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simpleflight_output.txt
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simpleflight_output.txt
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SINGLE
======
Cost
----
303.1 [N]
Free Variables
--------------
A : 8.46 aspect ratio
C_D : 0.02059 Drag coefficient of wing
C_L : 0.4988 Lift coefficent of wing
C_f : 0.003599 skin friction coefficient
D : 303.1 [N] total drag force
Re : 3.675e+06 Reynold's number
S : 16.44 [m²] total wing area
V : 38.15 [m/s] cruising speed
W : 7341 [N] total aircraft weight
W_w : 2401 [N] wing weight
Most Sensitive
--------------
W_0 : +1 aircraft weight excluding wing
e : -0.48 Oswald efficiency factor
(\frac{S}{S_{wet}}) : +0.43 wetted area ratio
k : +0.43 form factor
V_{min} : -0.37 takeoff speed
Tightest Constraints
--------------------
+1.3 : W >= W_0 + W_w
+1 : C_D >= (CDA0)/S + k·C_f·(\frac{S}{S_{wet}}) + C_L²/(π·A·e)
+1 : D >= 0.5·\rho·S·C_D·V²
+0.96 : W <= 0.5·\rho·S·C_L·V²
+0.43 : C_f >= 0.074/Re^0.2
Solution difference
===================
(positive means the argument is smaller)
Relative differences >1%
------------------------
The largest is +0%.
Sensitivity differences >0.1
----------------------------
The largest is +0.
SWEEP
=====
Cost
----
[ 338 396 294 326 ] [N]
Sweep Variables
---------------
V : [ 45 55 45 55 ] [m/s] cruising speed
V_{min} : [ 20 20 25 25 ] [m/s] takeoff speed
Free Variables
--------------
A : [ 6.2 4.77 8.84 7.16 ] aspect ratio
C_D : [ 0.0146 0.0123 0.0196 0.0157 ] Drag coefficient of wing
C_L : [ 0.296 0.198 0.463 0.31 ] Lift coefficent of wing
C_f : [ 0.00333 0.00314 0.00361 0.00342 ] skin friction coefficient
D : [ 338 396 294 326 ] [N] total drag force
Re : [ 5.38e+06 7.24e+06 3.63e+06 4.75e+06 ] Reynold's number
S : [ 18.6 17.3 12.1 11.2 ] [m²] total wing area
W : [ 6.85e+03 6.4e+03 6.97e+03 6.44e+03 ] [N] total aircraft weight
W_w : [ 1.91e+03 1.46e+03 2.03e+03 1.5e+03 ] [N] wing weight
Most Sensitive
--------------
W_0 : [ +0.92 +0.85 +0.95 +0.85 ] aircraft weight excluding wing
V_{min} : [ -0.82 -1 -0.41 -0.71 ] takeoff speed
V : [ +0.59 +0.97 +0.25 +0.75 ] cruising speed
(\frac{S}{S_{wet}}) : [ +0.56 +0.63 +0.45 +0.54 ] wetted area ratio
k : [ +0.56 +0.63 +0.45 +0.54 ] form factor
Tightest Constraints in last sweep
----------------------------------
+1 : C_D >= (CDA0)/S + k·C_f·(\frac{S}{S_{wet}}) + C_L²/(π·A·e)
+1 : D >= 0.5·\rho·S·C_D·V²
+1 : W >= W_0 + W_w
+0.57 : W <= 0.5·\rho·S·C_L·V²
+0.54 : C_f >= 0.074/Re^0.2
Solution difference
===================
(positive means the argument is smaller)
Relative differences >1%
------------------------
Re : [ +46.4% +97.1% -1.1% +29.2% ] Reynold's number
C_L : [ -40.6% -60.2% -7.2% -37.9% ] Lift coefficent of wing
V : [ +18.0% +44.2% +18.0% +44.2% ] cruising speed
W_w : [ -20.7% -39.3% -15.6% -37.4% ] wing weight
C_D : [ -29.0% -40.4% -5.0% -23.9% ] Drag coefficient of wing
A : [ -26.7% -43.6% +4.5% -15.3% ] aspect ratio
S : [ +12.8% +5.5% -26.5% -32.0% ] total wing area
D : [ +11.5% +30.7% -2.9% +7.5% ] total drag force
V_{min} : [ -9.1% -9.1% +13.6% +13.6% ] takeoff speed
W : [ -6.8% -12.8% -5.1% -12.2% ] total aircraft weight
C_f : [ -7.3% -12.7% - -5.0% ] skin friction coefficient
Absolute differences >0
-----------------------
Re : [ +1.7e+06 +3.6e+06 -4.1e+04 +1.1e+06 ] Reynold's number
W : [ -5e+02 -9.4e+02 -3.8e+02 -9e+02 ] [N] total aircraft weight
W_w : [ -5e+02 -9.4e+02 -3.8e+02 -9e+02 ] [N] wing weight
D : [ +35 +93 -8.8 +23 ] [N] total drag force
V : [ +6.8 +17 +6.8 +17 ] [m/s] cruising speed
S : [ +2.1 +0.9 -4.4 -5.3 ] [m²] total wing area
V_{min} : [ -2 -2 +3 +3 ] [m/s] takeoff speed
A : [ -2.3 -3.7 +0.38 -1.3 ] aspect ratio
C_L : [ -0.2 -0.3 -0.036 -0.19 ] Lift coefficent of wing
C_D : [ -0.006 -0.0083 -0.001 -0.0049 ] Drag coefficient of wing
C_f : [ -0.00026 -0.00046 +8e-06 -0.00018 ] skin friction coefficient
Sensitivity differences >0.1
----------------------------
V : [ +0.59 +0.97 +0.25 +0.75 ] cruising speed
V_{min} : [ -0.45 -0.67 - -0.34 ] takeoff speed
C_{L,max} : [ -0.23 -0.34 - -0.17 ] max CL with flaps down
e : [ +0.15 +0.25 - +0.19 ] Oswald efficiency factor
W_0 : [ - -0.17 - -0.16 ] aircraft weight excluding wing
\rho : [ - +0.13 - +0.19 ] density of air
(\frac{S}{S_{wet}}) : [ +0.13 +0.20 - +0.11 ] wetted area ratio
k : [ +0.13 +0.20 - +0.11 ] form factor
N_{ult} : [ -0.11 -0.18 - -0.14 ] ultimate load factor
W_{W_{coeff1}} : [ -0.11 -0.18 - -0.14 ] Wing Weight Coefficent 1
\tau : [ +0.11 +0.18 - +0.14 ] airfoil thickness to chord ratio