Flight_Sim/f-16_6.7.1.json at main · jkgoates/Flight_Sim · GitHub

1
2
3
4
5
6
7
8
9
10
11
12
13
14
15
16
17
18
19
20
21
22
23
24
25
26
27
28
29
30
31
32
33
34
35
36
37
38
39
40
41
42
43
44
45
46
47
48
49
50
51
52
53
54
55
56
57
58
59
60
61
62
63
64
65
66
67
68
69
70
71
72
73
74
75
76
77
78
79
80
81
82
83
84
85
86
87
88
89
90
91
92
93
94
95
96
97
98
99
100
101
102
103
104
105
106
107
108
109
{
    "simulation": {
        "verbose": false,
        "timestep[s]": 0.01,
        "total_time[s]" : 10.0
    },
    "vehicle": {
        "CG_shift[ft]": [1.0, 0.0, 0.0],
        "mass": {
            "weight[lbf]": 20500.0,
            "Ixx[slug-ft^2]": 9496.0,
            "Iyy[slug-ft^2]": 55814.0,
            "Izz[slug-ft^2]": 63100.0,
            "Ixy[slug-ft^2]": 0.0,
            "Ixz[slug-ft^2]": 982.0,
            "Iyz[slug-ft^2]": 0.0,
            "hx[slug-ft^2/s]": 160.0,
            "hy[slug-ft^2/s]": 0.0,
            "hz[slug-ft^2/s]": 0.0
        },
        "thrust": {
            "xlocation[ft]": [0.0, 0.0, 2.0],
            "T0[lbf]": 29550,
            "a" : 0.84
        },
        "aerodynamics": {
            "reference" : {
                "area[ft^2]": 300.0,
                "longitudinal_length[ft]": 11.32,
                "lateral_length[ft]": 30.0,
                "relative_location[ft]": [-1.0, 0.0, 0.0]
            },
            "coefficients": {
                "CL" : {
                    "0": 0.0535,
                    "alpha": 3.8459,
                    "alphahat": 0.0,
                    "qbar": 29.5,
                    "elevator": 0.5153
                },
                "CS" : {
                    "beta" : -1.1086,
                    "pbar" : -0.0207,
                    "alpha_pbar" : 1.1566,
                    "rbar" : 0.9900,
                    "aileron" : 0.0601,
                    "rudder" : 0.1668
                },
                "CD" : {
                    "L0": 0.0425,
                    "CL1": -0.1154,
                    "CL1_CL1": 0.2427,
                    "CS_CS": 0.8733,
                    "qbar": -1.498,
                    "alpha_qbar": 22.99,
                    "elevator": -0.0006,
                    "alpha_elevator": 0.7084,
                    "elevator_elevator": 0.3251
                },
                "Cl": {
                    "beta": -0.1048,
                    "pbar": -0.3766,
                    "rbar": -0.0206,
                    "alpha_rbar": 1.0114,
                    "aileron": -0.1337,
                    "rudder": 0.0272
                },
                "Cm": {
                    "0": -0.0642,
                    "alpha": 0.0955,
                    "qbar": -5.5,
                    "alphahat": 0.0,
                    "elevator": -0.5926
                },
                "Cn": {
                    "beta": 0.2194,
                    "pbar": -0.0074,
                    "alpha_pbar": -0.0904,
                    "rbar" : -0.4605,
                    "aileron": -0.0379,
                    "alpha_aileron": 0.0922,
                    "rudder": -0.0854
                }
            }

        }
    },
    "initial": {
        "airspeed[ft/s]": 330.0,
        "altitude[ft]": 1000.0,

        "xEuler_angles[deg]": [60.0, 7.694005314345, 0.0],
        "type": "trim",
        "trim": {
            "type": "sct",
            "bank_angle[deg]": 180.0,
            "xxxelevation_angle[deg]": 5.0,
            "xelevation_angle[deg]": 8.153227691712,
            "xxelevation_angle[deg]": 7.694005314345,
            "climb_angle[deg]": 0.0,
            "solver": {
                "finite_difference_step_size": 0.01,
                "relaxation_factor": 0.9,
                "tolerance": 1.0e-12,
                "max_iterations": 100
            }
        }
    }
}