PSU 94-097 (AIAA 2001-2478) (psu94097-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: PSU 94-097 (AIAA 2001-2478) (psu94097-il) Reynolds number: 50,000 Max Cl/Cd: 41.16 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-psu94097-il-50000-n5.txt Download as CSV file: xf-psu94097-il-50000-n5.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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.3359 0.10868 0.10214 -0.0379 1.0000 0.0968
-8.250 -0.3474 0.10727 0.10090 -0.0397 1.0000 0.0976
-8.000 -0.3597 0.10577 0.09956 -0.0397 1.0000 0.0978
-7.500 -0.3683 0.10039 0.09443 -0.0371 1.0000 0.0984
-7.250 -0.3548 0.09357 0.08751 -0.0353 1.0000 0.0541
-7.000 -0.3637 0.09149 0.08553 -0.0334 1.0000 0.0515
-6.750 -0.3755 0.08925 0.08341 -0.0326 1.0000 0.0491
-6.500 -0.3875 0.08565 0.07985 -0.0364 1.0000 0.0435
-6.250 -0.3904 0.08316 0.07742 -0.0350 0.9998 0.0424
-6.000 -0.3688 0.07796 0.07217 -0.0413 0.9929 0.0407
-5.750 -0.3445 0.07223 0.06630 -0.0490 0.9854 0.0394
-5.500 -0.3185 0.06638 0.06030 -0.0567 0.9782 0.0386
-5.250 -0.2880 0.06041 0.05410 -0.0646 0.9716 0.0382
-5.000 -0.2571 0.05492 0.04828 -0.0713 0.9652 0.0383
-4.750 -0.2228 0.04966 0.04259 -0.0776 0.9594 0.0386
-4.500 -0.1831 0.04461 0.03697 -0.0836 0.9552 0.0388
-4.250 -0.1496 0.04061 0.03239 -0.0871 0.9491 0.0387
-4.000 -0.1104 0.03693 0.02804 -0.0907 0.9448 0.0391
-3.750 -0.0688 0.03382 0.02425 -0.0939 0.9416 0.0404
-3.500 -0.0363 0.03182 0.02156 -0.0949 0.9357 0.0439
-3.250 -0.0013 0.03004 0.01962 -0.0968 0.9312 0.0503
-3.000 0.0370 0.02841 0.01759 -0.0982 0.9279 0.0579
-2.750 0.0657 0.02734 0.01638 -0.0985 0.9217 0.0716
-2.500 0.1020 0.02613 0.01515 -0.1003 0.9172 0.1018
-2.250 0.1435 0.02453 0.01403 -0.1037 0.9141 0.2121
-2.000 0.1719 0.02304 0.01387 -0.1045 0.9087 0.4949
-1.750 0.1865 0.02238 0.01396 -0.1002 0.9027 0.7471
-1.500 0.2075 0.02198 0.01357 -0.0976 0.8951 1.0000
-1.250 0.2409 0.02222 0.01332 -0.0991 0.8888 1.0000
-1.000 0.2749 0.02246 0.01313 -0.1006 0.8832 1.0000
-0.750 0.3037 0.02278 0.01313 -0.1013 0.8758 1.0000
-0.500 0.3403 0.02298 0.01301 -0.1032 0.8712 1.0000
-0.250 0.3647 0.02339 0.01318 -0.1031 0.8626 1.0000
0.000 0.4000 0.02360 0.01315 -0.1046 0.8576 1.0000
0.250 0.4242 0.02403 0.01342 -0.1045 0.8489 1.0000
0.500 0.4588 0.02423 0.01345 -0.1058 0.8437 1.0000
0.750 0.4826 0.02469 0.01377 -0.1055 0.8347 1.0000
1.000 0.5172 0.02486 0.01382 -0.1067 0.8294 1.0000
1.250 0.5403 0.02533 0.01421 -0.1063 0.8198 1.0000
1.500 0.5720 0.02555 0.01435 -0.1069 0.8133 1.0000
1.750 0.5979 0.02592 0.01468 -0.1068 0.8042 1.0000
2.000 0.6246 0.02626 0.01499 -0.1067 0.7954 1.0000
2.250 0.6561 0.02639 0.01510 -0.1071 0.7881 1.0000
2.500 0.6801 0.02679 0.01553 -0.1066 0.7776 1.0000
2.750 0.7082 0.02699 0.01574 -0.1065 0.7685 1.0000
3.000 0.7389 0.02702 0.01579 -0.1065 0.7598 1.0000
3.250 0.7632 0.02731 0.01612 -0.1058 0.7482 1.0000
3.500 0.7890 0.02751 0.01643 -0.1052 0.7369 1.0000
3.750 0.8169 0.02756 0.01654 -0.1047 0.7262 1.0000
4.000 0.8485 0.02735 0.01641 -0.1045 0.7167 1.0000
4.250 0.8733 0.02748 0.01664 -0.1036 0.7036 1.0000
4.500 0.8986 0.02754 0.01686 -0.1027 0.6902 1.0000
4.750 0.9243 0.02754 0.01698 -0.1017 0.6763 1.0000
5.000 0.9503 0.02749 0.01706 -0.1007 0.6618 1.0000
5.250 0.9765 0.02737 0.01708 -0.0997 0.6467 1.0000
5.500 0.9979 0.02755 0.01746 -0.0983 0.6282 1.0000
5.750 1.0214 0.02755 0.01762 -0.0969 0.6094 1.0000
6.000 1.0478 0.02732 0.01753 -0.0957 0.5906 1.0000
6.250 1.0683 0.02750 0.01787 -0.0941 0.5669 1.0000
6.500 1.0912 0.02752 0.01807 -0.0926 0.5421 1.0000
6.750 1.1141 0.02758 0.01822 -0.0910 0.5147 1.0000
7.000 1.1360 0.02776 0.01845 -0.0894 0.4845 1.0000
7.250 1.1567 0.02810 0.01877 -0.0876 0.4526 1.0000
7.500 1.1749 0.02870 0.01934 -0.0858 0.4199 1.0000
7.750 1.1910 0.02953 0.02018 -0.0838 0.3877 1.0000
8.000 1.2055 0.03053 0.02113 -0.0818 0.3576 1.0000
8.250 1.2185 0.03167 0.02225 -0.0798 0.3295 1.0000
8.500 1.2303 0.03292 0.02349 -0.0778 0.3033 1.0000
8.750 1.2407 0.03426 0.02482 -0.0756 0.2792 1.0000
9.000 1.2489 0.03567 0.02625 -0.0733 0.2566 1.0000
9.250 1.2557 0.03718 0.02781 -0.0710 0.2349 1.0000
9.500 1.2618 0.03881 0.02947 -0.0688 0.2148 1.0000
9.750 1.2668 0.04059 0.03137 -0.0667 0.1949 1.0000
10.000 1.2711 0.04251 0.03336 -0.0647 0.1762 1.0000
10.250 1.2734 0.04460 0.03546 -0.0628 0.1592 1.0000
10.500 1.2761 0.04684 0.03778 -0.0611 0.1426 1.0000
10.750 1.2775 0.04927 0.04030 -0.0595 0.1270 1.0000
11.000 1.2788 0.05183 0.04294 -0.0581 0.1135 1.0000
11.250 1.2790 0.05458 0.04576 -0.0567 0.1015 1.0000
11.500 1.2781 0.05748 0.04870 -0.0556 0.0914 1.0000
11.750 1.2781 0.06047 0.05180 -0.0544 0.0824 1.0000
12.000 1.2778 0.06367 0.05521 -0.0535 0.0742 1.0000
12.250 1.2754 0.06693 0.05845 -0.0527 0.0682 1.0000
12.500 1.2769 0.07038 0.06226 -0.0517 0.0623 1.0000
12.750 1.2740 0.07381 0.06570 -0.0512 0.0579 1.0000
13.000 1.2692 0.07803 0.07032 -0.0510 0.0538 1.0000
13.250 1.2627 0.08240 0.07495 -0.0511 0.0504 1.0000
13.500 1.2582 0.08647 0.07914 -0.0512 0.0479 1.0000
13.750 1.2534 0.09081 0.08356 -0.0514 0.0456 1.0000
14.000 1.2399 0.09679 0.08992 -0.0530 0.0444 1.0000
14.250 1.2248 0.10327 0.09671 -0.0553 0.0435 1.0000
14.500 1.2084 0.11037 0.10409 -0.0585 0.0429 1.0000
14.750 1.1908 0.11828 0.11223 -0.0625 0.0428 1.0000
15.000 1.1714 0.12720 0.12137 -0.0676 0.0432 1.0000
15.250 1.1515 0.13709 0.13142 -0.0735 0.0439 1.0000
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Polar data table (+)
Polar graphs
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