AS5046 (16%) (as5046-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: AS5046 (16%) (as5046-il) Reynolds number: 100,000 Max Cl/Cd: 42.34 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-as5046-il-100000-n5.txt Download as CSV file: xf-as5046-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: AS5046 (16%)
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
------ -------- --------- --------- -------- -------- --------
-12.500 -0.6774 0.08036 0.07447 -0.0498 1.0000 0.0209
-12.250 -0.6925 0.07555 0.06952 -0.0516 1.0000 0.0208
-12.000 -0.7075 0.07110 0.06493 -0.0528 1.0000 0.0208
-11.750 -0.7217 0.06701 0.06069 -0.0535 1.0000 0.0207
-11.500 -0.7348 0.06327 0.05677 -0.0537 1.0000 0.0207
-11.250 -0.7466 0.05984 0.05316 -0.0533 1.0000 0.0206
-11.000 -0.7569 0.05673 0.04986 -0.0524 1.0000 0.0206
-10.750 -0.7660 0.05393 0.04686 -0.0509 1.0000 0.0206
-10.500 -0.7735 0.05143 0.04416 -0.0487 1.0000 0.0205
-10.250 -0.7756 0.04893 0.04143 -0.0467 1.0000 0.0206
-10.000 -0.7740 0.04652 0.03877 -0.0447 1.0000 0.0206
-9.750 -0.7693 0.04425 0.03625 -0.0428 1.0000 0.0207
-9.250 -0.7284 0.03957 0.03117 -0.0442 0.9447 0.0217
-9.000 -0.6944 0.03750 0.02889 -0.0470 0.9201 0.0228
-8.750 -0.6600 0.03537 0.02644 -0.0493 0.9041 0.0240
-8.500 -0.6255 0.03340 0.02415 -0.0508 0.8917 0.0247
-8.250 -0.5919 0.03177 0.02226 -0.0518 0.8812 0.0252
-8.000 -0.5621 0.03033 0.02081 -0.0524 0.8716 0.0260
-7.750 -0.5359 0.02917 0.01961 -0.0524 0.8631 0.0269
-7.500 -0.5129 0.02814 0.01850 -0.0521 0.8552 0.0279
-7.250 -0.4913 0.02720 0.01744 -0.0516 0.8490 0.0294
-7.000 -0.4729 0.02625 0.01646 -0.0509 0.8429 0.0314
-6.750 -0.4540 0.02538 0.01555 -0.0504 0.8375 0.0339
-6.500 -0.4342 0.02457 0.01457 -0.0498 0.8328 0.0364
-6.250 -0.4160 0.02366 0.01363 -0.0492 0.8278 0.0391
-6.000 -0.3959 0.02290 0.01279 -0.0486 0.8230 0.0443
-5.750 -0.3755 0.02209 0.01198 -0.0481 0.8190 0.0534
-5.500 -0.3575 0.02098 0.01109 -0.0474 0.8157 0.0854
-5.250 -0.3563 0.01821 0.00986 -0.0461 0.8114 0.3317
-5.000 -0.3406 0.01861 0.01150 -0.0422 0.8075 0.5388
-4.750 -0.3138 0.01965 0.01243 -0.0411 0.8038 0.5996
-4.500 -0.2875 0.02125 0.01390 -0.0390 0.8007 0.6362
-4.250 -0.2591 0.02206 0.01460 -0.0375 0.7982 0.6444
-4.000 -0.2334 0.02197 0.01434 -0.0377 0.7947 0.6542
-3.750 -0.2064 0.02222 0.01449 -0.0370 0.7912 0.6591
-3.500 -0.1801 0.02209 0.01419 -0.0373 0.7877 0.6680
-3.250 -0.1531 0.02217 0.01415 -0.0370 0.7848 0.6726
-3.000 -0.1258 0.02225 0.01410 -0.0367 0.7821 0.6772
-2.750 -0.0998 0.02208 0.01382 -0.0371 0.7785 0.6842
-2.500 -0.0738 0.02204 0.01370 -0.0370 0.7748 0.6885
-2.250 -0.0473 0.02207 0.01366 -0.0368 0.7713 0.6920
-2.000 -0.0203 0.02201 0.01351 -0.0369 0.7680 0.6965
-1.750 0.0082 0.02181 0.01315 -0.0379 0.7652 0.7026
-1.500 0.0331 0.02185 0.01319 -0.0374 0.7609 0.7052
-1.250 0.0590 0.02186 0.01318 -0.0372 0.7568 0.7084
-1.000 0.0860 0.02183 0.01309 -0.0373 0.7530 0.7121
-0.750 0.1146 0.02174 0.01291 -0.0379 0.7496 0.7164
-0.500 0.1412 0.02169 0.01282 -0.0383 0.7451 0.7200
-0.250 0.1666 0.02171 0.01285 -0.0381 0.7401 0.7222
0.000 0.1937 0.02169 0.01281 -0.0381 0.7357 0.7248
0.250 0.2222 0.02165 0.01271 -0.0383 0.7319 0.7278
0.500 0.2475 0.02166 0.01276 -0.0385 0.7254 0.7309
0.750 0.2762 0.02158 0.01264 -0.0391 0.7199 0.7342
1.000 0.3051 0.02151 0.01252 -0.0393 0.7156 0.7366
1.250 0.3288 0.02156 0.01266 -0.0389 0.7079 0.7387
1.500 0.3563 0.02150 0.01260 -0.0389 0.7022 0.7408
1.750 0.3839 0.02147 0.01257 -0.0390 0.6965 0.7433
2.000 0.4098 0.02147 0.01263 -0.0390 0.6888 0.7461
2.250 0.4398 0.02133 0.01247 -0.0395 0.6833 0.7490
2.500 0.4664 0.02133 0.01253 -0.0398 0.6745 0.7516
2.750 0.4941 0.02115 0.01238 -0.0396 0.6673 0.7533
3.000 0.5185 0.02108 0.01240 -0.0390 0.6572 0.7554
3.250 0.5472 0.02080 0.01213 -0.0388 0.6491 0.7578
3.500 0.5718 0.02071 0.01215 -0.0384 0.6369 0.7603
3.750 0.5983 0.02055 0.01207 -0.0383 0.6255 0.7627
4.000 0.6264 0.02033 0.01190 -0.0384 0.6146 0.7651
4.250 0.6541 0.02015 0.01178 -0.0386 0.6016 0.7679
4.500 0.6787 0.02002 0.01176 -0.0379 0.5866 0.7700
4.750 0.7039 0.01987 0.01171 -0.0373 0.5706 0.7723
5.000 0.7290 0.01974 0.01165 -0.0368 0.5516 0.7746
5.250 0.7546 0.01963 0.01157 -0.0363 0.5295 0.7770
5.500 0.7806 0.01952 0.01141 -0.0359 0.5046 0.7795
5.750 0.8057 0.01955 0.01133 -0.0354 0.4758 0.7824
6.000 0.8288 0.01976 0.01142 -0.0347 0.4452 0.7851
6.250 0.8490 0.02008 0.01165 -0.0334 0.4146 0.7876
6.500 0.8688 0.02052 0.01199 -0.0323 0.3854 0.7903
6.750 0.8880 0.02104 0.01240 -0.0312 0.3577 0.7931
7.000 0.9072 0.02160 0.01289 -0.0302 0.3315 0.7959
7.250 0.9263 0.02222 0.01343 -0.0293 0.3079 0.7990
7.500 0.9446 0.02283 0.01400 -0.0283 0.2866 0.8019
7.750 0.9613 0.02346 0.01461 -0.0270 0.2679 0.8050
8.000 0.9781 0.02411 0.01526 -0.0257 0.2512 0.8086
8.250 0.9949 0.02481 0.01595 -0.0246 0.2357 0.8125
8.500 1.0116 0.02554 0.01669 -0.0236 0.2214 0.8164
8.750 1.0257 0.02626 0.01745 -0.0221 0.2088 0.8199
9.000 1.0376 0.02703 0.01823 -0.0203 0.1975 0.8239
9.250 1.0505 0.02787 0.01911 -0.0188 0.1864 0.8284
9.500 1.0653 0.02876 0.02006 -0.0178 0.1755 0.8334
9.750 1.0767 0.02970 0.02106 -0.0163 0.1663 0.8385
10.000 1.0883 0.03071 0.02217 -0.0150 0.1569 0.8449
10.250 1.1003 0.03175 0.02331 -0.0139 0.1482 0.8520
10.500 1.1086 0.03294 0.02456 -0.0125 0.1406 0.8605
10.750 1.1191 0.03403 0.02582 -0.0113 0.1323 0.8708
11.000 1.1247 0.03535 0.02718 -0.0097 0.1261 0.8852
11.250 1.1309 0.03639 0.02845 -0.0077 0.1191 0.9124
11.500 1.1350 0.03776 0.02988 -0.0065 0.1134 1.0000
11.750 1.1472 0.03937 0.03158 -0.0066 0.1066 1.0000
12.000 1.1559 0.04120 0.03343 -0.0065 0.1010 1.0000
12.250 1.1653 0.04302 0.03533 -0.0064 0.0956 1.0000
12.500 1.1730 0.04495 0.03735 -0.0062 0.0906 1.0000
12.750 1.1782 0.04707 0.03945 -0.0060 0.0868 1.0000
13.000 1.1858 0.04909 0.04164 -0.0058 0.0824 1.0000
13.250 1.1904 0.05132 0.04394 -0.0057 0.0788 1.0000
13.750 1.1980 0.05607 0.04887 -0.0054 0.0727 1.0000
14.000 1.2007 0.05860 0.05152 -0.0053 0.0698 1.0000
14.250 1.2018 0.06129 0.05429 -0.0055 0.0674 1.0000
14.500 1.2029 0.06397 0.05695 -0.0055 0.0653 1.0000
14.750 1.2028 0.06705 0.06028 -0.0058 0.0631 1.0000
15.000 1.2017 0.07029 0.06370 -0.0062 0.0610 1.0000
15.250 1.2000 0.07365 0.06718 -0.0068 0.0592 1.0000
15.500 1.1983 0.07704 0.07066 -0.0076 0.0576 1.0000
15.750 1.1980 0.08022 0.07384 -0.0083 0.0561 1.0000
16.000 1.1910 0.08473 0.07859 -0.0097 0.0547 1.0000
16.250 1.1823 0.08966 0.08376 -0.0115 0.0534 1.0000
16.500 1.1729 0.09482 0.08913 -0.0136 0.0522 1.0000
16.750 1.1628 0.10022 0.09470 -0.0160 0.0511 1.0000
17.000 1.1530 0.10571 0.10035 -0.0187 0.0501 1.0000
17.250 1.1449 0.11099 0.10573 -0.0213 0.0491 1.0000
17.500 1.1431 0.11505 0.10984 -0.0233 0.0481 1.0000
17.750 1.1312 0.12129 0.11620 -0.0266 0.0473 1.0000
18.000 1.1025 0.13152 0.12669 -0.0329 0.0470 1.0000
18.250 1.0578 0.14630 0.14174 -0.0424 0.0469 1.0000
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Polar data table (+)
Polar graphs
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