Aero 321 Final Exam 45 Questions with Verified Answers,100% CORRECT

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Aero 321 Final Exam 45 Questions with Verified Answers Equation of motion assumptions ( &when bad) - CORRECT ANSWER All internal forces are in equilibrium Constant gravity (bad for orbit) Flat ea... rth (bad for long flights) Constant mass(bad for rockets) Rigid body( bad for supersonic cruisers) Inertial Coupling - CORRECT ANSWER -Results from imbalances in inertia -Start with pitching equation, rearrange for pitch acceleration Gyroscopic Coupling - CORRECT ANSWER Spinning rotors, reduced with counter rotating. Large effect on yaw moment Roll Inertial and body - CORRECT ANSWER Φ Inertial (what you see) P Body (what you feel) Pitch Inertial and body - CORRECT ANSWER Θ Inertial (what you see) Q Body (what you feel) Yaw Inertial and body - CORRECT ANSWER Ψ Inertial (what you see) R Body (what you feel) Center of Pressure vs Aerodynamic Center - CORRECT ANSWER AC is CG location for Cmα=0 CP = AC on symmetric airfoil CP = CG location for Cm=0 Forget-Me-Not Equation - CORRECT ANSWER Cmα= CLα(XbarCG- XbarAC) Static Margin - CORRECT ANSWER SM= (XbarAC-XbarCG)×100% SM>0 Stable SM=0 Neutral stable SM<0 Unstable Shift of CG and AC when control surfaces are added or removed - CORRECT ANSWER Canards Move AC Forward, less stable Horizontal tail moves AC back more stable Fuselage contribution to AC shift - CORRECT ANSWER Wings back = more shift of AC 4 cases for Cm0 Cmα - CORRECT ANSWER Cmα>0 unstable Cm0 Trim when x intercept is positive Negative Static Stability Derivatives and names (C<0) - CORRECT ANSWER CLβ Dihedreal effect Cyβ Cmq Cmα CLp Cnr Positive Static Stability Derivatives and names (C>0) - CORRECT ANSWER Cnβ WeatherCock CLα Lift Curve Relative order of importance for classical derivatives - CORRECT ANSWER Airframe stability Damping Control Power Relative order of importance for modern fly by wire derivatives - CORRECT ANSWER Control Power Static Aerodynamic Dynamic Aerodynamic Evaluation of Derivatives - CORRECT ANSWER *Analytically* Direct Calculation Perturbation of nonlinear Parameter and system identification *Experimental* Wind tunnel Flight test Wing Orientation - CORRECT ANSWER Dihedral effect -CLβ Wing angle( upward= more negative) Wing position(top of fuselage= more negative) Wing swing Differential Eq to State Space - CORRECT ANSWER Dif eq to matrix Dif eq to Transform - CORRECT ANSWER Dif eq to Laplace Characteristic Equation - CORRECT ANSWER S²+2ζωS+ω²= Longitudinal Dynamic Modes - CORRECT ANSWER Phugoid- Throttle Short Period- Pitching Third Oscillary- Aft CG LateralDynamic Modes - CORRECT ANSWER Dutch Roll Spiral Lateral Phugoid Identify modes of transfer function - CORRECT ANSWER Short Period- Bigger Numbers Phugoid- Smaller Classes of planes - CORRECT ANSWER 1 Small, Cesna 2 Med, Tactical bomber 3 Larger, B-2, Commerical 4 Fighter, Manuverable Flight Phase Category - CORRECT ANSWER A-nonterminal, precision tracking B-nonterminal, gradual manuvering C-Terminal, Takeoff and landing Flight Levels - CORRECT ANSWER 1 Clearly adequate for mission 2 increase workload 3 excessive workload, failures Cooper-Harper Scale - CORRECT ANSWER 1Good 10 Bad First proposed modeling of Aerodynamic forces and moments in terms of stability - CORRECT ANSWER G.H. Bryan 1911 NACA, What is, When created, Purpose - CORRECT ANSWER National Advisory Committee for Aeronautics 1915 Ensure U.S.A would stay ahead of competition. Develop methods to determine what makes planes dynamically and statically stable First systematic study on effect of gust on airplane and when - CORRECT ANSWER E.B. Wilson 1915 Datcom first report - CORRECT ANSWER 1938 Multhopp Method, Wing Fuselage interfence, Who published first when - CORRECT ANSWER M. Munk 1923 When Laplace Transforms first used in stability and control literature - CORRECT ANSWER 1950 When did Cooper-Harper rating scale come out - CORRECT ANSWER 1969 Last year of historical development in Roskam paper - CORRECT ANSWER 1980 Constant mass is a good assumption as long as change of mass is small in - CORRECT ANSWER 1 minute Gravity is present in the translational equations but not the rotational equations because - CORRECT ANSWER Gravity acts through the aircraft center of mass Two class 1 methods for estimating aircraft inertias - CORRECT ANSWER Regression plots Radii of Gyration Bf109 the gyroscopic effect is most prominent in - CORRECT ANSWER Yaw After an aircraft is designed, the engineer can choose the location of the - CORRECT ANSWER Center of gravity Which reduces static lateral stability of an airplane - CORRECT ANSWER Anhedral wing Side area is added to the back of the P-51 to make it - CORRECT ANSWER More Stable in Yaw The derivative that needs to be positive for a statically stable airplane is - CORRECT ANSWER Weathercock stability Aircraft models are inaccurate for two common flight conditions - CORRECT ANSWER Transonic and high angle of attack [Show More]

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