This preview shows page 1. Sign up to view the full content.
Unformatted text preview: MAE-02 Introduction to Aerospace Engineering Fall, 2009, Mid-Term Exam Formula Sheet Dynamic Pressure: ( 2 1 2 q V = ) Aerodynamic Loads: ( ) 2 0 (symmetric) 0 (cambered) L L L o L D D D o Mo AC Mo Mo dC L qSC C d C D qSC C C eAR C M qScC C = = = = + = = < Aspect Ratio ( AR ) = b 2 / S Center of Gravity 1 1 1 n n i c g i i i i W W x x W W = = = = Air density (70 o F): 2 4 0.002377 lb-sec /ft Air = 1 hp = 550 lb-ft/sec = 746 Watts PERFORMANCE Altitude effects: SL altitude SL altitude V V = Propeller thrust efficiency: ( T Aircraft = p T engine ) Propeller thrust: sealevel p HP T V = Propeller thrust at altitude: altitude altitude sealevel sealevel T T = Steady level flight ( F M = = ) L W T D = = Thrust Required ( T =D = W/(L/D ) ) Minimum Thrust at Max (L/D): ( L D o C C e A R = ) min 2 Do W C T eAR = max( / ) 4 1 2 L D Do W V S eARC = Maximum and Minimum Speed: 2 / V q...
View Full Document
- Spring '08