/
sp_to_gp_sweep_output.txt
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/
sp_to_gp_sweep_output.txt
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Cost
----
[ 4.63e+03 6.23e+03 7.36e+03 ] [N]
Warnings
========
Unexpectedly Loose Constraints
------------------------------
| for sweep 0 |
0.9585 >= 0.9187 : V_{f_{avail}} >= V_f
| for sweep 1 |
0.9585 >= 0.9187 : V_{f_{avail}} >= V_f
| for sweep 2 |
0.9585 >= 0.9187 : V_{f_{avail}} >= V_f
Sweep Variables
---------------
V_f_wing : [ 0.1 0.3 0.5 ] [m³] fuel volume in the wing
Free Variables
--------------
(CDA0) : [ 0.05 0.05 0.05 ] [m²] fuselage drag area
A : [ 12.4 3.78 2.35 ] aspect ratio
C_D : [ 0.0136 0.011 0.0099 ] drag coefficient
C_L : [ 0.327 0.162 0.121 ] lift coefficient of wing
C_f : [ 0.00343 0.00284 0.00261 ] skin friction coefficient
D : [ 466 774 1e+03 ] [N] total drag force
L/D : [ 24.1 14.8 12.2 ] lift-to-drag ratio
Re : [ 4.64e+06 1.21e+07 1.83e+07 ] Reynold's number
S : [ 22 29.7 35.6 ] [m²] total wing area
T_{flight} : [ 16.6 13.4 12.3 ] [hr] flight time
V : [ 50.3 62.1 67.9 ] [m/s] cruising speed
V_f : [ 0.577 0.777 0.919 ] [m³] fuel volume
V_{f_{avail}} : [ 0.589 0.788 0.958 ] [m³] fuel volume available
W : [ 1.35e+04 1.45e+04 1.59e+04 ] [N] total aircraft weight
W_f : [ 4.63e+03 6.23e+03 7.36e+03 ] [N] fuel weight
W_w : [ 2.65e+03 2.05e+03 2.29e+03 ] [N] wing weight
W_w_strc : [ 1.33e+03 269 151 ] [N] wing structural weight
W_w_surf : [ 1.32e+03 1.78e+03 2.14e+03 ] [N] wing skin weight
Most Sensitive
--------------
Range : [ +1.4 +1.1 +1.2 ] aircraft range
TSFC : [ +1.4 +1.1 +1.2 ] thrust specific fuel consumption
(\frac{S}{S_{wet}}) : [ +0.85 +0.71 +0.74 ] wetted area ratio
k : [ +0.85 +0.71 +0.74 ] form factor
V_{min} : [ -1.4 0 0 ] takeoff speed
Tightest Constraints
(for the last sweep only)
--------------------
+1.2 : C_D >= (CDA0)/S + k·C_f·(\frac{S}{S_{wet}}) + C_L²/(π·A·e)
+1.2 : D >= 0.5·\rho·S·C_D·V²
+1.2 : T_{flight} >= Range/V
+1.2 : W_f >= TSFC·T_{flight}·D
+0.74 : C_f >= 0.074/Re^0.2