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 twinengine, 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 lateraldirectional quantities on the right. Note: Derivatives with respect to angles are per radian . C L ( · ) C m ( · ) α 5.240.780 δe 0.4652.12 q 7.8335.6 C Y ( · ) C l ( · ) C n ( · ) β0.3620.125 0.101 δa 0.000 0.200 0.000 δr 0.233 0.02400.107 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 pullup (that is, a pullup with load factor...
View
Full
Document
This document was uploaded on 02/05/2012.
 Fall '09

Click to edit the document details