S1010 HPV airfoil (s1010-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: S1010 HPV airfoil (s1010-il) Reynolds number: 1,000,000 Max Cl/Cd: 66.31 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s1010-il-1000000.txt Download as CSV file: xf-s1010-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: S1010 HPV airfoil
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
------ -------- --------- --------- -------- -------- --------
-11.250 -0.9927 0.04542 0.04355 -0.0209 1.0000 0.0048
-11.000 -1.0265 0.03903 0.03682 -0.0196 1.0000 0.0047
-10.750 -1.0229 0.03626 0.03385 -0.0188 1.0000 0.0048
-10.500 -1.0266 0.03199 0.02921 -0.0174 1.0000 0.0048
-10.250 -1.0187 0.02916 0.02609 -0.0162 1.0000 0.0049
-10.000 -1.0058 0.02694 0.02362 -0.0152 1.0000 0.0050
-9.750 -0.9917 0.02474 0.02115 -0.0141 1.0000 0.0051
-9.500 -0.9745 0.02299 0.01916 -0.0131 1.0000 0.0052
-9.250 -0.9552 0.02156 0.01752 -0.0122 1.0000 0.0053
-9.000 -0.9349 0.02025 0.01601 -0.0114 1.0000 0.0054
-8.750 -0.9214 0.01725 0.01258 -0.0098 1.0000 0.0056
-8.500 -0.9013 0.01577 0.01092 -0.0088 1.0000 0.0062
-8.250 -0.8773 0.01515 0.01024 -0.0083 1.0000 0.0066
-8.000 -0.8529 0.01462 0.00965 -0.0078 1.0000 0.0072
-7.750 -0.8286 0.01401 0.00895 -0.0072 1.0000 0.0078
-7.500 -0.8040 0.01347 0.00833 -0.0067 1.0000 0.0083
-7.250 -0.7818 0.01232 0.00700 -0.0057 1.0000 0.0094
-7.000 -0.7575 0.01174 0.00637 -0.0051 1.0000 0.0107
-6.750 -0.7324 0.01135 0.00594 -0.0046 1.0000 0.0120
-6.500 -0.7070 0.01107 0.00562 -0.0041 1.0000 0.0129
-6.250 -0.6836 0.01032 0.00477 -0.0032 1.0000 0.0151
-6.000 -0.6589 0.00994 0.00438 -0.0026 1.0000 0.0172
-5.750 -0.6340 0.00967 0.00407 -0.0020 1.0000 0.0190
-5.500 -0.6098 0.00927 0.00361 -0.0012 1.0000 0.0213
-5.250 -0.5858 0.00888 0.00325 -0.0004 1.0000 0.0266
-5.000 -0.5617 0.00852 0.00293 0.0004 1.0000 0.0353
-4.750 -0.5377 0.00824 0.00269 0.0012 1.0000 0.0459
-4.500 -0.5135 0.00803 0.00249 0.0020 1.0000 0.0537
-4.250 -0.4896 0.00782 0.00230 0.0028 1.0000 0.0618
-4.000 -0.4659 0.00761 0.00212 0.0037 1.0000 0.0706
-3.750 -0.4424 0.00744 0.00197 0.0046 1.0000 0.0795
-3.500 -0.4192 0.00727 0.00184 0.0056 1.0000 0.0900
-3.250 -0.3964 0.00711 0.00172 0.0066 1.0000 0.1030
-3.000 -0.3718 0.00695 0.00162 0.0072 0.9997 0.1176
-2.750 -0.3380 0.00676 0.00152 0.0058 0.9979 0.1377
-2.500 -0.3006 0.00658 0.00143 0.0037 0.9953 0.1599
-2.250 -0.2578 0.00633 0.00131 0.0005 0.9900 0.1913
-2.000 -0.2131 0.00605 0.00118 -0.0032 0.9840 0.2319
-1.750 -0.1797 0.00578 0.00109 -0.0044 0.9756 0.2808
-1.500 -0.1479 0.00541 0.00099 -0.0054 0.9668 0.3581
-1.250 -0.1197 0.00499 0.00090 -0.0055 0.9554 0.4576
-1.000 -0.0955 0.00444 0.00081 -0.0047 0.9413 0.5959
-0.750 -0.0735 0.00393 0.00078 -0.0033 0.9255 0.7414
-0.500 -0.0497 0.00376 0.00079 -0.0021 0.9080 0.8078
-0.250 -0.0248 0.00371 0.00079 -0.0010 0.8898 0.8424
0.000 0.0000 0.00369 0.00079 0.0000 0.8690 0.8690
0.250 0.0249 0.00371 0.00079 0.0010 0.8424 0.8898
0.500 0.0498 0.00376 0.00079 0.0021 0.8082 0.9084
0.750 0.0735 0.00393 0.00078 0.0033 0.7411 0.9256
1.000 0.0955 0.00444 0.00081 0.0047 0.5950 0.9413
1.250 0.1198 0.00499 0.00090 0.0055 0.4571 0.9553
1.500 0.1480 0.00540 0.00099 0.0053 0.3599 0.9668
1.750 0.1798 0.00578 0.00109 0.0044 0.2808 0.9757
2.000 0.2131 0.00605 0.00118 0.0032 0.2319 0.9840
2.250 0.2579 0.00633 0.00131 -0.0005 0.1913 0.9900
2.500 0.3008 0.00658 0.00143 -0.0038 0.1600 0.9953
2.750 0.3381 0.00676 0.00152 -0.0059 0.1378 0.9979
3.000 0.3719 0.00695 0.00162 -0.0073 0.1174 0.9997
3.250 0.3964 0.00711 0.00172 -0.0066 0.1033 1.0000
3.500 0.4192 0.00727 0.00184 -0.0056 0.0902 1.0000
3.750 0.4424 0.00744 0.00197 -0.0046 0.0795 1.0000
4.000 0.4659 0.00761 0.00212 -0.0037 0.0707 1.0000
4.250 0.4896 0.00782 0.00230 -0.0028 0.0618 1.0000
4.500 0.5135 0.00803 0.00249 -0.0020 0.0537 1.0000
4.750 0.5377 0.00824 0.00269 -0.0012 0.0460 1.0000
5.000 0.5618 0.00852 0.00293 -0.0004 0.0353 1.0000
5.250 0.5858 0.00888 0.00325 0.0004 0.0265 1.0000
5.500 0.6099 0.00927 0.00361 0.0012 0.0214 1.0000
5.750 0.6341 0.00967 0.00407 0.0020 0.0190 1.0000
6.000 0.6591 0.00994 0.00438 0.0026 0.0173 1.0000
6.250 0.6837 0.01032 0.00477 0.0032 0.0151 1.0000
6.500 0.7071 0.01107 0.00562 0.0041 0.0129 1.0000
6.750 0.7325 0.01136 0.00595 0.0046 0.0120 1.0000
7.000 0.7576 0.01173 0.00636 0.0051 0.0107 1.0000
7.250 0.7819 0.01232 0.00700 0.0057 0.0094 1.0000
7.500 0.8037 0.01355 0.00841 0.0067 0.0084 1.0000
7.750 0.8287 0.01399 0.00893 0.0072 0.0078 1.0000
8.000 0.8529 0.01464 0.00967 0.0078 0.0073 1.0000
8.250 0.8774 0.01516 0.01025 0.0083 0.0066 1.0000
8.500 0.9014 0.01575 0.01090 0.0088 0.0062 1.0000
8.750 0.9218 0.01717 0.01250 0.0097 0.0057 1.0000
9.000 0.9350 0.02025 0.01600 0.0114 0.0054 1.0000
9.250 0.9555 0.02151 0.01747 0.0122 0.0053 1.0000
9.500 0.9752 0.02286 0.01901 0.0130 0.0052 1.0000
9.750 0.9916 0.02477 0.02117 0.0141 0.0051 1.0000
10.000 1.0069 0.02676 0.02341 0.0151 0.0050 1.0000
10.250 1.0184 0.02924 0.02617 0.0163 0.0049 1.0000
10.500 1.0268 0.03199 0.02921 0.0174 0.0048 1.0000
10.750 1.0236 0.03619 0.03377 0.0188 0.0048 1.0000
11.000 1.0146 0.04068 0.03857 0.0197 0.0048 1.0000
11.250 0.9919 0.04557 0.04370 0.0208 0.0048 1.0000
11.750 0.8393 0.08870 0.08709 -0.0099 0.0054 1.0000
12.000 0.8296 0.09517 0.09356 -0.0133 0.0055 1.0000
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Polar data table (+)
Polar graphs
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