-
Notifications
You must be signed in to change notification settings - Fork 40
/
performance_modeling_output.txt
127 lines (101 loc) · 3.12 KB
/
performance_modeling_output.txt
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
110
111
112
113
114
115
116
117
118
119
120
121
122
123
124
125
126
Cost
----
Wfuel[0]
Constraints
-----------
Mission
"definition of Wburn":
Wfuel[:-1] >= Wfuel[1:] + Wburn[:-1]
"require fuel for the last leg":
Wfuel[3] >= Wburn[3]
FlightSegment
AircraftP
"fuel burn rate":
Wburn[:] >= 0.1·D[:]
"lift":
Aircraft.W + Wfuel[:] <= 0.5·rho[:]·CL[:]·S·V[:]²
"performance":
WingAero
"definition of D":
D[:] >= 0.5·rho[:]·V[:]²·CD[:]·S
"definition of Re":
Re[:] = rho[:]·V[:]·c/mu[:]
"drag model":
CD[:] >= 0.074/Re[:]^0.2 + CL[:]²/π/A/e[:]
FlightState
(no constraints)
Aircraft
"definition of W":
Aircraft.W >= Aircraft.Fuselage.W + Aircraft.Wing.W
"components":
Fuselage
(no constraints)
Wing
"definition of mean chord":
c = (S/A)^0.5
"parametrization of wing weight":
Aircraft.Wing.W >= S·Aircraft.Wing.rho
Optimal Cost
------------
1.091
Free Variables
--------------
| Aircraft
W : 144.1 [lbf] weight
| Aircraft.Wing
S : 44.14 [ft²] surface area
W : 44.14 [lbf] weight
c : 1.279 [ft] mean chord
| Mission.FlightSegment.AircraftP
Wburn : [ 0.274 0.273 0.272 0.272 ] [lbf] segment fuel burn
Wfuel : [ 1.09 0.817 0.544 0.272 ] [lbf] fuel weight
| Mission.FlightSegment.AircraftP.WingAero
D : [ 2.74 2.73 2.72 2.72 ] [lbf] drag force
Variable Sensitivities
----------------------
| Aircraft.Fuselage
W : +0.97 weight
| Aircraft.Wing
A : -0.67 aspect ratio
rho : +0.43 areal density
Next Most Sensitive Variables
-----------------------------
| Mission.FlightSegment.AircraftP.WingAero
e : [ -0.18 -0.18 -0.18 -0.18 ] Oswald efficiency
| Mission.FlightSegment.FlightState
V : [ -0.22 -0.21 -0.21 -0.21 ] true airspeed
rho : [ -0.12 -0.11 -0.11 -0.11 ] air density
Most Sensitive Constraints
--------------------------
| Aircraft
+1.4 : .W >= .Fuselage.W + .Wing.W
| Mission
+1 : Wfuel[0] >= Wfuel[1] + Wburn[0]
+0.75 : Wfuel[1] >= Wfuel[2] + Wburn[1]
+0.5 : Wfuel[2] >= Wfuel[3] + Wburn[2]
| Aircraft.Wing
+0.43 : .W >= S·.rho
Insensitive Constraints |below +1e-05|
--------------------------------------
(none)
Solution Diff (for selected variables)
======================================
(positive means the argument is smaller)
Constraint Differences
**********************
--- removed in argument
+++ added in argument
@@ -41,4 +41,3 @@
c = (S/A)^0.5
"parametrization of wing weight":
Aircraft.Wing.W >= S·Aircraft.Wing.rho
-Wburn[:] >= 0.2·D[:]
**********************
Relative Differences |above 1%|
-------------------------------
Wburn : [ +102.1% +101.6% +101.1% +100.5% ] segment fuel burn
Wfuel : [ +101.3% +101.1% +100.8% +100.5% ] fuel weight
D : [ +1.1% - - - ] drag force
Sensitivity Differences |above 0.1|
-----------------------------------
The largest is -0.00451643.