SIKORSKY SC1094R8 AIRFOIL (sc1095r8-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: SIKORSKY SC1094R8 AIRFOIL (sc1095r8-il) Reynolds number: 50,000 Max Cl/Cd: 24.41 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sc1095r8-il-50000.txt Download as CSV file: xf-sc1095r8-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: SIKORSKY SC1094R8 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-6.750 -0.4718 0.09959 0.09294 0.0044 1.0000 0.2587
-6.500 -0.4900 0.09820 0.09168 0.0017 1.0000 0.2719
-6.250 -0.4776 0.09452 0.08804 0.0033 1.0000 0.2883
-6.000 -0.4770 0.09164 0.08525 0.0036 1.0000 0.3056
-5.750 -0.4440 0.08720 0.08081 0.0079 1.0000 0.3308
-5.500 -0.4546 0.08542 0.07916 0.0084 1.0000 0.3558
-5.250 -0.4386 0.08241 0.07620 0.0118 1.0000 0.3890
-5.000 -0.4365 0.08028 0.07416 0.0147 1.0000 0.4244
-4.750 -0.3992 0.07650 0.07038 0.0194 1.0000 0.4721
-4.500 -0.3868 0.07441 0.06836 0.0240 1.0000 0.5259
-4.250 -0.3584 0.07174 0.06570 0.0291 1.0000 0.5948
-4.000 -0.2956 0.06716 0.06107 0.0326 1.0000 0.6952
-3.000 -0.3383 0.04306 0.03527 -0.0248 1.0000 0.2050
-2.750 -0.3094 0.03959 0.03105 -0.0250 1.0000 0.1702
-2.500 -0.2875 0.03700 0.02831 -0.0240 1.0000 0.1634
-2.250 -0.2635 0.03457 0.02541 -0.0231 1.0000 0.1553
-2.000 -0.2387 0.03285 0.02321 -0.0219 1.0000 0.1497
-1.750 -0.2154 0.03085 0.02102 -0.0208 1.0000 0.1470
-1.500 -0.1912 0.02919 0.01913 -0.0196 1.0000 0.1460
-1.250 -0.1670 0.02790 0.01756 -0.0184 1.0000 0.1487
-1.000 -0.1423 0.02686 0.01622 -0.0171 1.0000 0.1516
-0.750 -0.1179 0.02536 0.01478 -0.0161 1.0000 0.1555
-0.500 -0.0934 0.02439 0.01382 -0.0149 1.0000 0.1637
-0.250 -0.0687 0.02347 0.01292 -0.0136 1.0000 0.1752
0.000 -0.0439 0.02264 0.01214 -0.0125 1.0000 0.1910
0.250 -0.0195 0.02172 0.01141 -0.0117 1.0000 0.2230
0.500 0.0102 0.01798 0.01057 -0.0085 1.0000 1.0000
0.750 0.0283 0.01832 0.01042 -0.0072 1.0000 1.0000
1.000 0.0459 0.01873 0.01057 -0.0063 1.0000 1.0000
1.250 0.0631 0.01924 0.01091 -0.0057 1.0000 1.0000
1.500 0.0797 0.01990 0.01143 -0.0054 1.0000 1.0000
1.750 0.1428 0.02086 0.01224 -0.0130 0.9793 1.0000
2.000 0.2516 0.02123 0.01252 -0.0261 0.9298 1.0000
2.250 0.3389 0.02065 0.01196 -0.0334 0.8785 1.0000
2.500 0.3885 0.01996 0.01124 -0.0334 0.8257 1.0000
2.750 0.4186 0.01943 0.01057 -0.0299 0.7695 1.0000
3.000 0.4400 0.01921 0.01008 -0.0255 0.7067 1.0000
3.250 0.4597 0.01931 0.00977 -0.0213 0.6408 1.0000
3.500 0.4795 0.01977 0.00973 -0.0178 0.5752 1.0000
3.750 0.5010 0.02053 0.00998 -0.0152 0.5158 1.0000
4.000 0.5236 0.02145 0.01046 -0.0132 0.4651 1.0000
4.250 0.5473 0.02248 0.01117 -0.0118 0.4247 1.0000
4.500 0.5716 0.02351 0.01191 -0.0105 0.3933 1.0000
4.750 0.5965 0.02460 0.01286 -0.0094 0.3677 1.0000
5.000 0.6215 0.02568 0.01375 -0.0084 0.3473 1.0000
5.250 0.6465 0.02682 0.01477 -0.0075 0.3299 1.0000
5.500 0.6716 0.02812 0.01613 -0.0068 0.3158 1.0000
5.750 0.6963 0.02952 0.01760 -0.0060 0.3036 1.0000
6.000 0.7209 0.03085 0.01886 -0.0052 0.2929 1.0000
6.250 0.7448 0.03231 0.02045 -0.0045 0.2828 1.0000
6.500 0.7685 0.03409 0.02230 -0.0039 0.2763 1.0000
6.750 0.7899 0.03616 0.02473 -0.0033 0.2698 1.0000
7.000 0.8140 0.03772 0.02622 -0.0026 0.2637 1.0000
7.250 0.8321 0.04023 0.02909 -0.0020 0.2582 1.0000
7.500 0.8491 0.04288 0.03208 -0.0016 0.2534 1.0000
7.750 0.8658 0.04574 0.03520 -0.0012 0.2507 1.0000
8.000 0.8811 0.04888 0.03857 -0.0008 0.2489 1.0000
8.250 0.8966 0.05200 0.04185 -0.0005 0.2472 1.0000
8.500 0.9082 0.05575 0.04577 -0.0003 0.2456 1.0000
8.750 0.9080 0.06087 0.05124 -0.0009 0.2454 1.0000
9.000 0.9042 0.06653 0.05719 -0.0021 0.2464 1.0000
9.250 0.8492 0.08028 0.07134 -0.0101 0.2618 1.0000
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Polar data table (+)
Polar graphs
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