S1046 17% (Danny Howell) (s1046-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: S1046 17% (Danny Howell) (s1046-il) Reynolds number: 50,000 Max Cl/Cd: 25.26 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s1046-il-50000-n5.txt Download as CSV file: xf-s1046-il-50000-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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.000 -0.7741 0.09729 0.08941 -0.0179 1.0000 0.1560
-13.750 -0.7288 0.10260 0.09460 -0.0141 1.0000 0.1600
-13.500 -0.8718 0.07414 0.06614 -0.0291 1.0000 0.1692
-13.250 -0.7606 0.08953 0.08150 -0.0196 1.0000 0.1752
-13.000 -0.8876 0.06629 0.05817 -0.0313 1.0000 0.1829
-12.750 -0.8308 0.07159 0.06352 -0.0274 1.0000 0.1910
-12.500 -0.9037 0.05908 0.05081 -0.0327 1.0000 0.1971
-12.250 -0.8792 0.05958 0.05135 -0.0314 1.0000 0.2053
-12.000 -0.9183 0.05287 0.04445 -0.0329 1.0000 0.2118
-11.750 -0.9011 0.05242 0.04402 -0.0320 1.0000 0.2201
-11.500 -0.9280 0.04791 0.03932 -0.0318 1.0000 0.2270
-11.250 -0.9114 0.04743 0.03887 -0.0307 1.0000 0.2355
-11.000 -0.9346 0.04398 0.03523 -0.0290 1.0000 0.2429
-10.750 -0.9146 0.04374 0.03505 -0.0279 1.0000 0.2516
-10.500 -0.9346 0.04114 0.03226 -0.0248 1.0000 0.2592
-10.250 -0.9126 0.04098 0.03213 -0.0236 1.0000 0.2680
-10.000 -0.9148 0.03942 0.03045 -0.0212 1.0000 0.2766
-9.750 -0.9022 0.03868 0.02967 -0.0195 1.0000 0.2857
-9.500 -0.8915 0.03775 0.02868 -0.0178 1.0000 0.2944
-9.250 -0.8871 0.03653 0.02732 -0.0156 1.0000 0.3041
-9.000 -0.8669 0.03616 0.02697 -0.0144 1.0000 0.3128
-8.750 -0.8617 0.03494 0.02560 -0.0121 1.0000 0.3224
-8.500 -0.8423 0.03456 0.02523 -0.0108 1.0000 0.3315
-8.250 -0.8303 0.03375 0.02435 -0.0090 1.0000 0.3406
-8.000 -0.8186 0.03300 0.02352 -0.0070 1.0000 0.3502
-7.750 -0.8015 0.03257 0.02310 -0.0054 1.0000 0.3588
-7.500 -0.7963 0.03158 0.02196 -0.0028 1.0000 0.3687
-7.250 -0.7766 0.03140 0.02186 -0.0013 1.0000 0.3765
-7.000 -0.7705 0.03064 0.02102 0.0014 1.0000 0.3859
-6.750 -0.7569 0.03036 0.02078 0.0036 1.0000 0.3938
-6.500 -0.7522 0.02979 0.02013 0.0066 1.0000 0.4027
-6.250 -0.7431 0.02951 0.01986 0.0093 1.0000 0.4106
-6.000 -0.7333 0.02907 0.01935 0.0113 0.9982 0.4195
-5.750 -0.6951 0.02861 0.01875 0.0083 0.9838 0.4326
-5.500 -0.6542 0.02850 0.01862 0.0057 0.9710 0.4432
-5.250 -0.6153 0.02823 0.01829 0.0031 0.9577 0.4548
-5.000 -0.5777 0.02786 0.01781 0.0007 0.9447 0.4671
-4.750 -0.5386 0.02754 0.01738 -0.0019 0.9328 0.4797
-4.500 -0.4958 0.02742 0.01726 -0.0046 0.9222 0.4903
-4.250 -0.4609 0.02718 0.01695 -0.0060 0.9088 0.5018
-4.000 -0.4285 0.02687 0.01655 -0.0072 0.8954 0.5141
-3.750 -0.3934 0.02677 0.01644 -0.0083 0.8829 0.5246
-3.500 -0.3593 0.02662 0.01624 -0.0093 0.8707 0.5355
-3.250 -0.3298 0.02639 0.01594 -0.0096 0.8577 0.5474
-3.000 -0.3021 0.02630 0.01581 -0.0094 0.8438 0.5583
-2.750 -0.2742 0.02624 0.01574 -0.0091 0.8304 0.5684
-2.500 -0.2486 0.02609 0.01553 -0.0086 0.8174 0.5802
-2.250 -0.2218 0.02600 0.01537 -0.0081 0.8052 0.5917
-2.000 -0.1947 0.02598 0.01535 -0.0074 0.7926 0.6017
-1.750 -0.1717 0.02590 0.01524 -0.0064 0.7792 0.6133
-1.500 -0.1488 0.02581 0.01510 -0.0054 0.7664 0.6256
-1.250 -0.1217 0.02584 0.01513 -0.0047 0.7546 0.6355
-1.000 -0.0968 0.02577 0.01503 -0.0038 0.7429 0.6472
-0.750 -0.0753 0.02571 0.01494 -0.0026 0.7298 0.6598
-0.500 -0.0495 0.02577 0.01501 -0.0018 0.7175 0.6704
-0.250 -0.0236 0.02573 0.01496 -0.0010 0.7064 0.6818
0.000 0.0000 0.02569 0.01491 0.0000 0.6944 0.6944
0.250 0.0236 0.02573 0.01496 0.0010 0.6818 0.7064
0.500 0.0494 0.02577 0.01501 0.0018 0.6704 0.7175
0.750 0.0753 0.02571 0.01494 0.0026 0.6599 0.7297
1.000 0.0968 0.02576 0.01502 0.0038 0.6472 0.7429
1.250 0.1217 0.02583 0.01512 0.0047 0.6355 0.7546
1.500 0.1488 0.02581 0.01509 0.0054 0.6256 0.7664
1.750 0.1717 0.02590 0.01524 0.0064 0.6133 0.7792
2.000 0.1947 0.02598 0.01535 0.0074 0.6017 0.7926
2.250 0.2218 0.02599 0.01537 0.0081 0.5917 0.8052
2.500 0.2486 0.02609 0.01553 0.0086 0.5802 0.8174
2.750 0.2741 0.02624 0.01574 0.0091 0.5685 0.8305
3.000 0.3021 0.02630 0.01580 0.0094 0.5583 0.8438
3.250 0.3298 0.02639 0.01594 0.0096 0.5474 0.8577
3.500 0.3593 0.02662 0.01624 0.0093 0.5356 0.8707
3.750 0.3934 0.02677 0.01644 0.0083 0.5247 0.8829
4.000 0.4285 0.02686 0.01655 0.0072 0.5141 0.8954
4.250 0.4610 0.02717 0.01695 0.0060 0.5018 0.9088
4.500 0.4958 0.02742 0.01726 0.0046 0.4904 0.9222
4.750 0.5385 0.02754 0.01738 0.0019 0.4797 0.9329
5.000 0.5778 0.02785 0.01780 -0.0007 0.4670 0.9448
5.250 0.6155 0.02822 0.01828 -0.0031 0.4547 0.9578
5.500 0.6543 0.02850 0.01862 -0.0057 0.4431 0.9710
5.750 0.6952 0.02860 0.01874 -0.0083 0.4326 0.9838
6.000 0.7334 0.02907 0.01935 -0.0114 0.4195 0.9983
6.250 0.7430 0.02951 0.01986 -0.0092 0.4106 1.0000
6.500 0.7521 0.02978 0.02013 -0.0066 0.4026 1.0000
6.750 0.7568 0.03036 0.02078 -0.0036 0.3938 1.0000
7.000 0.7704 0.03064 0.02101 -0.0014 0.3859 1.0000
7.250 0.7766 0.03140 0.02186 0.0013 0.3766 1.0000
7.500 0.7963 0.03157 0.02195 0.0028 0.3687 1.0000
7.750 0.8015 0.03256 0.02309 0.0054 0.3588 1.0000
8.000 0.8186 0.03300 0.02352 0.0070 0.3502 1.0000
8.250 0.8303 0.03375 0.02435 0.0090 0.3406 1.0000
8.500 0.8424 0.03456 0.02522 0.0108 0.3315 1.0000
8.750 0.8619 0.03494 0.02559 0.0121 0.3224 1.0000
9.000 0.8671 0.03615 0.02696 0.0144 0.3128 1.0000
9.250 0.8873 0.03653 0.02731 0.0155 0.3041 1.0000
9.500 0.8917 0.03776 0.02869 0.0178 0.2944 1.0000
9.750 0.9025 0.03868 0.02967 0.0195 0.2856 1.0000
10.000 0.9152 0.03940 0.03043 0.0211 0.2765 1.0000
10.250 0.9131 0.04097 0.03213 0.0236 0.2680 1.0000
10.500 0.9354 0.04113 0.03225 0.0247 0.2592 1.0000
10.750 0.9153 0.04373 0.03504 0.0278 0.2515 1.0000
11.000 0.9347 0.04400 0.03526 0.0290 0.2428 1.0000
11.250 0.9123 0.04740 0.03885 0.0306 0.2355 1.0000
11.500 0.9287 0.04789 0.03931 0.0317 0.2270 1.0000
11.750 0.9025 0.05234 0.04395 0.0319 0.2199 1.0000
12.000 0.9184 0.05292 0.04450 0.0328 0.2117 1.0000
12.250 0.8814 0.05940 0.05116 0.0314 0.2051 1.0000
12.500 0.9037 0.05917 0.05090 0.0325 0.1969 1.0000
12.750 0.8338 0.07128 0.06321 0.0275 0.1909 1.0000
13.000 0.8877 0.06641 0.05830 0.0311 0.1829 1.0000
13.250 0.7630 0.08930 0.08129 0.0195 0.1752 1.0000
13.500 0.8709 0.07443 0.06643 0.0287 0.1691 1.0000
13.750 0.7309 0.10244 0.09444 0.0140 0.1600 1.0000
14.000 0.7810 0.09619 0.08831 0.0183 0.1559 1.0000
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