Joukovsky f=0% t=9% (joukowsk0009-jf) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: Joukovsky f=0% t=9% (joukowsk0009-jf) Reynolds number: 50,000 Max Cl/Cd: 25.66 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-joukowsk0009-jf-50000-n5.txt Download as CSV file: xf-joukowsk0009-jf-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: Joukovsky f=0% t=9%
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
------ -------- --------- --------- -------- -------- --------
-10.250 -0.7680 0.08649 0.07946 0.0059 1.0000 0.0583
-10.000 -0.8509 0.06953 0.06217 -0.0099 1.0000 0.0545
-9.750 -0.8646 0.06462 0.05708 -0.0114 1.0000 0.0547
-9.500 -0.8667 0.06054 0.05284 -0.0121 1.0000 0.0555
-9.250 -0.8664 0.05647 0.04853 -0.0126 1.0000 0.0563
-9.000 -0.8622 0.05262 0.04439 -0.0128 1.0000 0.0574
-8.750 -0.8537 0.04922 0.04070 -0.0128 1.0000 0.0593
-8.500 -0.8434 0.04583 0.03688 -0.0127 1.0000 0.0624
-8.250 -0.8313 0.04220 0.03258 -0.0125 1.0000 0.0655
-8.000 -0.8131 0.03947 0.02969 -0.0121 1.0000 0.0683
-7.750 -0.7933 0.03728 0.02728 -0.0117 1.0000 0.0722
-7.500 -0.7727 0.03497 0.02446 -0.0112 1.0000 0.0782
-7.250 -0.7511 0.03312 0.02265 -0.0107 1.0000 0.0835
-7.000 -0.7281 0.03128 0.02047 -0.0101 1.0000 0.0911
-6.750 -0.7060 0.02976 0.01899 -0.0096 1.0000 0.0998
-6.500 -0.6830 0.02820 0.01731 -0.0090 1.0000 0.1098
-6.250 -0.6601 0.02685 0.01591 -0.0084 1.0000 0.1236
-6.000 -0.6371 0.02554 0.01461 -0.0079 1.0000 0.1401
-5.750 -0.6139 0.02432 0.01338 -0.0074 1.0000 0.1624
-5.500 -0.5908 0.02319 0.01230 -0.0069 1.0000 0.1905
-5.250 -0.5678 0.02213 0.01143 -0.0065 1.0000 0.2240
-5.000 -0.5443 0.02123 0.01065 -0.0060 1.0000 0.2647
-4.750 -0.5206 0.02046 0.01003 -0.0055 1.0000 0.3089
-4.500 -0.4968 0.01981 0.00949 -0.0049 1.0000 0.3542
-4.250 -0.4731 0.01926 0.00906 -0.0041 1.0000 0.3987
-4.000 -0.4495 0.01880 0.00871 -0.0031 1.0000 0.4415
-3.750 -0.4260 0.01840 0.00841 -0.0020 1.0000 0.4819
-3.500 -0.4023 0.01804 0.00811 -0.0009 1.0000 0.5211
-3.250 -0.3788 0.01772 0.00787 0.0004 1.0000 0.5579
-3.000 -0.3553 0.01742 0.00763 0.0016 1.0000 0.5943
-2.750 -0.3322 0.01715 0.00744 0.0031 1.0000 0.6279
-2.500 -0.3094 0.01690 0.00724 0.0046 1.0000 0.6609
-2.250 -0.2870 0.01666 0.00708 0.0062 1.0000 0.6934
-2.000 -0.2649 0.01644 0.00693 0.0079 1.0000 0.7255
-1.750 -0.2433 0.01623 0.00678 0.0096 1.0000 0.7578
-1.500 -0.2217 0.01603 0.00665 0.0113 1.0000 0.7906
-1.250 -0.1991 0.01584 0.00655 0.0128 1.0000 0.8238
-1.000 -0.1731 0.01569 0.00646 0.0136 1.0000 0.8584
-0.750 -0.1407 0.01556 0.00637 0.0129 1.0000 0.8950
-0.500 -0.0978 0.01546 0.00629 0.0099 1.0000 0.9307
-0.250 -0.0479 0.01536 0.00620 0.0051 1.0000 0.9655
0.000 0.0000 0.01528 0.00613 0.0000 1.0000 1.0000
0.250 0.0479 0.01537 0.00620 -0.0051 0.9654 1.0000
0.500 0.0979 0.01546 0.00629 -0.0099 0.9307 1.0000
0.750 0.1407 0.01556 0.00637 -0.0129 0.8950 1.0000
1.000 0.1731 0.01568 0.00646 -0.0136 0.8584 1.0000
1.250 0.1991 0.01584 0.00655 -0.0128 0.8238 1.0000
1.500 0.2217 0.01603 0.00665 -0.0113 0.7906 1.0000
1.750 0.2433 0.01623 0.00678 -0.0096 0.7578 1.0000
2.000 0.2650 0.01644 0.00693 -0.0079 0.7256 1.0000
2.250 0.2870 0.01666 0.00708 -0.0062 0.6933 1.0000
2.500 0.3095 0.01690 0.00724 -0.0046 0.6609 1.0000
2.750 0.3323 0.01715 0.00744 -0.0031 0.6278 1.0000
3.000 0.3553 0.01742 0.00763 -0.0016 0.5943 1.0000
3.250 0.3788 0.01772 0.00787 -0.0004 0.5579 1.0000
3.500 0.4023 0.01804 0.00811 0.0009 0.5211 1.0000
3.750 0.4260 0.01840 0.00841 0.0020 0.4819 1.0000
4.000 0.4496 0.01880 0.00871 0.0031 0.4414 1.0000
4.250 0.4731 0.01926 0.00906 0.0041 0.3987 1.0000
4.500 0.4968 0.01981 0.00949 0.0049 0.3541 1.0000
4.750 0.5207 0.02046 0.01003 0.0055 0.3089 1.0000
5.000 0.5443 0.02123 0.01065 0.0060 0.2647 1.0000
5.250 0.5678 0.02213 0.01143 0.0065 0.2240 1.0000
5.500 0.5908 0.02319 0.01230 0.0069 0.1904 1.0000
5.750 0.6139 0.02432 0.01338 0.0074 0.1624 1.0000
6.000 0.6371 0.02554 0.01461 0.0079 0.1402 1.0000
6.250 0.6601 0.02685 0.01591 0.0085 0.1236 1.0000
6.500 0.6829 0.02820 0.01731 0.0090 0.1098 1.0000
6.750 0.7059 0.02975 0.01898 0.0096 0.0998 1.0000
7.000 0.7280 0.03128 0.02046 0.0102 0.0912 1.0000
7.250 0.7510 0.03312 0.02264 0.0107 0.0835 1.0000
7.500 0.7726 0.03497 0.02446 0.0112 0.0782 1.0000
7.750 0.7931 0.03727 0.02727 0.0117 0.0722 1.0000
8.000 0.8130 0.03947 0.02968 0.0122 0.0683 1.0000
8.250 0.8311 0.04218 0.03256 0.0125 0.0656 1.0000
8.500 0.8432 0.04582 0.03687 0.0128 0.0624 1.0000
8.750 0.8534 0.04922 0.04069 0.0128 0.0594 1.0000
9.000 0.8620 0.05259 0.04436 0.0128 0.0574 1.0000
9.250 0.8663 0.05643 0.04849 0.0126 0.0563 1.0000
9.500 0.8663 0.06054 0.05284 0.0121 0.0555 1.0000
9.750 0.8637 0.06468 0.05715 0.0114 0.0548 1.0000
10.000 0.8509 0.06950 0.06213 0.0100 0.0545 1.0000
10.250 0.7686 0.08643 0.07940 -0.0058 0.0583 1.0000
|
Polar data table (+)
Polar graphs
<< Back to Joukovsky f=0% t=9% (joukowsk0009-jf)