SIKORSKY SC1094 R8 AIRFOIL (sc1094r8-il) Xfoil prediction polar at RE=100,000 Ncrit=9
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Airfoil: SIKORSKY SC1094 R8 AIRFOIL (sc1094r8-il) Reynolds number: 100,000 Max Cl/Cd: 33.67 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sc1094r8-il-100000.txt Download as CSV file: xf-sc1094r8-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: SIKORSKY SC1094 R8 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.5039 0.11233 0.10727 0.0077 1.0000 0.0867
-9.000 -0.4978 0.10893 0.10390 0.0067 1.0000 0.0893
-8.750 -0.5048 0.10528 0.10030 0.0016 1.0000 0.0920
-8.500 -0.5052 0.10105 0.09613 -0.0012 1.0000 0.0932
-8.250 -0.4901 0.09780 0.09289 0.0007 1.0000 0.0956
-8.000 -0.4886 0.09421 0.08935 -0.0018 1.0000 0.0988
-7.750 -0.5148 0.08869 0.08383 -0.0164 1.0000 0.1011
-7.500 -0.4919 0.08564 0.08089 -0.0097 1.0000 0.1030
-7.250 -0.4832 0.08226 0.07753 -0.0106 1.0000 0.1064
-7.000 -0.4919 0.07673 0.07184 -0.0206 1.0000 0.1110
-6.750 -0.4745 0.07377 0.06902 -0.0173 1.0000 0.1136
-6.500 -0.4755 0.06961 0.06457 -0.0241 1.0000 0.1212
-6.250 -0.4577 0.06643 0.06160 -0.0208 1.0000 0.1244
-6.000 -0.4511 0.06273 0.05770 -0.0240 1.0000 0.1334
-5.750 -0.4358 0.05998 0.05507 -0.0223 1.0000 0.1385
-5.500 -0.4260 0.05660 0.05156 -0.0233 1.0000 0.1475
-5.250 -0.4153 0.05401 0.04877 -0.0239 1.0000 0.1592
-5.000 -0.4013 0.05120 0.04612 -0.0220 1.0000 0.1645
-4.750 -0.3901 0.04855 0.04339 -0.0214 1.0000 0.1767
-4.500 -0.3781 0.04619 0.04095 -0.0205 1.0000 0.1913
-4.250 -0.3659 0.04396 0.03870 -0.0192 1.0000 0.2075
-4.000 -0.3536 0.04181 0.03658 -0.0176 1.0000 0.2255
-3.750 -0.3411 0.03982 0.03464 -0.0157 1.0000 0.2462
-3.000 -0.2400 0.02761 0.01951 -0.0164 1.0000 0.0918
-2.750 -0.2169 0.02572 0.01746 -0.0155 1.0000 0.0886
-2.500 -0.1913 0.02413 0.01532 -0.0143 1.0000 0.0844
-2.250 -0.1670 0.02284 0.01389 -0.0135 1.0000 0.0840
-2.000 -0.1426 0.02177 0.01269 -0.0129 1.0000 0.0855
-1.750 -0.1187 0.02097 0.01196 -0.0124 1.0000 0.0892
-1.500 -0.0933 0.02025 0.01113 -0.0119 1.0000 0.0919
-1.250 -0.0684 0.01950 0.01049 -0.0117 1.0000 0.0956
-1.000 -0.0210 0.01865 0.00981 -0.0155 0.9919 0.1066
-0.750 0.0322 0.01767 0.00908 -0.0203 0.9798 0.1261
-0.500 0.0843 0.01385 0.00848 -0.0218 0.9749 1.0000
-0.250 0.1641 0.01371 0.00791 -0.0309 0.9563 1.0000
0.000 0.2226 0.01345 0.00748 -0.0358 0.9323 1.0000
0.250 0.2660 0.01316 0.00709 -0.0376 0.9057 1.0000
0.500 0.2961 0.01291 0.00674 -0.0366 0.8745 1.0000
0.750 0.3202 0.01269 0.00639 -0.0344 0.8400 1.0000
1.000 0.3412 0.01255 0.00610 -0.0316 0.7993 1.0000
1.250 0.3618 0.01247 0.00583 -0.0289 0.7511 1.0000
1.500 0.3825 0.01251 0.00559 -0.0263 0.6937 1.0000
1.750 0.4036 0.01273 0.00541 -0.0239 0.6273 1.0000
2.000 0.4251 0.01313 0.00537 -0.0220 0.5563 1.0000
2.250 0.4471 0.01369 0.00544 -0.0205 0.4914 1.0000
2.500 0.4697 0.01432 0.00564 -0.0193 0.4338 1.0000
2.750 0.4928 0.01500 0.00593 -0.0184 0.3839 1.0000
3.000 0.5165 0.01572 0.00630 -0.0176 0.3431 1.0000
3.250 0.5406 0.01646 0.00669 -0.0169 0.3125 1.0000
3.500 0.5657 0.01711 0.00718 -0.0163 0.2873 1.0000
3.750 0.5910 0.01778 0.00768 -0.0158 0.2681 1.0000
4.000 0.6165 0.01848 0.00820 -0.0154 0.2528 1.0000
4.250 0.6422 0.01917 0.00872 -0.0150 0.2402 1.0000
4.500 0.6683 0.01985 0.00940 -0.0146 0.2288 1.0000
4.750 0.6942 0.02070 0.01008 -0.0143 0.2200 1.0000
5.000 0.7204 0.02141 0.01085 -0.0139 0.2116 1.0000
5.250 0.7466 0.02237 0.01160 -0.0137 0.2051 1.0000
5.500 0.7726 0.02320 0.01261 -0.0133 0.1986 1.0000
5.750 0.7986 0.02404 0.01343 -0.0130 0.1928 1.0000
6.000 0.8248 0.02533 0.01455 -0.0129 0.1883 1.0000
6.250 0.8499 0.02633 0.01583 -0.0125 0.1843 1.0000
6.500 0.8750 0.02740 0.01705 -0.0121 0.1800 1.0000
6.750 0.9001 0.02845 0.01812 -0.0119 0.1761 1.0000
7.000 0.9252 0.03007 0.01965 -0.0118 0.1730 1.0000
7.250 0.9476 0.03157 0.02152 -0.0112 0.1707 1.0000
7.500 0.9692 0.03327 0.02357 -0.0106 0.1682 1.0000
7.750 0.9904 0.03499 0.02555 -0.0101 0.1655 1.0000
8.000 1.0120 0.03662 0.02733 -0.0096 0.1630 1.0000
8.250 1.0344 0.03824 0.02901 -0.0093 0.1610 1.0000
8.500 1.0548 0.04038 0.03128 -0.0089 0.1595 1.0000
8.750 1.0728 0.04335 0.03439 -0.0086 0.1583 1.0000
9.000 1.0828 0.04644 0.03796 -0.0075 0.1575 1.0000
9.250 1.0881 0.05015 0.04215 -0.0066 0.1567 1.0000
9.500 1.0887 0.05450 0.04692 -0.0057 0.1563 1.0000
9.750 1.0852 0.05945 0.05222 -0.0051 0.1567 1.0000
10.000 1.0823 0.06451 0.05751 -0.0048 0.1574 1.0000
10.250 1.0851 0.06930 0.06243 -0.0048 0.1581 1.0000
10.500 0.7938 0.12492 0.11864 -0.0441 0.2235 1.0000
10.750 0.8310 0.12832 0.12210 -0.0408 0.2219 1.0000
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Polar data table (+)
Polar graphs
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