah21-9-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: AH21 9% version (Andrew Hollom) (ah21-9-il) Reynolds number: 50,000 Max Cl/Cd: 34.53 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ah21-9-il-50000-n5.txt Download as CSV file: xf-ah21-9-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: AH21 9% version (Andrew Hollom)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.5000 0.09869 0.09148 -0.0266 1.0000 0.0625
-8.500 -0.5011 0.09478 0.08765 -0.0272 1.0000 0.0584
-8.250 -0.5185 0.08992 0.08298 -0.0321 1.0000 0.0518
-8.000 -0.5174 0.08642 0.07953 -0.0314 1.0000 0.0506
-7.750 -0.5193 0.08239 0.07557 -0.0328 1.0000 0.0499
-7.500 -0.5216 0.07825 0.07145 -0.0343 1.0000 0.0495
-7.250 -0.5228 0.07410 0.06730 -0.0355 1.0000 0.0491
-7.000 -0.5232 0.06980 0.06295 -0.0368 1.0000 0.0492
-6.750 -0.5216 0.06553 0.05858 -0.0377 1.0000 0.0492
-6.500 -0.5176 0.06125 0.05407 -0.0385 1.0000 0.0493
-6.250 -0.5110 0.05701 0.04961 -0.0389 1.0000 0.0493
-6.000 -0.5018 0.05283 0.04515 -0.0391 1.0000 0.0488
-5.750 -0.4898 0.04871 0.04069 -0.0391 1.0000 0.0481
-5.500 -0.4751 0.04477 0.03634 -0.0389 1.0000 0.0476
-5.250 -0.4579 0.04111 0.03219 -0.0386 1.0000 0.0474
-5.000 -0.4384 0.03778 0.02835 -0.0381 1.0000 0.0476
-4.750 -0.4171 0.03482 0.02486 -0.0374 1.0000 0.0482
-4.500 -0.3942 0.03248 0.02189 -0.0367 1.0000 0.0514
-4.250 -0.3718 0.03026 0.01935 -0.0360 1.0000 0.0549
-4.000 -0.3483 0.02835 0.01714 -0.0351 1.0000 0.0567
-3.750 -0.3243 0.02667 0.01519 -0.0341 1.0000 0.0586
-3.500 -0.3005 0.02525 0.01346 -0.0329 1.0000 0.0611
-3.250 -0.2768 0.02405 0.01200 -0.0316 1.0000 0.0642
-3.000 -0.2534 0.02294 0.01076 -0.0306 1.0000 0.0684
-2.750 -0.2299 0.02210 0.00975 -0.0297 1.0000 0.0793
-2.500 -0.2059 0.02112 0.00883 -0.0292 1.0000 0.0993
-2.250 -0.1807 0.01961 0.00781 -0.0292 1.0000 0.1777
-2.000 -0.1722 0.01703 0.00782 -0.0247 1.0000 0.6967
-1.750 -0.1301 0.01650 0.00737 -0.0256 1.0000 1.0000
-1.500 -0.1086 0.01651 0.00700 -0.0248 1.0000 1.0000
-1.250 -0.0868 0.01655 0.00671 -0.0240 1.0000 1.0000
-1.000 -0.0649 0.01662 0.00650 -0.0233 1.0000 1.0000
-0.750 -0.0428 0.01671 0.00632 -0.0226 1.0000 1.0000
-0.500 -0.0206 0.01683 0.00623 -0.0219 1.0000 1.0000
-0.250 0.0016 0.01697 0.00619 -0.0212 1.0000 1.0000
0.000 0.0237 0.01713 0.00621 -0.0206 1.0000 1.0000
0.250 0.0457 0.01732 0.00625 -0.0200 1.0000 1.0000
0.500 0.0676 0.01753 0.00637 -0.0194 1.0000 1.0000
0.750 0.0894 0.01777 0.00653 -0.0188 1.0000 1.0000
1.000 0.1110 0.01804 0.00674 -0.0182 1.0000 1.0000
1.250 0.1324 0.01833 0.00700 -0.0176 1.0000 1.0000
1.500 0.1536 0.01866 0.00732 -0.0171 1.0000 1.0000
1.750 0.1745 0.01901 0.00768 -0.0165 1.0000 1.0000
2.000 0.2158 0.01961 0.00834 -0.0201 0.9891 1.0000
2.250 0.2579 0.02018 0.00902 -0.0236 0.9774 1.0000
2.500 0.3002 0.02067 0.00965 -0.0271 0.9643 1.0000
2.750 0.3431 0.02106 0.01020 -0.0304 0.9491 1.0000
3.000 0.3884 0.02130 0.01070 -0.0340 0.9317 1.0000
3.250 0.4317 0.02132 0.01097 -0.0367 0.9098 1.0000
3.500 0.4774 0.02106 0.01102 -0.0393 0.8832 1.0000
3.750 0.5246 0.02040 0.01077 -0.0414 0.8492 1.0000
4.000 0.5625 0.01962 0.01031 -0.0411 0.8018 1.0000
4.250 0.6067 0.01877 0.00969 -0.0413 0.7160 1.0000
4.500 0.6572 0.01903 0.00901 -0.0418 0.4659 1.0000
4.750 0.6684 0.02085 0.00973 -0.0388 0.2933 1.0000
5.000 0.6843 0.02264 0.01086 -0.0372 0.1956 1.0000
5.250 0.7043 0.02427 0.01212 -0.0363 0.1440 1.0000
5.500 0.7274 0.02579 0.01357 -0.0355 0.1180 1.0000
5.750 0.7524 0.02720 0.01503 -0.0351 0.0972 1.0000
6.000 0.7798 0.02891 0.01682 -0.0348 0.0864 1.0000
6.250 0.8056 0.03060 0.01860 -0.0345 0.0760 1.0000
6.500 0.8328 0.03236 0.02072 -0.0340 0.0677 1.0000
6.750 0.8594 0.03479 0.02318 -0.0339 0.0635 1.0000
7.000 0.8853 0.03754 0.02651 -0.0330 0.0606 1.0000
7.250 0.9059 0.04018 0.02965 -0.0318 0.0565 1.0000
7.500 0.9234 0.04229 0.03188 -0.0308 0.0518 1.0000
7.750 0.9381 0.04571 0.03579 -0.0291 0.0498 1.0000
8.000 0.9485 0.04953 0.04026 -0.0269 0.0488 1.0000
8.250 0.9544 0.05360 0.04489 -0.0246 0.0480 1.0000
8.500 0.9561 0.05781 0.04960 -0.0223 0.0476 1.0000
8.750 0.9538 0.06215 0.05437 -0.0201 0.0473 1.0000
9.000 0.9472 0.06654 0.05911 -0.0180 0.0471 1.0000
9.250 0.9368 0.07089 0.06374 -0.0163 0.0469 1.0000
9.500 0.9213 0.07515 0.06821 -0.0147 0.0469 1.0000
9.750 0.9032 0.07946 0.07266 -0.0136 0.0471 1.0000
10.000 0.8845 0.08433 0.07762 -0.0142 0.0475 1.0000
10.250 0.8669 0.08995 0.08330 -0.0165 0.0480 1.0000
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Polar data table (+)
Polar graphs
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