AH 85-L-120/17 (ah85l120-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: AH 85-L-120/17 (ah85l120-il) Reynolds number: 1,000,000 Max Cl/Cd: 51.99 at α=8.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ah85l120-il-1000000-n5.txt Download as CSV file: xf-ah85l120-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: AH 85-L-120/17
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.000 -0.8896 0.11410 0.11257 -0.0035 1.0000 0.0033
-15.750 -0.8622 0.11613 0.11465 -0.0030 1.0000 0.0034
-15.500 -1.0333 0.07034 0.06822 -0.0280 1.0000 0.0031
-15.000 -1.0835 0.05380 0.05122 -0.0375 0.9572 0.0031
-14.750 -1.0763 0.04995 0.04719 -0.0413 0.9412 0.0031
-14.500 -1.0895 0.04423 0.04113 -0.0441 0.9284 0.0031
-14.250 -1.0993 0.03966 0.03629 -0.0455 0.9195 0.0032
-14.000 -1.0991 0.03637 0.03271 -0.0463 0.9132 0.0031
-13.750 -1.0715 0.03646 0.03286 -0.0476 0.9085 0.0034
-13.500 -1.0833 0.03221 0.02822 -0.0468 0.9028 0.0034
-13.250 -1.0713 0.03066 0.02652 -0.0468 0.8987 0.0034
-13.000 -1.0401 0.03135 0.02733 -0.0481 0.8954 0.0037
-12.750 -1.0396 0.02852 0.02419 -0.0469 0.8912 0.0036
-12.500 -1.0274 0.02693 0.02243 -0.0465 0.8881 0.0037
-12.250 -1.0033 0.02688 0.02239 -0.0470 0.8858 0.0040
-12.000 -0.9944 0.02501 0.02030 -0.0458 0.8829 0.0040
-11.750 -0.9801 0.02375 0.01889 -0.0451 0.8803 0.0041
-11.500 -0.9552 0.02379 0.01894 -0.0456 0.8781 0.0044
-11.250 -0.9402 0.02249 0.01745 -0.0448 0.8757 0.0044
-11.000 -0.9216 0.02158 0.01642 -0.0443 0.8735 0.0046
-10.750 -0.9049 0.02056 0.01527 -0.0434 0.8713 0.0047
-10.500 -0.8846 0.02007 0.01472 -0.0429 0.8694 0.0049
-10.250 -0.8676 0.01909 0.01361 -0.0419 0.8674 0.0050
-10.000 -0.8484 0.01841 0.01284 -0.0411 0.8654 0.0051
-9.750 -0.8325 0.01739 0.01169 -0.0398 0.8634 0.0050
-9.500 -0.8101 0.01711 0.01136 -0.0394 0.8616 0.0052
-9.250 -0.7967 0.01594 0.01004 -0.0375 0.8596 0.0056
-9.000 -0.7769 0.01550 0.00953 -0.0365 0.8578 0.0054
-8.750 -0.7590 0.01493 0.00895 -0.0352 0.8561 0.0062
-8.500 -0.7393 0.01452 0.00850 -0.0340 0.8544 0.0064
-8.250 -0.7222 0.01396 0.00787 -0.0324 0.8526 0.0066
-8.000 -0.7030 0.01361 0.00749 -0.0311 0.8508 0.0068
-7.750 -0.6832 0.01330 0.00713 -0.0298 0.8489 0.0073
-7.500 -0.6644 0.01287 0.00663 -0.0284 0.8472 0.0074
-7.250 -0.6441 0.01248 0.00616 -0.0273 0.8457 0.0077
-7.000 -0.6222 0.01220 0.00584 -0.0264 0.8443 0.0080
-6.750 -0.6003 0.01192 0.00554 -0.0255 0.8428 0.0081
-6.500 -0.5801 0.01153 0.00510 -0.0243 0.8411 0.0087
-6.250 -0.5595 0.01114 0.00470 -0.0231 0.8393 0.0099
-6.000 -0.5369 0.01089 0.00443 -0.0223 0.8377 0.0106
-5.750 -0.5139 0.01068 0.00419 -0.0216 0.8360 0.0117
-5.500 -0.4908 0.01046 0.00394 -0.0209 0.8344 0.0126
-5.250 -0.4683 0.01018 0.00366 -0.0200 0.8329 0.0162
-5.000 -0.4445 0.01000 0.00346 -0.0194 0.8313 0.0179
-4.750 -0.4212 0.00977 0.00325 -0.0187 0.8298 0.0237
-4.500 -0.3980 0.00955 0.00305 -0.0180 0.8282 0.0323
-4.250 -0.3758 0.00925 0.00285 -0.0171 0.8263 0.0524
-4.000 -0.3551 0.00888 0.00264 -0.0160 0.8243 0.0910
-3.750 -0.3335 0.00855 0.00245 -0.0150 0.8223 0.1268
-3.500 -0.3157 0.00802 0.00221 -0.0133 0.8202 0.2026
-3.250 -0.2949 0.00766 0.00203 -0.0122 0.8182 0.2557
-3.000 -0.2810 0.00696 0.00177 -0.0098 0.8160 0.3713
-2.750 -0.2698 0.00619 0.00153 -0.0068 0.8133 0.5027
-2.500 -0.2535 0.00571 0.00137 -0.0046 0.8104 0.5855
-2.250 -0.2325 0.00545 0.00126 -0.0033 0.8077 0.6330
-2.000 -0.2113 0.00522 0.00120 -0.0019 0.8053 0.6799
-1.750 -0.1864 0.00513 0.00116 -0.0013 0.8033 0.7051
-1.500 -0.1610 0.00508 0.00116 -0.0009 0.8012 0.7260
-1.250 -0.1351 0.00505 0.00117 -0.0005 0.7987 0.7440
-1.000 -0.1086 0.00504 0.00118 -0.0003 0.7959 0.7553
-0.750 -0.0818 0.00503 0.00120 -0.0001 0.7930 0.7656
-0.500 -0.0548 0.00504 0.00119 0.0000 0.7903 0.7746
-0.250 -0.0273 0.00505 0.00120 0.0000 0.7875 0.7795
0.000 0.0000 0.00505 0.00121 0.0000 0.7836 0.7837
0.250 0.0273 0.00505 0.00120 0.0000 0.7793 0.7875
0.500 0.0548 0.00504 0.00119 0.0000 0.7742 0.7902
0.750 0.0818 0.00503 0.00119 0.0002 0.7651 0.7930
1.000 0.1086 0.00503 0.00118 0.0003 0.7555 0.7958
1.250 0.1351 0.00505 0.00117 0.0005 0.7436 0.7987
1.500 0.1611 0.00508 0.00116 0.0009 0.7268 0.8012
1.750 0.1866 0.00513 0.00117 0.0013 0.7058 0.8032
2.000 0.2113 0.00522 0.00120 0.0019 0.6798 0.8053
2.250 0.2329 0.00543 0.00126 0.0032 0.6352 0.8077
2.500 0.2537 0.00570 0.00137 0.0045 0.5867 0.8104
2.750 0.2732 0.00604 0.00150 0.0061 0.5289 0.8132
3.000 0.2830 0.00686 0.00175 0.0094 0.3884 0.8159
3.250 0.2959 0.00761 0.00201 0.0120 0.2636 0.8181
3.500 0.3159 0.00800 0.00220 0.0133 0.2047 0.8202
3.750 0.3349 0.00847 0.00243 0.0148 0.1395 0.8223
4.000 0.3562 0.00881 0.00262 0.0158 0.0998 0.8243
4.250 0.3767 0.00920 0.00284 0.0170 0.0584 0.8262
4.500 0.3984 0.00952 0.00305 0.0179 0.0347 0.8281
4.750 0.4212 0.00977 0.00326 0.0187 0.0238 0.8299
5.000 0.4446 0.00999 0.00346 0.0194 0.0189 0.8314
5.250 0.4680 0.01020 0.00368 0.0201 0.0155 0.8329
5.500 0.4908 0.01045 0.00393 0.0209 0.0127 0.8344
5.750 0.5140 0.01067 0.00418 0.0216 0.0118 0.8361
6.000 0.5369 0.01089 0.00441 0.0223 0.0105 0.8377
6.250 0.5588 0.01118 0.00473 0.0232 0.0095 0.8393
6.500 0.5801 0.01151 0.00508 0.0243 0.0086 0.8410
6.750 0.6011 0.01185 0.00546 0.0253 0.0082 0.8427
7.000 0.6232 0.01211 0.00574 0.0262 0.0077 0.8442
7.250 0.6433 0.01252 0.00621 0.0274 0.0077 0.8457
7.500 0.6640 0.01287 0.00664 0.0285 0.0075 0.8472
7.750 0.6833 0.01328 0.00711 0.0298 0.0074 0.8489
8.000 0.7026 0.01362 0.00749 0.0312 0.0066 0.8508
8.250 0.7227 0.01390 0.00780 0.0323 0.0063 0.8525
8.500 0.7414 0.01434 0.00828 0.0336 0.0061 0.8543
8.750 0.7590 0.01491 0.00889 0.0351 0.0056 0.8561
9.000 0.7728 0.01583 0.00991 0.0372 0.0052 0.8580
9.250 0.7954 0.01602 0.01012 0.0377 0.0054 0.8597
9.500 0.8082 0.01728 0.01156 0.0397 0.0052 0.8618
9.750 0.8293 0.01771 0.01206 0.0403 0.0051 0.8636
10.000 0.8471 0.01857 0.01302 0.0414 0.0050 0.8655
10.250 0.8675 0.01906 0.01358 0.0419 0.0049 0.8674
10.500 0.8861 0.01984 0.01447 0.0428 0.0047 0.8694
10.750 0.9033 0.02076 0.01550 0.0437 0.0047 0.8714
11.000 0.9179 0.02209 0.01698 0.0448 0.0047 0.8736
11.250 0.9374 0.02284 0.01786 0.0451 0.0044 0.8758
11.500 0.9545 0.02387 0.01904 0.0457 0.0044 0.8782
11.750 0.9695 0.02512 0.02044 0.0464 0.0042 0.8807
12.000 0.9780 0.02712 0.02267 0.0476 0.0042 0.8835
12.250 0.9935 0.02808 0.02373 0.0480 0.0041 0.8862
12.500 1.0222 0.02755 0.02312 0.0470 0.0037 0.8884
12.750 1.0295 0.02970 0.02551 0.0478 0.0037 0.8918
13.000 1.0403 0.03133 0.02730 0.0480 0.0037 0.8957
13.250 1.0584 0.03206 0.02808 0.0477 0.0035 0.8995
13.500 1.0545 0.03543 0.03176 0.0484 0.0035 0.9042
13.750 1.0822 0.03530 0.03158 0.0471 0.0033 0.9083
14.000 1.0797 0.03861 0.03517 0.0470 0.0034 0.9143
14.250 1.0881 0.04105 0.03778 0.0456 0.0033 0.9206
14.750 1.0920 0.04807 0.04521 0.0415 0.0031 0.9415
15.000 1.0728 0.05564 0.05314 0.0364 0.0031 0.9597
15.250 1.0432 0.06468 0.06244 0.0314 0.0030 1.0000
15.500 1.0393 0.06935 0.06720 0.0285 0.0031 1.0000
16.000 0.9137 0.10848 0.10691 0.0058 0.0033 1.0000
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