S1046 17% (Danny Howell) (s1046-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: S1046 17% (Danny Howell) (s1046-il) Reynolds number: 100,000 Max Cl/Cd: 40.45 at α=7.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s1046-il-100000-n5.txt Download as CSV file: xf-s1046-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: S1046 17% (Danny Howell)
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
------ -------- --------- --------- -------- -------- --------
-16.250 -0.9380 0.09365 0.08714 -0.0177 1.0000 0.0644
-16.000 -0.9444 0.08909 0.08256 -0.0197 1.0000 0.0676
-15.750 -0.9519 0.08445 0.07788 -0.0218 1.0000 0.0708
-15.500 -0.9602 0.07966 0.07298 -0.0239 1.0000 0.0749
-15.250 -0.9679 0.07521 0.06849 -0.0257 1.0000 0.0787
-15.000 -0.9768 0.07071 0.06395 -0.0276 1.0000 0.0826
-14.750 -0.9836 0.06656 0.05967 -0.0291 1.0000 0.0871
-14.500 -0.9913 0.06255 0.05564 -0.0305 1.0000 0.0912
-14.250 -0.9988 0.05868 0.05171 -0.0318 1.0000 0.0958
-14.000 -1.0043 0.05516 0.04806 -0.0328 1.0000 0.1013
-13.750 -1.0115 0.05168 0.04458 -0.0337 1.0000 0.1060
-13.500 -1.0160 0.04852 0.04129 -0.0343 1.0000 0.1123
-13.250 -1.0212 0.04553 0.03830 -0.0347 1.0000 0.1179
-13.000 -1.0243 0.04281 0.03549 -0.0348 1.0000 0.1248
-12.750 -1.0272 0.04030 0.03296 -0.0347 1.0000 0.1314
-12.500 -1.0285 0.03802 0.03059 -0.0344 1.0000 0.1396
-12.250 -1.0300 0.03595 0.02853 -0.0338 1.0000 0.1469
-12.000 -1.0288 0.03415 0.02663 -0.0329 1.0000 0.1556
-11.750 -1.0283 0.03252 0.02501 -0.0317 1.0000 0.1632
-11.500 -1.0250 0.03113 0.02355 -0.0303 1.0000 0.1715
-11.250 -1.0217 0.02990 0.02229 -0.0286 1.0000 0.1797
-11.000 -1.0168 0.02884 0.02118 -0.0267 1.0000 0.1877
-10.750 -1.0115 0.02791 0.02018 -0.0244 1.0000 0.1963
-10.500 -1.0056 0.02711 0.01938 -0.0219 1.0000 0.2041
-10.250 -0.9977 0.02638 0.01853 -0.0196 1.0000 0.2133
-10.000 -0.9876 0.02572 0.01791 -0.0175 1.0000 0.2216
-9.750 -0.9756 0.02508 0.01721 -0.0155 1.0000 0.2310
-9.500 -0.9628 0.02450 0.01658 -0.0136 1.0000 0.2404
-9.250 -0.9489 0.02396 0.01603 -0.0118 1.0000 0.2494
-9.000 -0.9346 0.02344 0.01540 -0.0100 1.0000 0.2593
-8.750 -0.9197 0.02298 0.01498 -0.0082 1.0000 0.2678
-8.500 -0.9049 0.02252 0.01447 -0.0063 1.0000 0.2769
-8.250 -0.8905 0.02211 0.01404 -0.0044 1.0000 0.2858
-8.000 -0.8765 0.02171 0.01364 -0.0023 1.0000 0.2940
-7.750 -0.8641 0.02137 0.01326 -0.0001 1.0000 0.3028
-7.500 -0.8475 0.02103 0.01295 0.0014 0.9971 0.3111
-7.250 -0.8096 0.02063 0.01244 -0.0013 0.9828 0.3229
-7.000 -0.7723 0.02026 0.01203 -0.0036 0.9690 0.3340
-6.750 -0.7357 0.01991 0.01166 -0.0057 0.9550 0.3445
-6.500 -0.6998 0.01957 0.01123 -0.0076 0.9408 0.3554
-6.250 -0.6648 0.01926 0.01086 -0.0092 0.9266 0.3664
-6.000 -0.6310 0.01897 0.01055 -0.0105 0.9123 0.3760
-5.750 -0.5994 0.01870 0.01019 -0.0113 0.8977 0.3865
-5.500 -0.5695 0.01847 0.00991 -0.0117 0.8832 0.3963
-5.250 -0.5412 0.01826 0.00966 -0.0117 0.8691 0.4058
-5.000 -0.5145 0.01807 0.00934 -0.0114 0.8552 0.4165
-4.750 -0.4884 0.01790 0.00917 -0.0109 0.8415 0.4253
-4.500 -0.4633 0.01774 0.00895 -0.0103 0.8278 0.4353
-4.250 -0.4381 0.01760 0.00875 -0.0097 0.8147 0.4452
-4.000 -0.4126 0.01746 0.00859 -0.0091 0.8025 0.4546
-3.500 -0.3614 0.01722 0.00825 -0.0079 0.7784 0.4747
-3.250 -0.3359 0.01711 0.00811 -0.0074 0.7666 0.4849
-3.000 -0.3103 0.01701 0.00794 -0.0068 0.7556 0.4957
-2.750 -0.2845 0.01692 0.00786 -0.0062 0.7441 0.5052
-2.500 -0.2590 0.01684 0.00775 -0.0056 0.7324 0.5158
-2.250 -0.2332 0.01677 0.00764 -0.0050 0.7217 0.5264
-2.000 -0.2073 0.01671 0.00758 -0.0044 0.7107 0.5364
-1.750 -0.1817 0.01666 0.00751 -0.0039 0.6992 0.5474
-1.500 -0.1558 0.01661 0.00744 -0.0033 0.6886 0.5580
-1.250 -0.1298 0.01658 0.00741 -0.0027 0.6777 0.5682
-1.000 -0.1040 0.01655 0.00736 -0.0022 0.6662 0.5795
-0.750 -0.0779 0.01653 0.00733 -0.0016 0.6558 0.5901
-0.500 -0.0519 0.01652 0.00732 -0.0011 0.6447 0.6006
-0.250 -0.0261 0.01651 0.00730 -0.0006 0.6333 0.6119
0.000 0.0000 0.01651 0.00729 0.0000 0.6228 0.6229
0.250 0.0261 0.01651 0.00730 0.0006 0.6120 0.6333
0.500 0.0519 0.01652 0.00732 0.0011 0.6006 0.6447
0.750 0.0779 0.01653 0.00733 0.0016 0.5902 0.6558
1.000 0.1040 0.01655 0.00736 0.0022 0.5795 0.6662
1.250 0.1298 0.01658 0.00740 0.0027 0.5683 0.6777
1.500 0.1558 0.01661 0.00744 0.0033 0.5580 0.6886
1.750 0.1817 0.01666 0.00751 0.0039 0.5474 0.6992
2.000 0.2073 0.01671 0.00758 0.0044 0.5363 0.7107
2.250 0.2332 0.01677 0.00764 0.0050 0.5264 0.7217
2.500 0.2590 0.01684 0.00775 0.0056 0.5158 0.7324
2.750 0.2845 0.01692 0.00786 0.0062 0.5052 0.7441
3.000 0.3103 0.01701 0.00794 0.0068 0.4958 0.7556
3.250 0.3359 0.01711 0.00811 0.0074 0.4849 0.7665
3.500 0.3614 0.01722 0.00825 0.0079 0.4747 0.7784
4.000 0.4126 0.01746 0.00859 0.0091 0.4546 0.8025
4.250 0.4381 0.01760 0.00875 0.0097 0.4452 0.8147
4.500 0.4633 0.01774 0.00895 0.0103 0.4353 0.8277
4.750 0.4884 0.01790 0.00917 0.0109 0.4253 0.8415
5.000 0.5145 0.01807 0.00934 0.0114 0.4165 0.8552
5.250 0.5412 0.01826 0.00966 0.0117 0.4058 0.8691
5.500 0.5695 0.01847 0.00991 0.0117 0.3964 0.8832
5.750 0.5994 0.01870 0.01019 0.0113 0.3865 0.8978
6.000 0.6311 0.01897 0.01055 0.0105 0.3760 0.9123
6.250 0.6649 0.01926 0.01085 0.0092 0.3663 0.9266
6.500 0.6998 0.01957 0.01123 0.0076 0.3554 0.9409
6.750 0.7358 0.01991 0.01166 0.0057 0.3445 0.9550
7.000 0.7724 0.02026 0.01203 0.0036 0.3339 0.9690
7.250 0.8097 0.02063 0.01244 0.0012 0.3228 0.9829
7.500 0.8476 0.02103 0.01295 -0.0014 0.3110 0.9973
7.750 0.8641 0.02136 0.01326 0.0001 0.3028 1.0000
8.000 0.8765 0.02171 0.01364 0.0023 0.2940 1.0000
8.250 0.8905 0.02211 0.01404 0.0044 0.2858 1.0000
8.500 0.9049 0.02251 0.01447 0.0063 0.2769 1.0000
8.750 0.9198 0.02298 0.01498 0.0082 0.2678 1.0000
9.000 0.9347 0.02343 0.01540 0.0100 0.2593 1.0000
9.250 0.9490 0.02396 0.01603 0.0118 0.2493 1.0000
9.500 0.9629 0.02450 0.01658 0.0136 0.2404 1.0000
9.750 0.9758 0.02508 0.01721 0.0155 0.2310 1.0000
10.000 0.9879 0.02571 0.01791 0.0174 0.2217 1.0000
10.250 0.9980 0.02638 0.01853 0.0195 0.2133 1.0000
10.500 1.0059 0.02711 0.01938 0.0219 0.2040 1.0000
10.750 1.0119 0.02791 0.02018 0.0244 0.1962 1.0000
11.000 1.0173 0.02883 0.02118 0.0266 0.1877 1.0000
11.250 1.0224 0.02989 0.02228 0.0285 0.1797 1.0000
11.500 1.0256 0.03112 0.02354 0.0302 0.1715 1.0000
11.750 1.0289 0.03252 0.02501 0.0316 0.1631 1.0000
12.000 1.0294 0.03414 0.02662 0.0328 0.1555 1.0000
12.250 1.0308 0.03594 0.02852 0.0337 0.1467 1.0000
12.500 1.0294 0.03801 0.03058 0.0343 0.1394 1.0000
12.750 1.0284 0.04026 0.03293 0.0346 0.1314 1.0000
13.000 1.0253 0.04279 0.03547 0.0347 0.1246 1.0000
13.250 1.0221 0.04551 0.03828 0.0345 0.1177 1.0000
13.500 1.0172 0.04849 0.04127 0.0341 0.1120 1.0000
13.750 1.0129 0.05163 0.04453 0.0335 0.1059 1.0000
14.000 1.0051 0.05517 0.04806 0.0326 0.1010 1.0000
14.250 1.0003 0.05863 0.05166 0.0317 0.0956 1.0000
14.500 0.9925 0.06253 0.05562 0.0304 0.0910 1.0000
14.750 0.9851 0.06652 0.05962 0.0290 0.0869 1.0000
15.000 0.9780 0.07072 0.06396 0.0274 0.0823 1.0000
15.250 0.9695 0.07516 0.06843 0.0255 0.0785 1.0000
15.500 0.9618 0.07962 0.07294 0.0237 0.0747 1.0000
15.750 0.9538 0.08436 0.07779 0.0216 0.0707 1.0000
16.000 0.9460 0.08906 0.08252 0.0195 0.0674 1.0000
16.250 0.9397 0.09361 0.08711 0.0175 0.0643 1.0000
|
Polar data table (+)
Polar graphs
<< Back to S1046 17% (Danny Howell) (s1046-il)