S1046 17% (Danny Howell) (s1046-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: S1046 17% (Danny Howell) (s1046-il) Reynolds number: 200,000 Max Cl/Cd: 54.59 at α=8.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s1046-il-200000-n5.txt Download as CSV file: xf-s1046-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-17.500 -0.9942 0.10207 0.09653 -0.0117 1.0000 0.0282
-17.250 -1.0035 0.09678 0.09117 -0.0143 1.0000 0.0291
-17.000 -1.0121 0.09171 0.08601 -0.0166 1.0000 0.0302
-16.750 -1.0196 0.08693 0.08113 -0.0188 1.0000 0.0317
-16.500 -1.0260 0.08240 0.07650 -0.0207 1.0000 0.0330
-16.250 -1.0363 0.07739 0.07142 -0.0229 1.0000 0.0343
-16.000 -1.0452 0.07272 0.06668 -0.0249 1.0000 0.0360
-15.750 -1.0516 0.06851 0.06238 -0.0265 1.0000 0.0379
-15.500 -1.0576 0.06447 0.05823 -0.0280 1.0000 0.0401
-15.250 -1.0662 0.06023 0.05393 -0.0295 1.0000 0.0422
-15.000 -1.0719 0.05647 0.05010 -0.0307 1.0000 0.0450
-14.750 -1.0756 0.05311 0.04664 -0.0317 1.0000 0.0478
-14.500 -1.0827 0.04949 0.04299 -0.0326 1.0000 0.0510
-14.250 -1.0852 0.04652 0.03994 -0.0331 1.0000 0.0547
-14.000 -1.0891 0.04349 0.03686 -0.0336 1.0000 0.0584
-13.750 -1.0912 0.04075 0.03408 -0.0338 1.0000 0.0630
-13.500 -1.0918 0.03826 0.03154 -0.0338 1.0000 0.0676
-13.250 -1.0922 0.03588 0.02912 -0.0337 1.0000 0.0726
-13.000 -1.0903 0.03381 0.02700 -0.0333 1.0000 0.0781
-12.750 -1.0890 0.03178 0.02495 -0.0328 1.0000 0.0838
-12.500 -1.0850 0.03006 0.02317 -0.0321 1.0000 0.0899
-12.250 -1.0820 0.02837 0.02146 -0.0312 1.0000 0.0967
-12.000 -1.0771 0.02691 0.01998 -0.0301 1.0000 0.1034
-11.750 -1.0717 0.02559 0.01864 -0.0288 1.0000 0.1110
-11.500 -1.0660 0.02439 0.01743 -0.0273 1.0000 0.1183
-11.250 -1.0578 0.02341 0.01641 -0.0256 1.0000 0.1266
-11.000 -1.0521 0.02241 0.01544 -0.0236 1.0000 0.1349
-10.750 -1.0447 0.02159 0.01461 -0.0213 1.0000 0.1446
-10.250 -1.0297 0.02023 0.01328 -0.0161 1.0000 0.1653
-10.000 -1.0189 0.01963 0.01271 -0.0139 1.0000 0.1756
-9.750 -1.0048 0.01912 0.01218 -0.0120 1.0000 0.1853
-9.500 -0.9909 0.01862 0.01169 -0.0101 1.0000 0.1945
-9.250 -0.9759 0.01816 0.01122 -0.0082 1.0000 0.2031
-9.000 -0.9599 0.01777 0.01081 -0.0065 1.0000 0.2124
-8.750 -0.9458 0.01736 0.01042 -0.0044 1.0000 0.2208
-8.500 -0.9285 0.01701 0.01006 -0.0029 0.9986 0.2302
-8.250 -0.8929 0.01657 0.00959 -0.0050 0.9828 0.2423
-8.000 -0.8589 0.01615 0.00917 -0.0068 0.9638 0.2536
-7.750 -0.8235 0.01578 0.00876 -0.0087 0.9451 0.2643
-7.500 -0.7882 0.01546 0.00836 -0.0104 0.9264 0.2751
-7.250 -0.7563 0.01513 0.00801 -0.0115 0.9070 0.2847
-7.000 -0.7275 0.01487 0.00768 -0.0118 0.8875 0.2939
-6.750 -0.7012 0.01465 0.00738 -0.0115 0.8689 0.3033
-6.500 -0.6765 0.01443 0.00711 -0.0109 0.8518 0.3119
-6.250 -0.6516 0.01427 0.00684 -0.0103 0.8362 0.3210
-6.000 -0.6277 0.01407 0.00661 -0.0096 0.8216 0.3294
-5.750 -0.6029 0.01392 0.00636 -0.0089 0.8080 0.3382
-5.500 -0.5785 0.01374 0.00616 -0.0083 0.7949 0.3469
-5.250 -0.5534 0.01360 0.00595 -0.0077 0.7826 0.3556
-5.000 -0.5284 0.01345 0.00575 -0.0071 0.7712 0.3645
-4.750 -0.5031 0.01332 0.00556 -0.0066 0.7598 0.3732
-4.500 -0.4774 0.01319 0.00539 -0.0061 0.7486 0.3827
-4.250 -0.4519 0.01306 0.00523 -0.0056 0.7381 0.3913
-4.000 -0.4258 0.01296 0.00506 -0.0052 0.7275 0.4009
-3.750 -0.4000 0.01283 0.00494 -0.0048 0.7169 0.4101
-3.500 -0.3738 0.01274 0.00479 -0.0044 0.7072 0.4196
-3.250 -0.3475 0.01264 0.00467 -0.0040 0.6965 0.4294
-3.000 -0.3212 0.01254 0.00456 -0.0036 0.6866 0.4387
-2.750 -0.2946 0.01248 0.00443 -0.0033 0.6766 0.4488
-2.500 -0.2682 0.01238 0.00436 -0.0030 0.6660 0.4583
-2.250 -0.2415 0.01231 0.00426 -0.0026 0.6562 0.4681
-2.000 -0.2148 0.01225 0.00418 -0.0023 0.6456 0.4786
-1.750 -0.1881 0.01218 0.00412 -0.0020 0.6352 0.4882
-1.500 -0.1613 0.01214 0.00404 -0.0017 0.6250 0.4985
-1.250 -0.1345 0.01208 0.00400 -0.0014 0.6141 0.5088
-1.000 -0.1076 0.01204 0.00396 -0.0011 0.6035 0.5189
-0.750 -0.0807 0.01203 0.00390 -0.0009 0.5933 0.5296
-0.500 -0.0539 0.01199 0.00389 -0.0006 0.5822 0.5400
-0.250 -0.0269 0.01197 0.00388 -0.0003 0.5717 0.5503
0.250 0.0269 0.01197 0.00388 0.0003 0.5503 0.5717
0.500 0.0539 0.01199 0.00389 0.0006 0.5400 0.5822
0.750 0.0807 0.01203 0.00390 0.0009 0.5296 0.5933
1.000 0.1076 0.01204 0.00396 0.0012 0.5188 0.6036
1.250 0.1345 0.01208 0.00400 0.0014 0.5088 0.6142
1.500 0.1613 0.01214 0.00404 0.0017 0.4985 0.6251
1.750 0.1881 0.01218 0.00412 0.0020 0.4882 0.6352
2.000 0.2148 0.01225 0.00418 0.0023 0.4785 0.6456
2.250 0.2416 0.01231 0.00426 0.0026 0.4682 0.6562
2.500 0.2682 0.01238 0.00436 0.0030 0.4583 0.6660
2.750 0.2946 0.01248 0.00443 0.0033 0.4488 0.6766
3.000 0.3212 0.01254 0.00456 0.0036 0.4387 0.6865
3.250 0.3475 0.01264 0.00467 0.0040 0.4294 0.6965
3.500 0.3738 0.01274 0.00479 0.0044 0.4196 0.7072
3.750 0.4000 0.01283 0.00493 0.0048 0.4100 0.7170
4.000 0.4258 0.01296 0.00506 0.0052 0.4010 0.7276
4.250 0.4519 0.01306 0.00523 0.0056 0.3914 0.7380
4.500 0.4774 0.01319 0.00539 0.0061 0.3826 0.7486
4.750 0.5031 0.01332 0.00556 0.0066 0.3732 0.7598
5.000 0.5284 0.01345 0.00575 0.0071 0.3645 0.7711
5.250 0.5534 0.01360 0.00595 0.0077 0.3556 0.7826
5.500 0.5785 0.01374 0.00616 0.0082 0.3469 0.7949
5.750 0.6030 0.01392 0.00637 0.0089 0.3383 0.8080
6.000 0.6277 0.01407 0.00661 0.0096 0.3295 0.8217
6.250 0.6516 0.01427 0.00684 0.0103 0.3210 0.8362
6.500 0.6765 0.01443 0.00711 0.0109 0.3118 0.8518
6.750 0.7013 0.01465 0.00738 0.0115 0.3032 0.8689
7.000 0.7276 0.01487 0.00768 0.0117 0.2940 0.8875
7.250 0.7563 0.01513 0.00800 0.0115 0.2847 0.9070
7.500 0.7883 0.01546 0.00836 0.0104 0.2750 0.9265
7.750 0.8236 0.01578 0.00876 0.0087 0.2643 0.9450
8.000 0.8590 0.01615 0.00917 0.0068 0.2536 0.9639
8.250 0.8931 0.01657 0.00959 0.0050 0.2423 0.9829
8.500 0.9286 0.01701 0.01006 0.0028 0.2302 0.9987
8.750 0.9458 0.01736 0.01042 0.0044 0.2209 1.0000
9.000 0.9600 0.01777 0.01080 0.0064 0.2124 1.0000
9.250 0.9760 0.01816 0.01122 0.0082 0.2031 1.0000
9.500 0.9910 0.01862 0.01169 0.0101 0.1945 1.0000
9.750 1.0049 0.01912 0.01218 0.0120 0.1853 1.0000
10.000 1.0192 0.01963 0.01271 0.0138 0.1756 1.0000
10.250 1.0300 0.02023 0.01328 0.0161 0.1652 1.0000
10.500 1.0363 0.02091 0.01392 0.0189 0.1549 1.0000
10.750 1.0450 0.02159 0.01461 0.0213 0.1444 1.0000
11.000 1.0525 0.02241 0.01544 0.0235 0.1348 1.0000
11.250 1.0583 0.02340 0.01641 0.0256 0.1264 1.0000
11.500 1.0664 0.02439 0.01742 0.0272 0.1180 1.0000
11.750 1.0721 0.02559 0.01863 0.0287 0.1106 1.0000
12.000 1.0774 0.02692 0.01998 0.0300 0.1031 1.0000
12.250 1.0827 0.02835 0.02145 0.0311 0.0965 1.0000
12.500 1.0859 0.03003 0.02315 0.0320 0.0900 1.0000
12.750 1.0900 0.03175 0.02492 0.0327 0.0839 1.0000
13.000 1.0910 0.03381 0.02700 0.0332 0.0779 1.0000
13.250 1.0933 0.03585 0.02909 0.0335 0.0726 1.0000
13.500 1.0927 0.03825 0.03152 0.0337 0.0675 1.0000
13.750 1.0923 0.04072 0.03405 0.0337 0.0628 1.0000
14.000 1.0902 0.04347 0.03684 0.0334 0.0583 1.0000
14.250 1.0867 0.04646 0.03988 0.0330 0.0546 1.0000
14.500 1.0840 0.04947 0.04296 0.0324 0.0508 1.0000
14.750 1.0774 0.05302 0.04655 0.0315 0.0479 1.0000
15.000 1.0733 0.05644 0.05006 0.0306 0.0447 1.0000
15.250 1.0675 0.06020 0.05389 0.0294 0.0420 1.0000
15.500 1.0591 0.06443 0.05818 0.0278 0.0400 1.0000
15.750 1.0534 0.06843 0.06227 0.0263 0.0377 1.0000
16.000 1.0468 0.07267 0.06663 0.0247 0.0358 1.0000
16.250 1.0381 0.07732 0.07134 0.0227 0.0342 1.0000
16.750 1.0216 0.08685 0.08105 0.0186 0.0315 1.0000
17.000 1.0141 0.09164 0.08593 0.0164 0.0301 1.0000
17.250 1.0052 0.09675 0.09112 0.0140 0.0289 1.0000
17.500 0.9950 0.10221 0.09665 0.0114 0.0279 1.0000
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Polar data table (+)
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