AH 94-156 (ah94156-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: AH 94-156 (ah94156-il) Reynolds number: 500,000 Max Cl/Cd: 103.2 at α=7.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ah94156-il-500000.txt Download as CSV file: xf-ah94156-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: AH 94-156
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.1628 0.08889 0.08598 -0.0796 0.8001 0.0245
-11.000 -0.1600 0.08532 0.08241 -0.0810 0.7983 0.0250
-10.750 -0.1592 0.08136 0.07845 -0.0825 0.7965 0.0256
-10.500 -0.1620 0.07667 0.07375 -0.0845 0.7949 0.0258
-10.250 -0.1677 0.07140 0.06849 -0.0869 0.7934 0.0269
-10.000 -0.1776 0.06528 0.06237 -0.0899 0.7920 0.0274
-9.750 -0.1941 0.05771 0.05482 -0.0945 0.7906 0.0274
-9.500 -0.2307 0.04796 0.04503 -0.1019 0.7889 0.0266
-9.250 -0.2608 0.04265 0.03962 -0.1031 0.7865 0.0262
-9.000 -0.2854 0.03890 0.03576 -0.1017 0.7837 0.0262
-8.750 -0.3070 0.03606 0.03279 -0.0985 0.7809 0.0268
-8.500 -0.4150 0.03313 0.02835 -0.0907 0.7819 0.0182
-8.250 -0.4113 0.02982 0.02471 -0.0883 0.7797 0.0180
-8.000 -0.4020 0.02705 0.02158 -0.0861 0.7776 0.0178
-7.750 -0.3877 0.02486 0.01903 -0.0844 0.7756 0.0179
-7.500 -0.3687 0.02336 0.01728 -0.0833 0.7736 0.0182
-7.250 -0.3495 0.02146 0.01508 -0.0822 0.7715 0.0188
-7.000 -0.3267 0.01992 0.01344 -0.0818 0.7695 0.0193
-6.750 -0.3025 0.01894 0.01237 -0.0814 0.7674 0.0198
-6.500 -0.2778 0.01812 0.01144 -0.0811 0.7653 0.0204
-6.250 -0.2527 0.01731 0.01053 -0.0808 0.7635 0.0209
-6.000 -0.2275 0.01668 0.00981 -0.0805 0.7619 0.0219
-5.750 -0.2024 0.01610 0.00915 -0.0801 0.7602 0.0227
-5.500 -0.1780 0.01548 0.00847 -0.0797 0.7581 0.0237
-5.250 -0.1554 0.01475 0.00776 -0.0791 0.7558 0.0253
-5.000 -0.1307 0.01435 0.00735 -0.0788 0.7536 0.0269
-4.750 -0.1060 0.01395 0.00691 -0.0784 0.7516 0.0285
-4.500 -0.0824 0.01343 0.00633 -0.0778 0.7496 0.0305
-4.250 -0.0577 0.01304 0.00592 -0.0774 0.7478 0.0338
-4.000 -0.0320 0.01278 0.00561 -0.0772 0.7461 0.0380
-3.750 -0.0074 0.01246 0.00532 -0.0768 0.7441 0.0452
-3.500 0.0170 0.01209 0.00501 -0.0764 0.7417 0.0602
-3.250 0.0399 0.01159 0.00478 -0.0759 0.7394 0.1154
-3.000 0.0615 0.01096 0.00458 -0.0753 0.7372 0.2227
-2.750 0.0815 0.01022 0.00438 -0.0744 0.7351 0.3686
-2.500 0.0991 0.00932 0.00415 -0.0731 0.7330 0.5523
-2.250 0.1151 0.00875 0.00435 -0.0705 0.7311 0.7412
-2.000 0.1402 0.00922 0.00491 -0.0693 0.7289 0.8018
-1.750 0.1669 0.00952 0.00517 -0.0689 0.7263 0.8235
-1.500 0.1931 0.00985 0.00547 -0.0682 0.7237 0.8355
-1.250 0.2187 0.01019 0.00578 -0.0673 0.7211 0.8474
-1.000 0.2450 0.01046 0.00598 -0.0666 0.7188 0.8584
-0.750 0.2707 0.01066 0.00614 -0.0655 0.7166 0.8636
-0.500 0.2968 0.01087 0.00629 -0.0650 0.7141 0.8717
-0.250 0.3196 0.01099 0.00644 -0.0635 0.7109 0.8777
0.000 0.3442 0.01112 0.00655 -0.0626 0.7079 0.8855
0.250 0.3691 0.01112 0.00652 -0.0617 0.7052 0.8908
0.500 0.3955 0.01114 0.00649 -0.0612 0.7027 0.8962
0.750 0.4223 0.01118 0.00645 -0.0611 0.7004 0.9021
1.000 0.4461 0.01111 0.00642 -0.0601 0.6971 0.9056
1.250 0.4711 0.01108 0.00639 -0.0596 0.6937 0.9097
1.500 0.4970 0.01105 0.00633 -0.0594 0.6905 0.9141
1.750 0.5235 0.01092 0.00617 -0.0593 0.6878 0.9170
2.000 0.5521 0.01086 0.00606 -0.0595 0.6852 0.9191
2.250 0.5759 0.01080 0.00605 -0.0589 0.6813 0.9217
2.500 0.6015 0.01074 0.00599 -0.0587 0.6776 0.9242
2.750 0.6283 0.01065 0.00589 -0.0587 0.6741 0.9265
3.000 0.6566 0.01062 0.00580 -0.0591 0.6709 0.9284
3.250 0.6800 0.01051 0.00575 -0.0586 0.6664 0.9301
3.500 0.7055 0.01040 0.00566 -0.0583 0.6619 0.9316
3.750 0.7331 0.01030 0.00554 -0.0585 0.6580 0.9329
4.000 0.7593 0.01025 0.00550 -0.0584 0.6536 0.9343
4.250 0.7837 0.01018 0.00548 -0.0580 0.6478 0.9358
4.500 0.8108 0.01010 0.00538 -0.0582 0.6428 0.9368
4.750 0.8355 0.01007 0.00538 -0.0579 0.6370 0.9383
5.000 0.8607 0.01002 0.00536 -0.0578 0.6305 0.9393
5.250 0.8867 0.00999 0.00533 -0.0577 0.6239 0.9402
5.500 0.9109 0.00998 0.00535 -0.0574 0.6159 0.9413
5.750 0.9364 0.00999 0.00537 -0.0573 0.6085 0.9420
6.000 0.9607 0.00999 0.00540 -0.0570 0.5994 0.9426
6.250 0.9832 0.00999 0.00543 -0.0564 0.5894 0.9435
6.500 1.0050 0.01001 0.00545 -0.0555 0.5790 0.9447
6.750 1.0265 0.01008 0.00552 -0.0547 0.5677 0.9455
7.000 1.0464 0.01018 0.00564 -0.0536 0.5548 0.9463
7.250 1.0650 0.01032 0.00578 -0.0523 0.5412 0.9473
7.500 1.0793 0.01050 0.00593 -0.0501 0.5257 0.9488
7.750 1.0885 0.01074 0.00613 -0.0470 0.5081 0.9504
8.000 1.0978 0.01111 0.00646 -0.0442 0.4888 0.9518
8.250 1.1063 0.01157 0.00687 -0.0414 0.4698 0.9532
8.500 1.1137 0.01214 0.00739 -0.0386 0.4510 0.9547
8.750 1.1208 0.01279 0.00798 -0.0359 0.4326 0.9567
9.000 1.1303 0.01346 0.00863 -0.0338 0.4147 0.9583
9.250 1.1382 0.01427 0.00940 -0.0317 0.3947 0.9602
9.500 1.1448 0.01524 0.01029 -0.0295 0.3737 0.9624
9.750 1.1542 0.01618 0.01119 -0.0279 0.3531 0.9645
10.000 1.1626 0.01733 0.01227 -0.0265 0.3298 0.9670
10.250 1.1734 0.01855 0.01342 -0.0257 0.3047 0.9696
10.500 1.1836 0.01997 0.01475 -0.0252 0.2771 0.9736
10.750 1.1943 0.02149 0.01615 -0.0249 0.2491 0.9788
11.000 1.1984 0.02303 0.01757 -0.0234 0.2225 1.0000
11.250 1.2013 0.02461 0.01902 -0.0217 0.1966 1.0000
11.500 1.2041 0.02626 0.02055 -0.0200 0.1700 1.0000
11.750 1.2043 0.02816 0.02227 -0.0183 0.1409 1.0000
12.000 1.2072 0.02994 0.02393 -0.0169 0.1167 1.0000
12.250 1.2079 0.03195 0.02581 -0.0154 0.0922 1.0000
12.500 1.2096 0.03395 0.02770 -0.0141 0.0727 1.0000
12.750 1.2121 0.03596 0.02963 -0.0129 0.0568 1.0000
13.000 1.2137 0.03812 0.03171 -0.0119 0.0437 1.0000
13.250 1.2164 0.04024 0.03379 -0.0109 0.0340 1.0000
13.500 1.2176 0.04258 0.03612 -0.0100 0.0275 1.0000
13.750 1.2244 0.04447 0.03806 -0.0096 0.0242 1.0000
14.000 1.2249 0.04701 0.04062 -0.0088 0.0212 1.0000
14.250 1.2309 0.04909 0.04280 -0.0085 0.0195 1.0000
14.500 1.2336 0.05155 0.04530 -0.0081 0.0179 1.0000
14.750 1.2305 0.05469 0.04852 -0.0076 0.0166 1.0000
15.000 1.2354 0.05704 0.05097 -0.0075 0.0158 1.0000
15.250 1.2386 0.05964 0.05364 -0.0075 0.0149 1.0000
15.500 1.2405 0.06243 0.05652 -0.0076 0.0144 1.0000
15.750 1.2422 0.06531 0.05945 -0.0078 0.0137 1.0000
16.000 1.2340 0.06943 0.06366 -0.0079 0.0131 1.0000
16.250 1.2333 0.07273 0.06705 -0.0083 0.0126 1.0000
16.500 1.2363 0.07566 0.07009 -0.0088 0.0121 1.0000
16.750 1.2372 0.07887 0.07341 -0.0094 0.0120 1.0000
17.000 1.2376 0.08224 0.07686 -0.0101 0.0115 1.0000
17.250 1.2374 0.08569 0.08040 -0.0108 0.0112 1.0000
17.500 1.2373 0.08920 0.08398 -0.0117 0.0108 1.0000
17.750 1.2364 0.09284 0.08770 -0.0128 0.0105 1.0000
18.000 1.2353 0.09650 0.09144 -0.0137 0.0104 1.0000
18.250 1.2336 0.10026 0.09526 -0.0148 0.0102 1.0000
|
Polar data table (+)
Polar graphs
<< Back to AH 94-156 (ah94156-il)