SIKORSKY SC1094 R8 AIRFOIL (sc1094r8-il) Xfoil prediction polar at RE=100,000 Ncrit=5
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Airfoil: SIKORSKY SC1094 R8 AIRFOIL (sc1094r8-il) Reynolds number: 100,000 Max Cl/Cd: 37.65 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sc1094r8-il-100000-n5.txt Download as CSV file: xf-sc1094r8-il-100000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.4254 0.10402 0.09912 -0.0027 1.0000 0.0634
-8.750 -0.4311 0.09946 0.09460 -0.0060 1.0000 0.0645
-8.500 -0.4384 0.09454 0.08973 -0.0099 1.0000 0.0648
-8.250 -0.4360 0.09030 0.08553 -0.0112 1.0000 0.0652
-8.000 -0.4291 0.08673 0.08199 -0.0112 1.0000 0.0659
-7.750 -0.4281 0.08264 0.07794 -0.0129 1.0000 0.0664
-7.500 -0.4307 0.07821 0.07356 -0.0156 1.0000 0.0670
-7.000 -0.4911 0.06594 0.06072 -0.0248 1.0000 0.0443
-6.750 -0.4813 0.06218 0.05688 -0.0257 1.0000 0.0437
-6.250 -0.4626 0.05180 0.04596 -0.0282 1.0000 0.0401
-6.000 -0.4485 0.04863 0.04265 -0.0280 1.0000 0.0394
-5.750 -0.4345 0.04497 0.03875 -0.0276 1.0000 0.0384
-5.500 -0.4204 0.04077 0.03416 -0.0268 1.0000 0.0374
-5.250 -0.4057 0.03621 0.02896 -0.0256 1.0000 0.0364
-5.000 -0.3883 0.03363 0.02607 -0.0243 1.0000 0.0363
-4.750 -0.3699 0.03121 0.02329 -0.0230 1.0000 0.0363
-4.500 -0.3505 0.02907 0.02081 -0.0217 1.0000 0.0365
-4.250 -0.3309 0.02782 0.01948 -0.0206 1.0000 0.0373
-4.000 -0.3106 0.02657 0.01807 -0.0195 1.0000 0.0385
-3.750 -0.2892 0.02504 0.01620 -0.0182 1.0000 0.0399
-3.500 -0.2673 0.02367 0.01457 -0.0171 1.0000 0.0407
-3.250 -0.2455 0.02266 0.01350 -0.0161 1.0000 0.0414
-3.000 -0.2055 0.02140 0.01212 -0.0184 0.9930 0.0426
-2.750 -0.1612 0.02019 0.01072 -0.0214 0.9842 0.0449
-2.500 -0.1151 0.01928 0.00983 -0.0249 0.9746 0.0485
-2.250 -0.0744 0.01838 0.00898 -0.0273 0.9640 0.0512
-2.000 -0.0356 0.01761 0.00824 -0.0292 0.9539 0.0550
-1.750 -0.0019 0.01701 0.00771 -0.0301 0.9406 0.0605
-1.500 0.0303 0.01645 0.00718 -0.0307 0.9261 0.0666
-1.250 0.0621 0.01595 0.00673 -0.0310 0.9106 0.0777
-1.000 0.0926 0.01541 0.00631 -0.0310 0.8936 0.0977
-0.750 0.1209 0.01463 0.00591 -0.0307 0.8722 0.1754
-0.500 0.1304 0.01232 0.00605 -0.0253 0.8495 0.8199
-0.250 0.1913 0.01214 0.00583 -0.0288 0.8125 0.9875
0.000 0.2290 0.01206 0.00548 -0.0301 0.7717 1.0000
0.250 0.2513 0.01207 0.00524 -0.0283 0.7300 1.0000
0.500 0.2737 0.01214 0.00502 -0.0267 0.6818 1.0000
0.750 0.2961 0.01230 0.00484 -0.0251 0.6277 1.0000
1.000 0.3187 0.01255 0.00471 -0.0236 0.5699 1.0000
1.250 0.3415 0.01287 0.00466 -0.0224 0.5141 1.0000
1.500 0.3647 0.01323 0.00466 -0.0214 0.4637 1.0000
1.750 0.3884 0.01361 0.00472 -0.0205 0.4192 1.0000
2.000 0.4126 0.01399 0.00482 -0.0198 0.3806 1.0000
2.250 0.4370 0.01438 0.00495 -0.0191 0.3463 1.0000
2.500 0.4617 0.01477 0.00511 -0.0186 0.3156 1.0000
2.750 0.4867 0.01516 0.00530 -0.0181 0.2880 1.0000
3.000 0.5118 0.01556 0.00552 -0.0176 0.2630 1.0000
3.250 0.5370 0.01597 0.00576 -0.0171 0.2419 1.0000
3.500 0.5623 0.01640 0.00603 -0.0167 0.2240 1.0000
3.750 0.5877 0.01683 0.00634 -0.0163 0.2094 1.0000
4.000 0.6130 0.01729 0.00669 -0.0159 0.1975 1.0000
4.250 0.6379 0.01780 0.00704 -0.0155 0.1878 1.0000
4.500 0.6635 0.01825 0.00747 -0.0151 0.1788 1.0000
4.750 0.6883 0.01881 0.00791 -0.0147 0.1719 1.0000
5.000 0.7138 0.01930 0.00839 -0.0143 0.1649 1.0000
5.250 0.7386 0.01988 0.00887 -0.0139 0.1593 1.0000
5.500 0.7639 0.02045 0.00945 -0.0135 0.1541 1.0000
5.750 0.7890 0.02102 0.01001 -0.0131 0.1494 1.0000
6.000 0.8136 0.02166 0.01057 -0.0127 0.1455 1.0000
6.250 0.8387 0.02230 0.01124 -0.0123 0.1415 1.0000
6.500 0.8637 0.02294 0.01194 -0.0119 0.1377 1.0000
6.750 0.8884 0.02362 0.01260 -0.0116 0.1346 1.0000
7.000 0.9128 0.02440 0.01329 -0.0112 0.1322 1.0000
7.250 0.9376 0.02516 0.01418 -0.0108 0.1293 1.0000
7.500 0.9620 0.02593 0.01507 -0.0104 0.1264 1.0000
7.750 0.9861 0.02671 0.01588 -0.0100 0.1238 1.0000
8.000 1.0101 0.02752 0.01668 -0.0097 0.1218 1.0000
8.250 1.0341 0.02847 0.01760 -0.0094 0.1202 1.0000
8.500 1.0572 0.02952 0.01888 -0.0089 0.1182 1.0000
8.750 1.0797 0.03058 0.02013 -0.0084 0.1161 1.0000
9.000 1.1020 0.03162 0.02132 -0.0079 0.1141 1.0000
9.250 1.1240 0.03263 0.02241 -0.0074 0.1124 1.0000
9.500 1.1463 0.03365 0.02347 -0.0070 0.1109 1.0000
9.750 1.1686 0.03480 0.02465 -0.0066 0.1098 1.0000
10.000 1.1871 0.03635 0.02648 -0.0059 0.1085 1.0000
10.250 1.2036 0.03805 0.02849 -0.0050 0.1070 1.0000
10.500 1.2191 0.03975 0.03047 -0.0041 0.1054 1.0000
10.750 1.2341 0.04140 0.03235 -0.0033 0.1040 1.0000
11.000 1.2489 0.04300 0.03413 -0.0024 0.1027 1.0000
11.250 1.2634 0.04461 0.03590 -0.0015 0.1017 1.0000
11.500 1.2775 0.04627 0.03770 -0.0007 0.1008 1.0000
11.750 1.2919 0.04793 0.03945 0.0001 0.1000 1.0000
12.000 1.2934 0.05059 0.04242 0.0016 0.0991 1.0000
12.250 1.2794 0.05424 0.04652 0.0036 0.0982 1.0000
12.500 1.2549 0.05822 0.05084 0.0059 0.0975 1.0000
12.750 1.2185 0.06387 0.05683 0.0060 0.0970 1.0000
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Polar data table (+)
Polar graphs
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