This preview has intentionally blurred sections. Sign up to view the full version.View Full Document
Unformatted text preview: AOE 3134 Stability and Control Exam #1 Solutions y p Figure 1: A STOL aircraft. Figure 1 shows a twin-engine, short takeoff and landing aircraft. When flying at 10 , 000 ft 1 at Mach number M = 0 . 370, the two engines generate a combined 4 , 750 lbs of thrust. Mass and geometric parameters include: W = 40 , 000 lbs S = 945 ft 2 ¯ c = 10 . 1 ft b = 96 ft y p = 15 . 6 ft . Stability and control derivatives are given in the following tables, with longitudinal quantities on the left and lateral-directional quantities on the right. Note: Derivatives with respect to angles are per radian . C L ( · ) C m ( · ) α 5.24-0.780 δe 0.465-2.12 q 7.83-35.6 C Y ( · ) C l ( · ) C n ( · ) β-0.362-0.125 0.101 δa 0.000 0.200 0.000 δr 0.233 0.0240-0.107 Problem 1. (50 points) (a) Given that C L = C L α α + C L δe δe C m = C m + C m α α + C m δe δe with C m = 0 . 0120, compute the equilibrium angle of attack and elevator angle. (b) Compute the additional elevator increment Δ δe that would be required for a steady, wings level 2 g pull-up (that is, a pull-up with load factor...
View Full Document
This document was uploaded on 02/05/2012.
- Fall '09