OPTIMIZATION
SUMMARY
NOTE: the summary below highlights only one version of the final design;
all code available below can be run for any version of the Cardinal--including
rejected designs |
FIXED-WING MILITARY VERSION |
Design Variable |
Initial Guess Input |
Optimized Output |
Wing Area |
1035 ft2 |
1150 ft2 |
Wing
Position |
16.5 ft |
15.0 ft |
Horizontal
Tail Area |
225 ft2 |
190 ft2 |
Vertical
Tail Area |
275 ft2 |
208 ft2 |
Thrust |
33000 lb |
22875 lb |
Takeoff
Weight |
46312 lb |
46761 lb |
Cruise
Speed |
350 ktas |
350 ktas |
Cruise
Altitude |
35000 ft |
37000 ft |
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DESIGN
CONSTRAINTS |
CONSTRAINT |
< , > |
BOUND |
Volume |
< |
60 ft l x 29 ft w x 18.5 ft h |
Takeoff
ground roll |
< |
300 ft |
Landing
ground roll |
< |
400 ft |
Cruise Range |
> |
1500 nm |
Center-of-gravity
excursion |
< |
25% mac |
Static
Margin |
> |
5 % mac |
Takeoff
Rotation, Sht |
> |
Sht, required for rotation |
Tipover
Angle |
> |
18 degrees |
Turnover
Angle |
< |
54 degrees |
Fuselage
Clearance Angle |
> |
10 degrees |
Weight on
Nose |
> |
8% |
Minimum
control speed |
> |
1.2*Vstall, landing |
|
|
SUMMARY OF OPTIMIZED CONSTRAINT VALUES
NOTE: the optimal design met all constraints, the "tough" ones are
listed below |
CONSTRAINT |
BOUND |
INITIAL DESIGN |
OPTIMAL DESIGN |
Takeoff ground roll |
< 300 ft |
184 ft |
290 ft |
Landing ground roll |
< 400 ft |
347 ft |
315 ft |
Cruise Range |
> 1500 nm |
960 nm |
1500 nm |
SUMMARY
OF AUTOMATED DESIGN TOOLS
NOTE: all codes must be downloaded to a common directory for successful
operation |
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