S1016 (s1016-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: S1016 (s1016-il) Reynolds number: 50,000 Max Cl/Cd: 22.37 at α=8.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s1016-il-50000-n5.txt Download as CSV file: xf-s1016-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: S1016
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
------ -------- --------- --------- -------- -------- --------
-15.000 -0.5794 0.11835 0.11021 -0.0509 1.0000 0.1124
-14.750 -0.6725 0.09535 0.08720 -0.0632 1.0000 0.1153
-14.500 -0.7679 0.07831 0.06989 -0.0712 1.0000 0.1145
-14.250 -0.8124 0.07100 0.06232 -0.0727 1.0000 0.1152
-14.000 -0.8448 0.06591 0.05696 -0.0723 1.0000 0.1165
-13.750 -0.8738 0.06191 0.05265 -0.0706 1.0000 0.1180
-13.500 -0.8777 0.05995 0.05065 -0.0688 1.0000 0.1205
-13.250 -0.8776 0.05870 0.04941 -0.0667 1.0000 0.1233
-13.000 -0.8898 0.05711 0.04772 -0.0634 1.0000 0.1257
-12.750 -0.9061 0.05549 0.04594 -0.0594 1.0000 0.1281
-12.500 -0.9246 0.05386 0.04409 -0.0549 1.0000 0.1305
-12.250 -0.9445 0.05225 0.04219 -0.0501 1.0000 0.1328
-12.000 -0.9366 0.05144 0.04148 -0.0478 1.0000 0.1363
-11.750 -0.9393 0.05044 0.04041 -0.0444 1.0000 0.1398
-11.500 -0.9458 0.04925 0.03906 -0.0405 1.0000 0.1436
-11.250 -0.9549 0.04794 0.03746 -0.0363 1.0000 0.1474
-11.000 -0.9454 0.04711 0.03672 -0.0341 1.0000 0.1519
-10.750 -0.9434 0.04618 0.03572 -0.0310 1.0000 0.1567
-10.500 -0.9447 0.04510 0.03441 -0.0274 1.0000 0.1620
-10.250 -0.9357 0.04426 0.03360 -0.0251 1.0000 0.1675
-10.000 -0.9299 0.04342 0.03268 -0.0223 1.0000 0.1735
-9.750 -0.9241 0.04250 0.03160 -0.0195 1.0000 0.1803
-9.500 -0.9135 0.04178 0.03093 -0.0173 1.0000 0.1872
-9.250 -0.9075 0.04095 0.02990 -0.0145 1.0000 0.1953
-9.000 -0.8936 0.04027 0.02932 -0.0127 1.0000 0.2033
-8.750 -0.8839 0.03954 0.02847 -0.0103 1.0000 0.2128
-8.500 -0.8645 0.03885 0.02781 -0.0095 0.9987 0.2238
-8.250 -0.8435 0.03816 0.02714 -0.0090 0.9968 0.2363
-8.000 -0.8249 0.03750 0.02646 -0.0082 0.9950 0.2500
-7.750 -0.8071 0.03689 0.02584 -0.0072 0.9934 0.2647
-7.500 -0.7907 0.03627 0.02525 -0.0060 0.9915 0.2811
-7.250 -0.7748 0.03565 0.02471 -0.0047 0.9893 0.2988
-7.000 -0.7601 0.03504 0.02420 -0.0032 0.9871 0.3183
-6.750 -0.7472 0.03447 0.02375 -0.0014 0.9850 0.3401
-6.500 -0.7331 0.03393 0.02332 0.0003 0.9828 0.3659
-6.250 -0.7181 0.03345 0.02303 0.0020 0.9805 0.3956
-6.000 -0.7060 0.03301 0.02280 0.0044 0.9780 0.4285
-5.750 -0.6880 0.03280 0.02285 0.0061 0.9758 0.4687
-5.500 -0.6536 0.03324 0.02359 0.0060 0.9741 0.5171
-5.250 -0.6093 0.03442 0.02495 0.0049 0.9726 0.5626
-5.000 -0.5685 0.03581 0.02635 0.0043 0.9709 0.5973
-4.750 -0.5318 0.03712 0.02758 0.0041 0.9690 0.6243
-4.500 -0.5097 0.03793 0.02829 0.0057 0.9662 0.6488
-4.250 -0.4851 0.03887 0.02913 0.0070 0.9632 0.6687
-4.000 -0.4614 0.03968 0.02982 0.0082 0.9600 0.6889
-3.750 -0.4476 0.04014 0.03018 0.0104 0.9564 0.7116
-3.500 -0.4204 0.04095 0.03088 0.0107 0.9534 0.7290
-3.250 -0.4038 0.04148 0.03131 0.0128 0.9493 0.7456
-3.000 -0.3818 0.04206 0.03180 0.0139 0.9454 0.7618
-2.750 -0.3549 0.04263 0.03227 0.0140 0.9418 0.7772
-2.500 -0.3313 0.04310 0.03265 0.0146 0.9381 0.7924
-2.250 -0.2900 0.04366 0.03313 0.0124 0.9345 0.8024
-2.000 -0.2591 0.04400 0.03339 0.0116 0.9303 0.8144
-1.750 -0.2309 0.04427 0.03359 0.0110 0.9261 0.8273
-1.500 -0.1862 0.04457 0.03383 0.0076 0.9226 0.8359
-1.250 -0.1639 0.04464 0.03386 0.0081 0.9165 0.8466
-1.000 -0.1304 0.04479 0.03397 0.0064 0.9117 0.8565
-0.750 -0.0876 0.04491 0.03404 0.0030 0.9076 0.8640
-0.500 -0.0714 0.04491 0.03403 0.0044 0.8998 0.8739
-0.250 -0.0285 0.04494 0.03405 0.0009 0.8947 0.8802
0.000 0.0000 0.04495 0.03406 0.0000 0.8876 0.8877
0.250 0.0286 0.04494 0.03405 -0.0009 0.8801 0.8947
0.500 0.0715 0.04491 0.03403 -0.0044 0.8740 0.8998
0.750 0.0874 0.04491 0.03404 -0.0030 0.8640 0.9076
1.000 0.1302 0.04478 0.03396 -0.0064 0.8565 0.9117
1.250 0.1639 0.04464 0.03386 -0.0081 0.8466 0.9166
1.500 0.1861 0.04456 0.03382 -0.0076 0.8359 0.9226
1.750 0.2307 0.04426 0.03358 -0.0110 0.8273 0.9261
2.000 0.2592 0.04398 0.03338 -0.0116 0.8144 0.9303
2.250 0.2902 0.04365 0.03311 -0.0124 0.8025 0.9345
2.500 0.3312 0.04309 0.03264 -0.0145 0.7924 0.9381
2.750 0.3550 0.04262 0.03226 -0.0140 0.7773 0.9418
3.000 0.3817 0.04205 0.03179 -0.0139 0.7618 0.9454
3.250 0.4036 0.04148 0.03131 -0.0128 0.7457 0.9494
3.500 0.4203 0.04094 0.03086 -0.0107 0.7290 0.9535
3.750 0.4479 0.04012 0.03016 -0.0104 0.7116 0.9564
4.000 0.4615 0.03966 0.02980 -0.0082 0.6889 0.9601
4.250 0.4852 0.03886 0.02912 -0.0070 0.6688 0.9632
4.500 0.5098 0.03791 0.02827 -0.0057 0.6488 0.9663
4.750 0.5322 0.03710 0.02756 -0.0042 0.6247 0.9691
5.000 0.5687 0.03579 0.02633 -0.0044 0.5974 0.9710
5.250 0.6095 0.03441 0.02493 -0.0049 0.5627 0.9727
5.500 0.6538 0.03321 0.02357 -0.0060 0.5169 0.9741
5.750 0.6881 0.03278 0.02283 -0.0062 0.4686 0.9758
6.000 0.7062 0.03299 0.02279 -0.0044 0.4286 0.9780
6.250 0.7184 0.03343 0.02301 -0.0020 0.3957 0.9805
6.500 0.7335 0.03391 0.02330 -0.0004 0.3659 0.9828
6.750 0.7474 0.03445 0.02373 0.0013 0.3401 0.9851
7.000 0.7605 0.03503 0.02418 0.0031 0.3182 0.9871
7.250 0.7751 0.03563 0.02469 0.0047 0.2986 0.9894
7.500 0.7911 0.03625 0.02524 0.0060 0.2811 0.9916
7.750 0.8075 0.03687 0.02582 0.0072 0.2647 0.9935
8.000 0.8252 0.03749 0.02644 0.0082 0.2498 0.9951
8.250 0.8437 0.03814 0.02712 0.0090 0.2361 0.9969
8.500 0.8648 0.03883 0.02780 0.0094 0.2237 0.9987
8.750 0.8841 0.03952 0.02845 0.0102 0.2128 1.0000
9.000 0.8934 0.04025 0.02930 0.0127 0.2032 1.0000
9.250 0.9076 0.04094 0.02988 0.0145 0.1952 1.0000
9.500 0.9141 0.04176 0.03091 0.0172 0.1872 1.0000
9.750 0.9243 0.04248 0.03158 0.0195 0.1802 1.0000
10.000 0.9301 0.04340 0.03266 0.0223 0.1735 1.0000
10.250 0.9358 0.04424 0.03357 0.0251 0.1675 1.0000
10.500 0.9442 0.04507 0.03438 0.0275 0.1619 1.0000
10.750 0.9436 0.04615 0.03569 0.0310 0.1567 1.0000
11.000 0.9455 0.04707 0.03668 0.0341 0.1518 1.0000
11.250 0.9547 0.04792 0.03744 0.0363 0.1474 1.0000
11.500 0.9453 0.04921 0.03902 0.0406 0.1435 1.0000
11.750 0.9391 0.05040 0.04037 0.0444 0.1397 1.0000
12.000 0.9369 0.05140 0.04143 0.0477 0.1363 1.0000
12.250 0.9446 0.05222 0.04216 0.0501 0.1328 1.0000
12.500 0.9247 0.05382 0.04405 0.0549 0.1305 1.0000
12.750 0.9062 0.05544 0.04589 0.0594 0.1280 1.0000
13.000 0.8899 0.05705 0.04766 0.0634 0.1256 1.0000
13.250 0.8782 0.05864 0.04934 0.0667 0.1233 1.0000
13.500 0.8786 0.05990 0.05060 0.0688 0.1205 1.0000
13.750 0.8743 0.06192 0.05266 0.0705 0.1180 1.0000
14.000 0.8456 0.06592 0.05697 0.0721 0.1165 1.0000
14.250 0.8134 0.07102 0.06233 0.0725 0.1152 1.0000
14.500 0.7689 0.07835 0.06993 0.0710 0.1144 1.0000
14.750 0.6711 0.09588 0.08773 0.0627 0.1152 1.0000
15.000 0.5812 0.11833 0.11019 0.0507 0.1122 1.0000
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