AH 83-159 (ah83159-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: AH 83-159 (ah83159-il) Reynolds number: 500,000 Max Cl/Cd: 105.52 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ah83159-il-500000-n5.txt Download as CSV file: xf-ah83159-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: AH 83-159
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.2115 0.08648 0.08301 -0.0949 0.7500 0.0072
-11.000 -0.2202 0.08067 0.07722 -0.0976 0.7476 0.0071
-10.750 -0.2350 0.07359 0.07017 -0.1013 0.7453 0.0071
-10.500 -0.2653 0.06202 0.05861 -0.1099 0.7429 0.0069
-10.250 -0.3063 0.05302 0.04949 -0.1139 0.7403 0.0068
-10.000 -0.3466 0.04643 0.04272 -0.1127 0.7373 0.0066
-9.750 -0.3932 0.03986 0.03586 -0.1080 0.7342 0.0066
-9.500 -0.4244 0.03506 0.03071 -0.1025 0.7314 0.0067
-9.250 -0.4412 0.03042 0.02558 -0.0982 0.7290 0.0068
-8.750 -0.4320 0.02499 0.01939 -0.0933 0.7247 0.0071
-8.500 -0.4175 0.02321 0.01734 -0.0919 0.7222 0.0072
-8.250 -0.3999 0.02176 0.01564 -0.0908 0.7197 0.0074
-8.000 -0.3805 0.02047 0.01412 -0.0899 0.7175 0.0075
-7.750 -0.3584 0.01968 0.01315 -0.0893 0.7155 0.0078
-7.500 -0.3360 0.01887 0.01216 -0.0887 0.7137 0.0080
-7.250 -0.3130 0.01813 0.01126 -0.0882 0.7120 0.0081
-7.000 -0.2916 0.01695 0.00997 -0.0875 0.7099 0.0084
-6.750 -0.2691 0.01616 0.00910 -0.0870 0.7077 0.0086
-6.500 -0.2460 0.01553 0.00841 -0.0865 0.7054 0.0088
-6.250 -0.2225 0.01499 0.00779 -0.0860 0.7033 0.0090
-6.000 -0.1985 0.01451 0.00726 -0.0857 0.7014 0.0094
-5.750 -0.1745 0.01406 0.00674 -0.0853 0.6997 0.0097
-5.500 -0.1500 0.01367 0.00627 -0.0850 0.6981 0.0103
-5.250 -0.1253 0.01328 0.00584 -0.0847 0.6961 0.0109
-5.000 -0.1001 0.01295 0.00546 -0.0845 0.6940 0.0114
-4.750 -0.0754 0.01254 0.00503 -0.0842 0.6918 0.0125
-4.500 -0.0496 0.01227 0.00474 -0.0841 0.6898 0.0139
-4.250 -0.0235 0.01203 0.00446 -0.0841 0.6880 0.0160
-4.000 0.0025 0.01178 0.00420 -0.0840 0.6862 0.0198
-3.750 0.0288 0.01155 0.00396 -0.0840 0.6845 0.0252
-3.500 0.0553 0.01134 0.00375 -0.0840 0.6826 0.0323
-3.250 0.0817 0.01112 0.00358 -0.0841 0.6806 0.0450
-3.000 0.1078 0.01083 0.00341 -0.0842 0.6786 0.0752
-2.750 0.1329 0.01043 0.00325 -0.0842 0.6766 0.1362
-2.500 0.1574 0.00992 0.00307 -0.0842 0.6746 0.2344
-2.250 0.1810 0.00926 0.00287 -0.0842 0.6726 0.3732
-2.000 0.2038 0.00842 0.00264 -0.0841 0.6709 0.5512
-1.750 0.2260 0.00798 0.00278 -0.0831 0.6693 0.7068
-1.500 0.2518 0.00820 0.00313 -0.0824 0.6672 0.7571
-1.250 0.2797 0.00843 0.00334 -0.0824 0.6651 0.7789
-1.000 0.3077 0.00866 0.00354 -0.0824 0.6630 0.7924
-0.750 0.3356 0.00886 0.00371 -0.0823 0.6609 0.8006
-0.500 0.3636 0.00902 0.00382 -0.0824 0.6589 0.8063
-0.250 0.3911 0.00918 0.00394 -0.0823 0.6570 0.8101
0.000 0.4196 0.00929 0.00399 -0.0826 0.6553 0.8143
0.250 0.4490 0.00932 0.00399 -0.0833 0.6532 0.8184
0.500 0.4767 0.00937 0.00404 -0.0834 0.6509 0.8197
0.750 0.5047 0.00941 0.00408 -0.0836 0.6486 0.8209
1.000 0.5327 0.00945 0.00411 -0.0839 0.6463 0.8223
1.250 0.5609 0.00949 0.00412 -0.0842 0.6440 0.8237
1.500 0.5894 0.00953 0.00413 -0.0846 0.6420 0.8253
1.750 0.6178 0.00957 0.00416 -0.0850 0.6397 0.8268
2.000 0.6460 0.00960 0.00420 -0.0854 0.6369 0.8285
2.250 0.6745 0.00962 0.00423 -0.0859 0.6338 0.8303
2.500 0.7032 0.00964 0.00423 -0.0864 0.6308 0.8318
2.750 0.7318 0.00967 0.00424 -0.0869 0.6279 0.8332
3.000 0.7592 0.00971 0.00429 -0.0871 0.6247 0.8340
3.250 0.7863 0.00973 0.00436 -0.0872 0.6204 0.8349
3.500 0.8135 0.00976 0.00441 -0.0874 0.6161 0.8357
3.750 0.8410 0.00980 0.00443 -0.0876 0.6125 0.8366
4.000 0.8680 0.00985 0.00454 -0.0878 0.6084 0.8377
4.250 0.8950 0.00990 0.00462 -0.0879 0.6040 0.8389
4.500 0.9221 0.00995 0.00470 -0.0881 0.6000 0.8400
4.750 0.9491 0.01001 0.00479 -0.0883 0.5955 0.8411
5.000 0.9758 0.01007 0.00489 -0.0885 0.5903 0.8422
5.250 1.0024 0.01014 0.00499 -0.0886 0.5852 0.8433
5.500 1.0288 0.01022 0.00511 -0.0887 0.5796 0.8447
5.750 1.0546 0.01031 0.00522 -0.0887 0.5723 0.8459
6.000 1.0799 0.01041 0.00535 -0.0887 0.5640 0.8469
6.250 1.1032 0.01052 0.00548 -0.0881 0.5536 0.8477
6.500 1.1248 0.01066 0.00564 -0.0873 0.5402 0.8485
6.750 1.1444 0.01087 0.00583 -0.0861 0.5228 0.8494
7.000 1.1606 0.01116 0.00608 -0.0843 0.5023 0.8506
7.250 1.1724 0.01156 0.00642 -0.0817 0.4787 0.8520
7.500 1.1753 0.01206 0.00682 -0.0775 0.4529 0.8535
7.750 1.1694 0.01284 0.00747 -0.0720 0.4221 0.8554
8.000 1.1616 0.01393 0.00843 -0.0668 0.3913 0.8574
8.250 1.1550 0.01522 0.00956 -0.0622 0.3605 0.8595
8.500 1.1510 0.01657 0.01078 -0.0583 0.3314 0.8609
8.750 1.1497 0.01785 0.01196 -0.0550 0.3064 0.8620
9.000 1.1499 0.01916 0.01318 -0.0520 0.2826 0.8631
9.250 1.1515 0.02047 0.01442 -0.0493 0.2589 0.8642
9.500 1.1533 0.02184 0.01571 -0.0468 0.2363 0.8656
9.750 1.1510 0.02350 0.01723 -0.0440 0.2054 0.8669
10.000 1.1524 0.02504 0.01865 -0.0417 0.1809 0.8679
10.250 1.1513 0.02677 0.02024 -0.0393 0.1515 0.8689
10.500 1.1498 0.02862 0.02192 -0.0371 0.1213 0.8699
10.750 1.1490 0.03053 0.02366 -0.0350 0.0932 0.8707
11.000 1.1508 0.03234 0.02534 -0.0334 0.0711 0.8716
11.250 1.1557 0.03398 0.02691 -0.0320 0.0551 0.8724
11.500 1.1626 0.03553 0.02842 -0.0309 0.0443 0.8733
12.000 1.1769 0.03874 0.03159 -0.0290 0.0271 0.8747
12.250 1.1858 0.04022 0.03309 -0.0282 0.0229 0.8753
12.500 1.1934 0.04185 0.03473 -0.0275 0.0186 0.8759
12.750 1.2030 0.04335 0.03629 -0.0269 0.0158 0.8765
13.000 1.2102 0.04510 0.03806 -0.0262 0.0130 0.8771
13.250 1.2189 0.04676 0.03977 -0.0257 0.0107 0.8777
13.500 1.2258 0.04862 0.04167 -0.0251 0.0088 0.8783
13.750 1.2339 0.05040 0.04354 -0.0247 0.0078 0.8789
14.000 1.2393 0.05251 0.04568 -0.0242 0.0065 0.8795
14.250 1.2464 0.05448 0.04774 -0.0239 0.0059 0.8801
14.500 1.2532 0.05653 0.04988 -0.0237 0.0055 0.8807
14.750 1.2594 0.05868 0.05211 -0.0234 0.0052 0.8815
15.000 1.2649 0.06096 0.05447 -0.0233 0.0050 0.8823
15.250 1.2678 0.06358 0.05717 -0.0232 0.0045 0.8830
15.500 1.2721 0.06612 0.05980 -0.0233 0.0044 0.8836
15.750 1.2742 0.06899 0.06277 -0.0234 0.0042 0.8841
16.000 1.2786 0.07160 0.06548 -0.0236 0.0041 0.8846
16.250 1.2815 0.07448 0.06848 -0.0239 0.0039 0.8852
16.500 1.2849 0.07733 0.07143 -0.0244 0.0038 0.8857
16.750 1.2865 0.08050 0.07470 -0.0249 0.0037 0.8861
17.000 1.2883 0.08368 0.07799 -0.0256 0.0035 0.8866
17.250 1.2897 0.08696 0.08137 -0.0263 0.0034 0.8871
17.500 1.2899 0.09047 0.08498 -0.0272 0.0033 0.8875
17.750 1.2879 0.09441 0.08903 -0.0283 0.0032 0.8879
18.000 1.2878 0.09810 0.09282 -0.0294 0.0032 0.8883
18.500 1.2834 0.10625 0.10121 -0.0322 0.0030 0.8892
18.750 1.2801 0.11060 0.10567 -0.0338 0.0030 0.8897
19.000 1.2744 0.11541 0.11060 -0.0357 0.0029 0.8901
19.250 1.2702 0.12005 0.11536 -0.0377 0.0029 0.8906
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Polar data table (+)
Polar graphs
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