PSU 94-097 (AIAA 2001-2478) (psu94097-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: PSU 94-097 (AIAA 2001-2478) (psu94097-il) Reynolds number: 500,000 Max Cl/Cd: 126.62 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-psu94097-il-500000.txt Download as CSV file: xf-psu94097-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: PSU 94-097 (AIAA 2001-2478)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.3207 0.09792 0.09577 -0.0377 1.0000 0.0110
-8.500 -0.3155 0.09436 0.09224 -0.0397 1.0000 0.0111
-8.250 -0.3166 0.08931 0.08724 -0.0418 0.9965 0.0114
-8.000 -0.3016 0.08552 0.08345 -0.0456 0.9854 0.0117
-7.750 -0.2865 0.08182 0.07975 -0.0495 0.9723 0.0120
-7.500 -0.2759 0.07823 0.07615 -0.0526 0.9559 0.0123
-7.250 -0.2714 0.07498 0.07286 -0.0546 0.9379 0.0126
-7.000 -0.2633 0.07122 0.06906 -0.0583 0.9233 0.0129
-6.750 -0.2514 0.06684 0.06463 -0.0638 0.9110 0.0133
-6.500 -0.2353 0.06173 0.05945 -0.0709 0.9000 0.0137
-6.250 -0.2146 0.05584 0.05347 -0.0791 0.8895 0.0143
-6.000 -0.1891 0.04914 0.04659 -0.0873 0.8808 0.0153
-5.750 -0.1575 0.04287 0.04000 -0.0932 0.8730 0.0161
-5.500 -0.1325 0.03795 0.03473 -0.0968 0.8654 0.0162
-5.250 -0.1142 0.03092 0.02738 -0.1009 0.8587 0.0174
-5.000 -0.0890 0.02866 0.02495 -0.1022 0.8519 0.0183
-4.750 -0.0617 0.02605 0.02205 -0.1034 0.8457 0.0197
-4.500 -0.0255 0.01854 0.01334 -0.1041 0.8405 0.0112
-4.250 0.0040 0.01597 0.01041 -0.1047 0.8344 0.0108
-3.750 0.0622 0.01286 0.00679 -0.1054 0.8234 0.0123
-3.500 0.0909 0.01233 0.00620 -0.1056 0.8179 0.0137
-3.250 0.1204 0.01143 0.00515 -0.1058 0.8128 0.0139
-3.000 0.1503 0.01070 0.00432 -0.1061 0.8071 0.0142
-2.750 0.1801 0.01017 0.00367 -0.1064 0.8022 0.0153
-2.500 0.2106 0.00959 0.00300 -0.1069 0.7971 0.0208
-2.250 0.2413 0.00886 0.00258 -0.1077 0.7917 0.1103
-2.000 0.2709 0.00836 0.00246 -0.1085 0.7872 0.2344
-1.750 0.3008 0.00791 0.00239 -0.1093 0.7818 0.3623
-1.500 0.3305 0.00743 0.00236 -0.1100 0.7766 0.5253
-1.250 0.3591 0.00715 0.00238 -0.1103 0.7720 0.6472
-1.000 0.3872 0.00696 0.00240 -0.1102 0.7661 0.7291
-0.750 0.4139 0.00684 0.00239 -0.1097 0.7608 0.7921
-0.500 0.4389 0.00673 0.00239 -0.1088 0.7552 0.8494
-0.250 0.4607 0.00659 0.00234 -0.1071 0.7492 0.9044
0.000 0.4846 0.00644 0.00218 -0.1059 0.7435 1.0000
0.250 0.5144 0.00647 0.00214 -0.1063 0.7362 1.0000
0.500 0.5438 0.00655 0.00211 -0.1067 0.7300 1.0000
0.750 0.5732 0.00658 0.00212 -0.1071 0.7229 1.0000
1.000 0.6024 0.00666 0.00210 -0.1073 0.7167 1.0000
1.250 0.6317 0.00670 0.00213 -0.1077 0.7093 1.0000
1.750 0.6897 0.00683 0.00217 -0.1082 0.6947 1.0000
2.000 0.7184 0.00692 0.00220 -0.1084 0.6875 1.0000
2.250 0.7473 0.00697 0.00225 -0.1087 0.6791 1.0000
2.500 0.7760 0.00705 0.00229 -0.1089 0.6710 1.0000
2.750 0.8045 0.00712 0.00234 -0.1091 0.6620 1.0000
3.000 0.8331 0.00719 0.00243 -0.1093 0.6522 1.0000
3.250 0.8615 0.00728 0.00250 -0.1094 0.6421 1.0000
3.500 0.8896 0.00738 0.00257 -0.1095 0.6309 1.0000
3.750 0.9176 0.00748 0.00265 -0.1096 0.6183 1.0000
4.000 0.9455 0.00759 0.00277 -0.1097 0.6032 1.0000
4.250 0.9732 0.00772 0.00288 -0.1097 0.5855 1.0000
4.500 1.0003 0.00790 0.00301 -0.1097 0.5645 1.0000
4.750 1.0269 0.00813 0.00319 -0.1095 0.5387 1.0000
5.000 1.0528 0.00844 0.00339 -0.1093 0.5089 1.0000
5.250 1.0781 0.00881 0.00364 -0.1090 0.4742 1.0000
5.500 1.1025 0.00928 0.00394 -0.1086 0.4347 1.0000
5.750 1.1263 0.00982 0.00432 -0.1082 0.3944 1.0000
6.000 1.1497 0.01039 0.00472 -0.1077 0.3546 1.0000
6.250 1.1731 0.01095 0.00513 -0.1072 0.3196 1.0000
6.500 1.1964 0.01150 0.00556 -0.1067 0.2884 1.0000
6.750 1.2194 0.01207 0.00601 -0.1062 0.2590 1.0000
7.000 1.2422 0.01263 0.00648 -0.1056 0.2325 1.0000
7.250 1.2646 0.01322 0.00696 -0.1050 0.2065 1.0000
7.500 1.2866 0.01382 0.00746 -0.1043 0.1827 1.0000
7.750 1.3086 0.01439 0.00797 -0.1036 0.1624 1.0000
8.000 1.3299 0.01500 0.00852 -0.1029 0.1422 1.0000
8.250 1.3503 0.01567 0.00911 -0.1019 0.1213 1.0000
8.500 1.3699 0.01638 0.00976 -0.1009 0.1010 1.0000
8.750 1.3875 0.01724 0.01048 -0.0996 0.0794 1.0000
9.000 1.4035 0.01818 0.01129 -0.0981 0.0581 1.0000
9.250 1.4191 0.01910 0.01213 -0.0966 0.0419 1.0000
9.500 1.4336 0.02005 0.01301 -0.0949 0.0304 1.0000
9.750 1.4478 0.02093 0.01388 -0.0930 0.0233 1.0000
10.000 1.4584 0.02187 0.01483 -0.0906 0.0185 1.0000
10.250 1.4705 0.02275 0.01575 -0.0885 0.0149 1.0000
10.500 1.4803 0.02384 0.01691 -0.0863 0.0108 1.0000
10.750 1.4811 0.02571 0.01879 -0.0831 0.0054 1.0000
11.000 1.4870 0.02725 0.02041 -0.0807 0.0036 1.0000
11.250 1.4899 0.02913 0.02243 -0.0782 0.0030 1.0000
11.500 1.4957 0.03078 0.02421 -0.0762 0.0026 1.0000
11.750 1.5002 0.03261 0.02617 -0.0744 0.0023 1.0000
12.000 1.5033 0.03462 0.02831 -0.0726 0.0022 1.0000
12.250 1.5036 0.03698 0.03080 -0.0708 0.0020 1.0000
12.500 1.5001 0.03978 0.03375 -0.0690 0.0019 1.0000
12.750 1.4933 0.04305 0.03719 -0.0674 0.0019 1.0000
13.000 1.4849 0.04660 0.04090 -0.0660 0.0018 1.0000
13.250 1.4733 0.05066 0.04514 -0.0648 0.0018 1.0000
13.500 1.4646 0.05452 0.04915 -0.0640 0.0018 1.0000
13.750 1.4584 0.05822 0.05301 -0.0635 0.0018 1.0000
14.000 1.4510 0.06224 0.05719 -0.0633 0.0017 1.0000
14.250 1.4427 0.06655 0.06166 -0.0634 0.0017 1.0000
14.500 1.4336 0.07117 0.06646 -0.0638 0.0017 1.0000
14.750 1.4237 0.07613 0.07158 -0.0646 0.0017 1.0000
15.000 1.4128 0.08140 0.07702 -0.0656 0.0017 1.0000
15.250 1.4010 0.08702 0.08280 -0.0671 0.0017 1.0000
15.500 1.3888 0.09295 0.08891 -0.0689 0.0017 1.0000
15.750 1.3762 0.09915 0.09527 -0.0710 0.0017 1.0000
16.000 1.3626 0.10570 0.10197 -0.0735 0.0017 1.0000
16.250 1.3488 0.11253 0.10897 -0.0764 0.0017 1.0000
16.500 1.3353 0.11949 0.11609 -0.0795 0.0017 1.0000
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Polar data table (+)
Polar graphs
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