PW75 (pw75-pw) Xfoil prediction polar at RE=5,000,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: PW75 (pw75-pw) Reynolds number: 5,000,000 Max Cl/Cd: 107.17 at α=8° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-pw75-pw-5000000.txt Download as CSV file: xf-pw75-pw-5000000.csv |
XFOIL Version 6.96
Calculated polar for: PW75
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 5.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.9885 0.01146 0.00775 0.0057 1.0000 0.0022
-9.000 -0.9660 0.00997 0.00598 0.0066 1.0000 0.0025
-8.750 -0.9395 0.00947 0.00544 0.0069 1.0000 0.0036
-8.500 -0.9112 0.00943 0.00550 0.0069 1.0000 0.0046
-8.250 -0.8823 0.00983 0.00602 0.0069 0.9660 0.0051
-8.000 -0.8570 0.01034 0.00656 0.0078 0.9289 0.0054
-7.750 -0.8286 0.01086 0.00710 0.0079 0.8990 0.0056
-7.500 -0.7997 0.01134 0.00759 0.0079 0.8727 0.0059
-7.250 -0.7711 0.01161 0.00784 0.0078 0.8490 0.0061
-7.000 -0.7531 0.00842 0.00387 0.0098 0.8286 0.0055
-5.250 -0.5440 0.01376 0.00967 0.0070 0.7029 0.0011
-5.000 -0.5170 0.01320 0.00901 0.0072 0.6863 0.0011
-4.750 -0.4899 0.01259 0.00830 0.0074 0.6694 0.0010
-4.500 -0.4627 0.01199 0.00757 0.0076 0.6525 0.0010
-4.250 -0.4353 0.01144 0.00694 0.0078 0.6366 0.0009
-4.000 -0.4078 0.01087 0.00628 0.0080 0.6206 0.0009
-3.750 -0.3802 0.01034 0.00567 0.0082 0.6046 0.0009
-3.500 -0.3526 0.00982 0.00507 0.0084 0.5894 0.0009
-3.250 -0.3250 0.00929 0.00447 0.0086 0.5742 0.0008
-2.750 -0.2698 0.00828 0.00332 0.0091 0.5459 0.0008
-2.500 -0.2422 0.00778 0.00275 0.0094 0.5322 0.0009
-2.250 -0.2143 0.00747 0.00238 0.0095 0.5181 0.0011
-2.000 -0.1871 0.00637 0.00091 0.0105 0.5049 0.0050
-1.750 -0.1585 0.00632 0.00086 0.0104 0.4908 0.0059
-1.500 -0.1299 0.00629 0.00082 0.0104 0.4765 0.0065
-1.250 -0.1013 0.00627 0.00075 0.0103 0.4623 0.0066
-1.000 -0.0726 0.00625 0.00071 0.0102 0.4485 0.0071
-0.750 -0.0440 0.00623 0.00066 0.0101 0.4343 0.0075
-0.500 -0.0153 0.00622 0.00063 0.0100 0.4201 0.0081
-0.250 0.0134 0.00622 0.00059 0.0099 0.4063 0.0082
0.250 0.0708 0.00623 0.00057 0.0098 0.3782 0.0099
0.500 0.0995 0.00625 0.00057 0.0096 0.3650 0.0160
0.750 0.1281 0.00625 0.00057 0.0095 0.3505 0.0197
1.000 0.1562 0.00607 0.00055 0.0095 0.3365 0.1022
1.500 0.2097 0.00503 0.00052 0.0094 0.3111 0.5159
1.750 0.2334 0.00418 0.00053 0.0100 0.2992 0.8301
2.000 0.2610 0.00412 0.00057 0.0101 0.2887 0.8749
2.250 0.2888 0.00415 0.00062 0.0102 0.2757 0.8994
2.500 0.3169 0.00419 0.00067 0.0102 0.2647 0.9150
2.750 0.3450 0.00425 0.00072 0.0103 0.2542 0.9269
3.000 0.3725 0.00434 0.00078 0.0104 0.2376 0.9409
3.250 0.3986 0.00455 0.00089 0.0108 0.2024 0.9588
3.500 0.4250 0.00475 0.00099 0.0111 0.1734 0.9717
3.750 0.4513 0.00531 0.00124 0.0112 0.0988 0.9812
4.000 0.4805 0.00575 0.00147 0.0107 0.0528 0.9884
4.250 0.5095 0.00592 0.00160 0.0105 0.0432 0.9931
4.500 0.5419 0.00636 0.00187 0.0093 0.0075 0.9948
4.750 0.5743 0.00659 0.00206 0.0082 0.0015 0.9959
5.000 0.6066 0.00671 0.00215 0.0071 0.0006 0.9970
5.250 0.6385 0.00685 0.00227 0.0062 0.0005 0.9981
5.500 0.6702 0.00701 0.00240 0.0053 0.0005 0.9990
5.750 0.7019 0.00717 0.00254 0.0043 0.0005 0.9996
6.000 0.7315 0.00735 0.00270 0.0038 0.0006 1.0000
6.250 0.7568 0.00754 0.00288 0.0043 0.0006 1.0000
6.500 0.7824 0.00771 0.00304 0.0047 0.0006 1.0000
6.750 0.8084 0.00789 0.00321 0.0050 0.0007 1.0000
7.000 0.8345 0.00806 0.00343 0.0053 0.0008 1.0000
7.250 0.8608 0.00825 0.00363 0.0055 0.0009 1.0000
7.500 0.8876 0.00843 0.00384 0.0057 0.0012 1.0000
8.000 0.9420 0.00879 0.00424 0.0059 0.0018 1.0000
8.500 0.9957 0.00942 0.00498 0.0062 0.0023 1.0000
8.750 1.0220 0.00989 0.00554 0.0063 0.0022 1.0000
9.000 1.0470 0.01066 0.00646 0.0066 0.0020 1.0000
10.250 1.1728 0.01340 0.00942 0.0070 0.0011 1.0000
10.500 1.1969 0.01405 0.01012 0.0072 0.0010 1.0000
10.750 1.2207 0.01471 0.01082 0.0073 0.0009 1.0000
11.000 1.2442 0.01538 0.01154 0.0074 0.0008 1.0000
11.250 1.2673 0.01608 0.01229 0.0076 0.0007 1.0000
11.500 1.2895 0.01689 0.01316 0.0079 0.0006 1.0000
11.750 1.3095 0.01799 0.01436 0.0083 0.0005 1.0000
12.000 1.3249 0.01967 0.01620 0.0090 0.0005 1.0000
12.250 1.3329 0.02215 0.01890 0.0102 0.0004 1.0000
12.500 1.3267 0.02595 0.02302 0.0118 0.0004 1.0000
|
Polar data table (+)
Polar graphs
<< Back to PW75 (pw75-pw)