/
performance_modeling_output.txt
100 lines (80 loc) · 2.45 KB
/
performance_modeling_output.txt
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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/PI/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
Cost
----
1.091 [lbf]
Free Variables
--------------
| Aircraft
W : 144.1 [lbf] weight
| Aircraft.Wing
S : 44.14 [ft**2] 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
Sensitivities
-------------
| Aircraft.Fuselage
W : +0.97 weight
| Aircraft.Wing
A : -0.67 aspect ratio
rho : +0.43 areal density
Next Largest Sensitivities
--------------------------
| 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
Tightest 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
All Loose Constraints
---------------------
No constraints had a sensitivity below +1e-05.