AS5048 (18%) (as5048-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: AS5048 (18%) (as5048-il) Reynolds number: 100,000 Max Cl/Cd: 40.44 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-as5048-il-100000-n5.txt Download as CSV file: xf-as5048-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: AS5048 (18%)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.000 -0.6223 0.09629 0.09049 -0.0570 1.0000 0.0226
-13.750 -0.6488 0.08890 0.08294 -0.0606 1.0000 0.0223
-13.500 -0.6736 0.08266 0.07653 -0.0630 1.0000 0.0222
-13.250 -0.6965 0.07723 0.07091 -0.0644 1.0000 0.0221
-13.000 -0.7169 0.07252 0.06601 -0.0650 1.0000 0.0220
-12.750 -0.7352 0.06836 0.06166 -0.0649 1.0000 0.0221
-12.500 -0.7517 0.06462 0.05771 -0.0643 1.0000 0.0222
-12.250 -0.7659 0.06129 0.05417 -0.0631 1.0000 0.0224
-12.000 -0.7785 0.05826 0.05091 -0.0616 1.0000 0.0226
-11.750 -0.7893 0.05552 0.04794 -0.0596 1.0000 0.0228
-11.500 -0.7985 0.05302 0.04520 -0.0571 1.0000 0.0230
-11.250 -0.8060 0.05077 0.04271 -0.0543 1.0000 0.0233
-11.000 -0.8115 0.04877 0.04047 -0.0511 1.0000 0.0235
-10.750 -0.8141 0.04695 0.03844 -0.0478 1.0000 0.0236
-10.250 -0.7725 0.04246 0.03373 -0.0484 0.9852 0.0243
-10.000 -0.7449 0.04041 0.03155 -0.0494 0.9566 0.0248
-9.750 -0.7072 0.03840 0.02938 -0.0519 0.9350 0.0256
-9.500 -0.6640 0.03655 0.02734 -0.0550 0.9221 0.0266
-9.250 -0.6204 0.03493 0.02550 -0.0583 0.9109 0.0285
-9.000 -0.5797 0.03349 0.02406 -0.0616 0.8997 0.0303
-8.750 -0.5409 0.03219 0.02264 -0.0642 0.8891 0.0319
-8.500 -0.5086 0.03099 0.02127 -0.0660 0.8782 0.0333
-8.250 -0.4849 0.02969 0.01995 -0.0670 0.8680 0.0351
-8.000 -0.4634 0.02860 0.01874 -0.0676 0.8591 0.0378
-7.750 -0.4452 0.02756 0.01757 -0.0674 0.8512 0.0403
-7.500 -0.4296 0.02652 0.01644 -0.0669 0.8440 0.0428
-7.250 -0.4121 0.02563 0.01540 -0.0663 0.8381 0.0462
-7.000 -0.3997 0.02477 0.01453 -0.0648 0.8321 0.0513
-6.750 -0.3867 0.02396 0.01372 -0.0633 0.8271 0.0601
-6.500 -0.3748 0.02289 0.01283 -0.0617 0.8230 0.0881
-6.250 -0.3789 0.02106 0.01183 -0.0583 0.8186 0.2162
-6.000 -0.3865 0.01932 0.01097 -0.0541 0.8137 0.3615
-5.750 -0.3673 0.02004 0.01275 -0.0505 0.8100 0.5272
-5.500 -0.3434 0.02077 0.01339 -0.0492 0.8065 0.5797
-5.000 -0.2927 0.02320 0.01558 -0.0459 0.8007 0.6371
-4.750 -0.2619 0.02376 0.01604 -0.0455 0.7977 0.6425
-4.500 -0.2430 0.02351 0.01561 -0.0447 0.7941 0.6535
-4.250 -0.2120 0.02386 0.01585 -0.0447 0.7912 0.6573
-4.000 -0.1843 0.02397 0.01582 -0.0446 0.7886 0.6631
-3.750 -0.1620 0.02371 0.01538 -0.0444 0.7862 0.6714
-3.500 -0.1363 0.02386 0.01549 -0.0438 0.7830 0.6749
-3.250 -0.1123 0.02387 0.01542 -0.0433 0.7796 0.6798
-3.000 -0.0932 0.02352 0.01493 -0.0428 0.7763 0.6876
-2.750 -0.0657 0.02360 0.01495 -0.0426 0.7736 0.6904
-2.500 -0.0384 0.02361 0.01488 -0.0425 0.7709 0.6939
-2.250 -0.0134 0.02354 0.01471 -0.0424 0.7682 0.6985
-2.000 0.0050 0.02330 0.01440 -0.0417 0.7644 0.7046
-1.750 0.0295 0.02335 0.01444 -0.0412 0.7609 0.7072
-1.500 0.0549 0.02336 0.01440 -0.0409 0.7576 0.7102
-1.250 0.0811 0.02331 0.01429 -0.0409 0.7546 0.7138
-1.000 0.1078 0.02318 0.01407 -0.0413 0.7520 0.7180
-0.750 0.1271 0.02312 0.01400 -0.0405 0.7476 0.7218
-0.500 0.1502 0.02317 0.01406 -0.0398 0.7434 0.7241
-0.250 0.1759 0.02317 0.01405 -0.0397 0.7397 0.7266
0.000 0.2037 0.02313 0.01396 -0.0400 0.7365 0.7292
0.250 0.2278 0.02313 0.01395 -0.0397 0.7325 0.7324
0.500 0.2484 0.02315 0.01396 -0.0391 0.7270 0.7360
0.750 0.2745 0.02309 0.01389 -0.0392 0.7224 0.7385
1.000 0.3039 0.02304 0.01381 -0.0396 0.7187 0.7404
1.250 0.3241 0.02315 0.01398 -0.0384 0.7126 0.7428
1.500 0.3479 0.02316 0.01403 -0.0380 0.7067 0.7453
1.750 0.3774 0.02306 0.01391 -0.0385 0.7023 0.7477
2.000 0.4003 0.02311 0.01398 -0.0380 0.6963 0.7503
2.250 0.4239 0.02313 0.01403 -0.0377 0.6898 0.7533
2.500 0.4538 0.02300 0.01390 -0.0382 0.6851 0.7556
2.750 0.4747 0.02308 0.01406 -0.0371 0.6781 0.7576
3.000 0.4991 0.02304 0.01408 -0.0366 0.6712 0.7596
3.250 0.5313 0.02280 0.01385 -0.0374 0.6664 0.7616
3.500 0.5477 0.02291 0.01408 -0.0356 0.6563 0.7644
3.750 0.5800 0.02254 0.01370 -0.0363 0.6497 0.7671
4.000 0.5983 0.02253 0.01379 -0.0349 0.6382 0.7700
4.250 0.6245 0.02227 0.01357 -0.0346 0.6289 0.7722
4.500 0.6475 0.02206 0.01345 -0.0336 0.6186 0.7741
4.750 0.6666 0.02201 0.01353 -0.0322 0.6067 0.7764
5.000 0.6891 0.02185 0.01346 -0.0312 0.5952 0.7790
5.250 0.7140 0.02163 0.01330 -0.0306 0.5837 0.7819
5.500 0.7354 0.02154 0.01330 -0.0296 0.5692 0.7849
5.750 0.7581 0.02143 0.01324 -0.0288 0.5533 0.7878
6.000 0.7803 0.02129 0.01314 -0.0277 0.5360 0.7901
6.250 0.8012 0.02120 0.01310 -0.0264 0.5159 0.7926
6.500 0.8235 0.02113 0.01299 -0.0252 0.4937 0.7952
6.750 0.8447 0.02116 0.01293 -0.0240 0.4696 0.7983
7.000 0.8628 0.02139 0.01308 -0.0225 0.4434 0.8019
7.250 0.8792 0.02174 0.01333 -0.0208 0.4177 0.8056
7.500 0.8909 0.02216 0.01369 -0.0182 0.3936 0.8088
7.750 0.9018 0.02268 0.01413 -0.0156 0.3707 0.8123
8.000 0.9135 0.02332 0.01472 -0.0135 0.3480 0.8161
8.250 0.9255 0.02404 0.01538 -0.0116 0.3267 0.8203
8.500 0.9368 0.02482 0.01611 -0.0097 0.3073 0.8244
8.750 0.9471 0.02561 0.01688 -0.0077 0.2899 0.8288
9.000 0.9578 0.02645 0.01773 -0.0059 0.2738 0.8343
9.250 0.9692 0.02734 0.01863 -0.0044 0.2590 0.8404
9.500 0.9789 0.02821 0.01955 -0.0025 0.2457 0.8470
9.750 0.9890 0.02915 0.02053 -0.0009 0.2336 0.8550
10.000 0.9969 0.03014 0.02155 0.0010 0.2228 0.8644
10.250 1.0053 0.03107 0.02259 0.0029 0.2120 0.8771
10.500 1.0106 0.03198 0.02360 0.0053 0.2030 0.8985
10.750 1.0155 0.03290 0.02459 0.0075 0.1942 0.9872
11.000 1.0282 0.03404 0.02578 0.0077 0.1846 1.0000
11.250 1.0391 0.03544 0.02713 0.0081 0.1761 1.0000
11.500 1.0520 0.03674 0.02853 0.0083 0.1669 1.0000
11.750 1.0621 0.03820 0.02996 0.0087 0.1594 1.0000
12.000 1.0729 0.03965 0.03150 0.0091 0.1512 1.0000
12.250 1.0814 0.04124 0.03308 0.0096 0.1442 1.0000
12.500 1.0909 0.04280 0.03475 0.0100 0.1368 1.0000
12.750 1.0975 0.04455 0.03648 0.0105 0.1308 1.0000
13.000 1.1058 0.04624 0.03831 0.0109 0.1238 1.0000
13.250 1.1104 0.04819 0.04024 0.0114 0.1185 1.0000
13.500 1.1178 0.05001 0.04220 0.0117 0.1125 1.0000
13.750 1.1221 0.05208 0.04432 0.0120 0.1074 1.0000
14.000 1.1259 0.05422 0.04650 0.0124 0.1029 1.0000
14.250 1.1307 0.05638 0.04880 0.0126 0.0981 1.0000
14.500 1.1326 0.05879 0.05125 0.0127 0.0942 1.0000
14.750 1.1354 0.06121 0.05372 0.0128 0.0905 1.0000
15.000 1.1378 0.06376 0.05642 0.0128 0.0866 1.0000
15.250 1.1386 0.06650 0.05924 0.0126 0.0834 1.0000
15.500 1.1396 0.06919 0.06191 0.0125 0.0807 1.0000
15.750 1.1402 0.07220 0.06513 0.0121 0.0777 1.0000
16.000 1.1394 0.07538 0.06846 0.0116 0.0748 1.0000
16.250 1.1381 0.07863 0.07178 0.0109 0.0724 1.0000
16.500 1.1382 0.08167 0.07483 0.0103 0.0704 1.0000
16.750 1.1352 0.08538 0.07872 0.0094 0.0683 1.0000
17.000 1.1304 0.08945 0.08299 0.0082 0.0662 1.0000
17.250 1.1252 0.09361 0.08729 0.0067 0.0642 1.0000
17.500 1.1213 0.09760 0.09137 0.0053 0.0624 1.0000
17.750 1.1201 0.10112 0.09492 0.0040 0.0609 1.0000
18.000 1.1145 0.10553 0.09946 0.0022 0.0594 1.0000
18.250 1.1004 0.11167 0.10586 -0.0007 0.0582 1.0000
18.500 1.0847 0.11825 0.11265 -0.0040 0.0570 1.0000
18.750 1.0672 0.12538 0.11998 -0.0079 0.0559 1.0000
19.000 1.0470 0.13334 0.12813 -0.0125 0.0549 1.0000
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Polar data table (+)
Polar graphs
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