SIKORSKY SC1095 AIRFOIL (sc1095-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: SIKORSKY SC1095 AIRFOIL (sc1095-il) Reynolds number: 50,000 Max Cl/Cd: 26.55 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sc1095-il-50000-n5.txt Download as CSV file: xf-sc1095-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: SIKORSKY SC1095 AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-10.000 -0.6693 0.09579 0.08882 -0.0018 1.0000 0.0761
-9.750 -0.6813 0.08823 0.08131 -0.0074 1.0000 0.0765
-9.500 -0.7020 0.07910 0.07221 -0.0151 1.0000 0.0759
-9.250 -0.7249 0.07180 0.06484 -0.0193 1.0000 0.0757
-9.000 -0.7404 0.06534 0.05817 -0.0219 1.0000 0.0763
-8.750 -0.7500 0.05935 0.05184 -0.0233 1.0000 0.0774
-8.500 -0.7551 0.05360 0.04555 -0.0240 1.0000 0.0797
-8.250 -0.7503 0.04926 0.04073 -0.0239 1.0000 0.0829
-8.000 -0.7332 0.04725 0.03861 -0.0234 1.0000 0.0863
-7.750 -0.7195 0.04394 0.03488 -0.0229 1.0000 0.0895
-7.500 -0.7057 0.04044 0.03062 -0.0224 1.0000 0.0945
-7.250 -0.6855 0.03855 0.02865 -0.0219 1.0000 0.0989
-7.000 -0.6649 0.03642 0.02622 -0.0213 1.0000 0.1035
-6.750 -0.6438 0.03398 0.02312 -0.0207 1.0000 0.1094
-6.500 -0.6211 0.03267 0.02190 -0.0202 1.0000 0.1156
-6.250 -0.5979 0.03096 0.01971 -0.0196 1.0000 0.1235
-6.000 -0.5744 0.02965 0.01843 -0.0191 1.0000 0.1302
-5.750 -0.5504 0.02840 0.01689 -0.0185 1.0000 0.1398
-5.500 -0.5266 0.02738 0.01585 -0.0179 1.0000 0.1492
-5.250 -0.5025 0.02634 0.01473 -0.0173 1.0000 0.1587
-5.000 -0.4778 0.02539 0.01359 -0.0167 1.0000 0.1692
-4.750 -0.4536 0.02451 0.01273 -0.0160 1.0000 0.1795
-4.500 -0.4289 0.02364 0.01183 -0.0153 1.0000 0.1886
-4.250 -0.4043 0.02288 0.01100 -0.0146 1.0000 0.2006
-4.000 -0.3802 0.02216 0.01029 -0.0139 1.0000 0.2148
-3.750 -0.3563 0.02144 0.00961 -0.0132 1.0000 0.2301
-3.500 -0.3337 0.02071 0.00900 -0.0123 1.0000 0.2496
-3.250 -0.3120 0.01998 0.00845 -0.0114 1.0000 0.2803
-3.000 -0.2911 0.01917 0.00796 -0.0104 1.0000 0.3291
-2.750 -0.2719 0.01827 0.00759 -0.0090 1.0000 0.4144
-2.500 -0.2554 0.01740 0.00750 -0.0064 1.0000 0.5519
-2.250 -0.2387 0.01698 0.00763 -0.0028 1.0000 0.6924
-2.000 -0.2168 0.01690 0.00776 0.0000 1.0000 0.7970
-1.750 -0.1854 0.01695 0.00782 0.0006 1.0000 0.8774
-1.500 -0.1345 0.01705 0.00778 -0.0029 1.0000 0.9495
-1.250 -0.0515 0.01701 0.00750 -0.0135 1.0000 1.0000
-1.000 -0.0444 0.01694 0.00735 -0.0106 1.0000 1.0000
-0.750 -0.0367 0.01693 0.00726 -0.0078 1.0000 1.0000
-0.500 -0.0275 0.01697 0.00723 -0.0053 1.0000 1.0000
-0.250 -0.0158 0.01707 0.00725 -0.0032 1.0000 1.0000
0.000 -0.0018 0.01722 0.00733 -0.0015 1.0000 1.0000
0.250 0.0466 0.01744 0.00749 -0.0062 0.9848 1.0000
0.500 0.1001 0.01763 0.00766 -0.0116 0.9670 1.0000
0.750 0.1515 0.01775 0.00780 -0.0164 0.9476 1.0000
1.000 0.1972 0.01781 0.00789 -0.0198 0.9251 1.0000
1.250 0.2409 0.01778 0.00792 -0.0225 0.9005 1.0000
1.500 0.2772 0.01771 0.00788 -0.0234 0.8694 1.0000
1.750 0.3078 0.01762 0.00780 -0.0229 0.8309 1.0000
2.000 0.3356 0.01753 0.00769 -0.0216 0.7871 1.0000
2.250 0.3606 0.01750 0.00757 -0.0198 0.7383 1.0000
2.500 0.3840 0.01755 0.00747 -0.0177 0.6847 1.0000
2.750 0.4065 0.01773 0.00741 -0.0156 0.6264 1.0000
3.000 0.4282 0.01805 0.00746 -0.0136 0.5654 1.0000
3.250 0.4496 0.01852 0.00761 -0.0119 0.5061 1.0000
3.500 0.4712 0.01908 0.00788 -0.0104 0.4523 1.0000
3.750 0.4929 0.01972 0.00826 -0.0092 0.4045 1.0000
4.000 0.5154 0.02040 0.00871 -0.0083 0.3633 1.0000
4.250 0.5387 0.02112 0.00924 -0.0076 0.3268 1.0000
4.500 0.5624 0.02186 0.00985 -0.0070 0.2965 1.0000
4.750 0.5864 0.02261 0.01050 -0.0065 0.2707 1.0000
5.000 0.6109 0.02338 0.01120 -0.0060 0.2500 1.0000
5.250 0.6354 0.02417 0.01191 -0.0055 0.2329 1.0000
5.500 0.6599 0.02497 0.01270 -0.0050 0.2178 1.0000
5.750 0.6850 0.02581 0.01359 -0.0046 0.2053 1.0000
6.000 0.7103 0.02675 0.01459 -0.0041 0.1956 1.0000
6.250 0.7349 0.02770 0.01547 -0.0037 0.1870 1.0000
6.500 0.7597 0.02870 0.01668 -0.0033 0.1776 1.0000
6.750 0.7842 0.02977 0.01778 -0.0028 0.1706 1.0000
7.000 0.8090 0.03104 0.01927 -0.0024 0.1646 1.0000
7.250 0.8334 0.03227 0.02055 -0.0020 0.1597 1.0000
7.500 0.8568 0.03374 0.02231 -0.0016 0.1543 1.0000
7.750 0.8793 0.03514 0.02395 -0.0011 0.1484 1.0000
8.000 0.9025 0.03647 0.02528 -0.0007 0.1441 1.0000
8.250 0.9229 0.03855 0.02779 -0.0002 0.1406 1.0000
8.500 0.9417 0.04076 0.03045 0.0004 0.1370 1.0000
8.750 0.9606 0.04267 0.03263 0.0010 0.1331 1.0000
9.000 0.9822 0.04417 0.03412 0.0015 0.1294 1.0000
9.250 0.9909 0.04735 0.03796 0.0024 0.1256 1.0000
9.500 0.9989 0.05070 0.04179 0.0032 0.1228 1.0000
9.750 1.0072 0.05372 0.04515 0.0040 0.1199 1.0000
10.000 1.0235 0.05547 0.04700 0.0047 0.1164 1.0000
10.250 1.0216 0.05928 0.05120 0.0055 0.1136 1.0000
10.500 1.0007 0.06489 0.05725 0.0059 0.1118 1.0000
10.750 0.9703 0.07104 0.06368 0.0055 0.1111 1.0000
11.000 0.9269 0.07935 0.07211 0.0019 0.1113 1.0000
11.250 0.8719 0.09369 0.08642 -0.0090 0.1119 1.0000
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Polar data table (+)
Polar graphs
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