PSU 94-097 (AIAA 2001-2478) (psu94097-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: PSU 94-097 (AIAA 2001-2478) (psu94097-il) Reynolds number: 1,000,000 Max Cl/Cd: 150.73 at α=3.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-psu94097-il-1000000.txt Download as CSV file: xf-psu94097-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.3117 0.08967 0.08802 -0.0382 0.9306 0.0061
-8.000 -0.3081 0.08624 0.08454 -0.0396 0.9148 0.0062
-7.750 -0.3037 0.08264 0.08090 -0.0416 0.9008 0.0064
-7.500 -0.2989 0.07884 0.07706 -0.0441 0.8874 0.0065
-7.250 -0.2939 0.07482 0.07301 -0.0474 0.8747 0.0067
-7.000 -0.2813 0.06965 0.06780 -0.0539 0.8634 0.0070
-6.750 -0.2635 0.06414 0.06223 -0.0619 0.8534 0.0071
-6.500 -0.2425 0.05795 0.05595 -0.0709 0.8440 0.0072
-6.250 -0.2187 0.05114 0.04903 -0.0795 0.8355 0.0072
-6.000 -0.1940 0.04416 0.04186 -0.0865 0.8281 0.0073
-5.750 -0.1685 0.03707 0.03452 -0.0918 0.8210 0.0073
-5.000 -0.0870 0.01464 0.00997 -0.1017 0.8032 0.0049
-4.750 -0.0573 0.01281 0.00778 -0.1022 0.7977 0.0049
-4.500 -0.0281 0.01167 0.00647 -0.1026 0.7919 0.0053
-4.250 0.0008 0.01118 0.00587 -0.1029 0.7866 0.0058
-4.000 0.0303 0.01062 0.00522 -0.1033 0.7812 0.0064
-3.750 0.0597 0.01008 0.00456 -0.1036 0.7759 0.0068
-3.500 0.0892 0.00957 0.00395 -0.1040 0.7710 0.0070
-3.250 0.1189 0.00917 0.00349 -0.1044 0.7659 0.0072
-3.000 0.1490 0.00856 0.00276 -0.1049 0.7610 0.0083
-2.750 0.1788 0.00827 0.00242 -0.1053 0.7563 0.0091
-2.500 0.2087 0.00800 0.00207 -0.1057 0.7512 0.0100
-2.250 0.2392 0.00755 0.00168 -0.1062 0.7465 0.0417
-2.000 0.2690 0.00727 0.00156 -0.1068 0.7417 0.0925
-1.750 0.2989 0.00694 0.00147 -0.1074 0.7365 0.1722
-1.500 0.3288 0.00659 0.00141 -0.1082 0.7313 0.2842
-1.250 0.3587 0.00632 0.00137 -0.1088 0.7260 0.3717
-1.000 0.3887 0.00596 0.00136 -0.1096 0.7206 0.5085
-0.750 0.4182 0.00575 0.00136 -0.1101 0.7149 0.6037
-0.500 0.4475 0.00559 0.00138 -0.1104 0.7082 0.6777
-0.250 0.4763 0.00552 0.00139 -0.1106 0.7020 0.7344
0.000 0.5050 0.00541 0.00142 -0.1107 0.6960 0.7837
0.250 0.5329 0.00536 0.00143 -0.1107 0.6899 0.8258
0.500 0.5599 0.00529 0.00145 -0.1104 0.6836 0.8671
0.750 0.5823 0.00517 0.00144 -0.1089 0.6770 0.9272
1.000 0.6074 0.00507 0.00136 -0.1081 0.6705 1.0000
1.250 0.6368 0.00513 0.00137 -0.1085 0.6632 1.0000
1.500 0.6661 0.00518 0.00140 -0.1088 0.6560 1.0000
1.750 0.6953 0.00526 0.00142 -0.1092 0.6481 1.0000
2.000 0.7244 0.00532 0.00147 -0.1095 0.6397 1.0000
2.250 0.7534 0.00540 0.00150 -0.1098 0.6307 1.0000
2.500 0.7823 0.00548 0.00155 -0.1101 0.6203 1.0000
2.750 0.8111 0.00556 0.00161 -0.1103 0.6089 1.0000
3.000 0.8397 0.00567 0.00168 -0.1106 0.5962 1.0000
3.250 0.8681 0.00580 0.00176 -0.1108 0.5806 1.0000
3.750 0.9240 0.00613 0.00195 -0.1111 0.5408 1.0000
4.000 0.9515 0.00637 0.00210 -0.1111 0.5154 1.0000
4.250 0.9784 0.00665 0.00227 -0.1112 0.4849 1.0000
4.500 1.0050 0.00699 0.00246 -0.1111 0.4516 1.0000
4.750 1.0310 0.00738 0.00270 -0.1110 0.4142 1.0000
5.000 1.0568 0.00780 0.00296 -0.1109 0.3791 1.0000
5.250 1.0824 0.00822 0.00323 -0.1108 0.3436 1.0000
5.750 1.1330 0.00908 0.00383 -0.1104 0.2826 1.0000
6.000 1.1583 0.00949 0.00412 -0.1102 0.2564 1.0000
6.250 1.1834 0.00991 0.00444 -0.1100 0.2310 1.0000
6.500 1.2081 0.01034 0.00477 -0.1097 0.2068 1.0000
6.750 1.2323 0.01081 0.00512 -0.1093 0.1833 1.0000
7.000 1.2560 0.01132 0.00552 -0.1089 0.1590 1.0000
7.250 1.2789 0.01189 0.00595 -0.1084 0.1325 1.0000
7.500 1.3010 0.01252 0.00642 -0.1077 0.1062 1.0000
7.750 1.3236 0.01306 0.00687 -0.1071 0.0872 1.0000
8.000 1.3454 0.01367 0.00738 -0.1064 0.0702 1.0000
8.250 1.3667 0.01429 0.00791 -0.1056 0.0536 1.0000
8.500 1.3870 0.01498 0.00852 -0.1047 0.0391 1.0000
8.750 1.4072 0.01565 0.00913 -0.1037 0.0284 1.0000
9.000 1.4273 0.01629 0.00974 -0.1028 0.0209 1.0000
9.250 1.4473 0.01689 0.01034 -0.1018 0.0159 1.0000
9.500 1.4664 0.01755 0.01098 -0.1006 0.0117 1.0000
9.750 1.4837 0.01831 0.01173 -0.0992 0.0071 1.0000
10.000 1.4939 0.01962 0.01302 -0.0967 0.0015 1.0000
10.250 1.5071 0.02050 0.01400 -0.0946 0.0010 1.0000
10.500 1.5155 0.02154 0.01517 -0.0917 0.0009 1.0000
10.750 1.5252 0.02256 0.01629 -0.0892 0.0008 1.0000
11.000 1.5354 0.02359 0.01741 -0.0870 0.0008 1.0000
11.250 1.5445 0.02475 0.01867 -0.0848 0.0007 1.0000
11.500 1.5525 0.02604 0.02006 -0.0827 0.0007 1.0000
11.750 1.5588 0.02752 0.02166 -0.0805 0.0007 1.0000
12.000 1.5643 0.02912 0.02337 -0.0784 0.0007 1.0000
12.250 1.5685 0.03090 0.02528 -0.0764 0.0007 1.0000
12.500 1.5711 0.03288 0.02738 -0.0745 0.0007 1.0000
12.750 1.5723 0.03506 0.02970 -0.0727 0.0006 1.0000
13.000 1.5724 0.03743 0.03221 -0.0711 0.0006 1.0000
13.250 1.5704 0.04010 0.03501 -0.0695 0.0006 1.0000
13.500 1.5671 0.04301 0.03807 -0.0682 0.0006 1.0000
13.750 1.5624 0.04613 0.04133 -0.0670 0.0006 1.0000
14.000 1.5558 0.04962 0.04496 -0.0661 0.0006 1.0000
14.250 1.5487 0.05327 0.04876 -0.0654 0.0006 1.0000
14.500 1.5398 0.05730 0.05293 -0.0650 0.0006 1.0000
14.750 1.5298 0.06172 0.05750 -0.0650 0.0006 1.0000
15.000 1.5190 0.06644 0.06238 -0.0653 0.0006 1.0000
15.250 1.5063 0.07166 0.06776 -0.0661 0.0006 1.0000
15.500 1.4928 0.07729 0.07354 -0.0672 0.0006 1.0000
15.750 1.4787 0.08325 0.07965 -0.0688 0.0006 1.0000
16.000 1.4633 0.08966 0.08621 -0.0708 0.0006 1.0000
16.250 1.4466 0.09655 0.09326 -0.0732 0.0007 1.0000
16.500 1.4314 0.10341 0.10026 -0.0758 0.0007 1.0000
16.750 1.4139 0.11086 0.10785 -0.0789 0.0007 1.0000
17.000 1.3975 0.11833 0.11547 -0.0822 0.0007 1.0000
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Polar data table (+)
Polar graphs
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