S1048 14% (Danny Howell) (s1048-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: S1048 14% (Danny Howell) (s1048-il) Reynolds number: 1,000,000 Max Cl/Cd: 83.87 at α=6.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s1048-il-1000000.txt Download as CSV file: xf-s1048-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: S1048 14% (Danny Howell)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-17.000 -1.1134 0.08175 0.07812 -0.0154 1.0000 0.0055
-16.750 -1.1237 0.07651 0.07280 -0.0178 1.0000 0.0056
-16.500 -1.1344 0.07133 0.06751 -0.0202 1.0000 0.0057
-16.250 -1.1378 0.06728 0.06339 -0.0220 1.0000 0.0057
-16.000 -1.1504 0.06216 0.05816 -0.0241 1.0000 0.0057
-15.750 -1.1586 0.05775 0.05365 -0.0259 1.0000 0.0057
-15.500 -1.1644 0.05381 0.04963 -0.0274 1.0000 0.0059
-15.250 -1.1719 0.04978 0.04550 -0.0288 1.0000 0.0059
-15.000 -1.1758 0.04630 0.04194 -0.0299 1.0000 0.0060
-14.750 -1.1810 0.04278 0.03831 -0.0309 1.0000 0.0060
-14.500 -1.1803 0.04000 0.03547 -0.0316 1.0000 0.0062
-14.250 -1.1820 0.03709 0.03246 -0.0321 1.0000 0.0062
-14.000 -1.1817 0.03449 0.02978 -0.0324 1.0000 0.0064
-13.750 -1.1796 0.03220 0.02741 -0.0324 1.0000 0.0066
-13.500 -1.1777 0.03002 0.02514 -0.0322 1.0000 0.0067
-13.250 -1.1777 0.02784 0.02285 -0.0316 1.0000 0.0066
-13.000 -1.1706 0.02638 0.02132 -0.0309 1.0000 0.0069
-12.750 -1.1643 0.02498 0.01985 -0.0299 1.0000 0.0071
-12.500 -1.1598 0.02359 0.01838 -0.0284 1.0000 0.0071
-12.250 -1.1554 0.02236 0.01706 -0.0265 1.0000 0.0072
-12.000 -1.1546 0.02107 0.01568 -0.0239 1.0000 0.0074
-11.750 -1.1539 0.01993 0.01447 -0.0206 1.0000 0.0078
-11.500 -1.1477 0.01915 0.01364 -0.0176 1.0000 0.0081
-11.250 -1.1364 0.01850 0.01294 -0.0153 1.0000 0.0085
-11.000 -1.1216 0.01787 0.01226 -0.0136 1.0000 0.0089
-10.750 -1.1050 0.01730 0.01165 -0.0121 1.0000 0.0094
-10.500 -1.0871 0.01679 0.01108 -0.0107 1.0000 0.0097
-10.250 -1.0725 0.01600 0.01024 -0.0088 1.0000 0.0107
-10.000 -1.0544 0.01545 0.00966 -0.0074 1.0000 0.0116
-9.750 -1.0348 0.01500 0.00917 -0.0062 1.0000 0.0127
-9.500 -1.0167 0.01443 0.00858 -0.0047 1.0000 0.0144
-9.250 -0.9976 0.01394 0.00809 -0.0033 1.0000 0.0162
-9.000 -0.9788 0.01345 0.00758 -0.0019 1.0000 0.0192
-8.750 -0.9597 0.01298 0.00711 -0.0004 1.0000 0.0232
-8.500 -0.9414 0.01245 0.00663 0.0011 1.0000 0.0304
-8.250 -0.9237 0.01191 0.00617 0.0028 1.0000 0.0421
-8.000 -0.9053 0.01143 0.00577 0.0044 1.0000 0.0550
-7.750 -0.8833 0.01091 0.00535 0.0051 0.9993 0.0719
-7.500 -0.8478 0.01035 0.00492 0.0030 0.9954 0.0949
-7.250 -0.8139 0.00981 0.00452 0.0013 0.9899 0.1207
-7.000 -0.7789 0.00932 0.00416 -0.0006 0.9831 0.1472
-6.750 -0.7456 0.00889 0.00384 -0.0021 0.9714 0.1732
-6.500 -0.7104 0.00847 0.00354 -0.0039 0.9564 0.2013
-6.250 -0.6785 0.00816 0.00328 -0.0048 0.9328 0.2224
-6.000 -0.6529 0.00795 0.00307 -0.0044 0.9047 0.2433
-5.750 -0.6287 0.00777 0.00287 -0.0036 0.8786 0.2639
-5.500 -0.6037 0.00761 0.00270 -0.0030 0.8555 0.2821
-5.250 -0.5780 0.00750 0.00255 -0.0025 0.8349 0.2978
-5.000 -0.5518 0.00739 0.00241 -0.0021 0.8162 0.3111
-4.750 -0.5254 0.00728 0.00228 -0.0018 0.7986 0.3265
-4.500 -0.4987 0.00719 0.00216 -0.0015 0.7822 0.3403
-4.250 -0.4716 0.00711 0.00205 -0.0013 0.7667 0.3526
-4.000 -0.4444 0.00704 0.00195 -0.0012 0.7523 0.3647
-3.750 -0.4171 0.00697 0.00185 -0.0010 0.7384 0.3767
-3.500 -0.3898 0.00690 0.00176 -0.0008 0.7251 0.3885
-3.000 -0.3346 0.00678 0.00161 -0.0006 0.6991 0.4117
-2.750 -0.3068 0.00674 0.00154 -0.0006 0.6866 0.4233
-2.500 -0.2791 0.00668 0.00148 -0.0005 0.6745 0.4346
-2.250 -0.2514 0.00663 0.00142 -0.0004 0.6623 0.4456
-2.000 -0.2236 0.00660 0.00137 -0.0003 0.6501 0.4568
-1.750 -0.1955 0.00657 0.00132 -0.0003 0.6375 0.4683
-1.500 -0.1677 0.00653 0.00128 -0.0003 0.6252 0.4800
-1.250 -0.1398 0.00650 0.00125 -0.0002 0.6128 0.4915
-1.000 -0.1118 0.00648 0.00122 -0.0002 0.6004 0.5031
-0.750 -0.0839 0.00648 0.00120 -0.0001 0.5881 0.5149
-0.500 -0.0560 0.00646 0.00118 -0.0001 0.5755 0.5270
-0.250 -0.0280 0.00644 0.00118 0.0000 0.5631 0.5392
0.000 0.0000 0.00644 0.00117 0.0000 0.5512 0.5510
0.250 0.0280 0.00644 0.00118 0.0000 0.5391 0.5633
0.500 0.0560 0.00646 0.00118 0.0001 0.5272 0.5755
0.750 0.0839 0.00647 0.00120 0.0001 0.5151 0.5880
1.000 0.1118 0.00648 0.00122 0.0002 0.5032 0.6004
1.250 0.1398 0.00650 0.00125 0.0002 0.4915 0.6128
1.500 0.1677 0.00653 0.00128 0.0003 0.4800 0.6252
1.750 0.1955 0.00657 0.00132 0.0003 0.4682 0.6375
2.000 0.2236 0.00660 0.00137 0.0003 0.4568 0.6500
2.250 0.2514 0.00663 0.00142 0.0004 0.4457 0.6623
2.500 0.2791 0.00668 0.00148 0.0005 0.4347 0.6745
2.750 0.3068 0.00673 0.00154 0.0006 0.4232 0.6866
3.000 0.3346 0.00678 0.00161 0.0006 0.4117 0.6991
3.500 0.3898 0.00690 0.00176 0.0008 0.3884 0.7250
3.750 0.4171 0.00697 0.00185 0.0010 0.3768 0.7384
4.000 0.4443 0.00704 0.00195 0.0012 0.3646 0.7524
4.250 0.4716 0.00711 0.00205 0.0013 0.3524 0.7668
4.500 0.4987 0.00719 0.00216 0.0015 0.3401 0.7822
4.750 0.5254 0.00728 0.00228 0.0018 0.3264 0.7986
5.000 0.5518 0.00739 0.00241 0.0021 0.3110 0.8161
5.250 0.5780 0.00750 0.00255 0.0025 0.2978 0.8349
5.500 0.6036 0.00761 0.00270 0.0030 0.2823 0.8556
5.750 0.6287 0.00776 0.00287 0.0036 0.2646 0.8787
6.000 0.6529 0.00795 0.00307 0.0044 0.2433 0.9047
6.250 0.6785 0.00816 0.00328 0.0048 0.2223 0.9326
6.500 0.7104 0.00847 0.00354 0.0039 0.2005 0.9564
7.000 0.7788 0.00933 0.00416 0.0006 0.1466 0.9831
7.250 0.8137 0.00982 0.00452 -0.0013 0.1203 0.9899
7.500 0.8477 0.01036 0.00492 -0.0030 0.0947 0.9954
7.750 0.8832 0.01091 0.00535 -0.0051 0.0719 0.9992
8.000 0.9054 0.01143 0.00577 -0.0044 0.0551 1.0000
8.250 0.9237 0.01191 0.00617 -0.0028 0.0421 1.0000
8.500 0.9415 0.01245 0.00663 -0.0011 0.0306 1.0000
8.750 0.9596 0.01299 0.00712 0.0004 0.0230 1.0000
9.000 0.9787 0.01345 0.00758 0.0019 0.0192 1.0000
9.250 0.9976 0.01394 0.00809 0.0034 0.0163 1.0000
9.500 1.0167 0.01443 0.00858 0.0047 0.0144 1.0000
9.750 1.0348 0.01499 0.00917 0.0062 0.0127 1.0000
10.000 1.0545 0.01544 0.00965 0.0074 0.0117 1.0000
10.250 1.0722 0.01602 0.01025 0.0089 0.0106 1.0000
10.500 1.0871 0.01678 0.01107 0.0107 0.0097 1.0000
10.750 1.1052 0.01728 0.01163 0.0120 0.0092 1.0000
11.000 1.1218 0.01785 0.01224 0.0136 0.0088 1.0000
11.250 1.1366 0.01849 0.01292 0.0153 0.0084 1.0000
11.500 1.1487 0.01911 0.01359 0.0175 0.0081 1.0000
11.750 1.1540 0.01993 0.01446 0.0206 0.0078 1.0000
12.000 1.1558 0.02101 0.01562 0.0237 0.0075 1.0000
12.250 1.1544 0.02241 0.01712 0.0266 0.0073 1.0000
12.500 1.1615 0.02350 0.01827 0.0283 0.0071 1.0000
12.750 1.1659 0.02488 0.01975 0.0298 0.0071 1.0000
13.000 1.1721 0.02628 0.02122 0.0308 0.0069 1.0000
13.250 1.1754 0.02805 0.02308 0.0316 0.0068 1.0000
13.500 1.1835 0.02954 0.02463 0.0321 0.0065 1.0000
13.750 1.1805 0.03215 0.02736 0.0323 0.0066 1.0000
14.000 1.1825 0.03445 0.02973 0.0323 0.0064 1.0000
14.250 1.1826 0.03707 0.03244 0.0320 0.0063 1.0000
14.500 1.1793 0.04017 0.03564 0.0315 0.0062 1.0000
14.750 1.1775 0.04323 0.03879 0.0307 0.0062 1.0000
15.000 1.1779 0.04613 0.04176 0.0299 0.0060 1.0000
15.250 1.1721 0.04984 0.04556 0.0287 0.0059 1.0000
15.500 1.1677 0.05349 0.04930 0.0274 0.0058 1.0000
15.750 1.1580 0.05790 0.05382 0.0258 0.0058 1.0000
16.000 1.1514 0.06212 0.05812 0.0240 0.0057 1.0000
16.250 1.1416 0.06689 0.06298 0.0220 0.0056 1.0000
16.500 1.1336 0.07158 0.06775 0.0199 0.0055 1.0000
16.750 1.1226 0.07677 0.07307 0.0175 0.0056 1.0000
17.000 1.1083 0.08263 0.07901 0.0148 0.0055 1.0000
17.250 1.0932 0.08877 0.08526 0.0119 0.0053 1.0000
|
Polar data table (+)
Polar graphs
<< Back to S1048 14% (Danny Howell) (s1048-il)