§AERE 355 Homework 2

Sep 25, 2025

§1.

V=0.158Mach V = 0.158 \text{Mach}
δe=0 \delta_e = 0
β=5° \beta = 5 \degree
δr=?, δa=? \delta_r = ?, ~ \delta_a = ?
From table B.1:
Cnβ=−0.071 C_{n_\beta} = -0.071
Cnδr=−0.072 C_{n_{\delta_r}} = -0.072
Cnδa=−0.0035 C_{n_{\delta_a}} = -0.0035
Equations from chapter 2:
Cn=Cnββ+Cnδrδr+Cnδaδa C_n = C_{n_\beta} \beta + C_{n_{\delta_r}} \delta_r + C_{n_{\delta_a}} \delta_a
Cl=Clββ+Clδrδr+Clδaδa C_l = C_{l_\beta} \beta + C_{l_{\delta_r}} \delta_r + C_{l_{\delta_a}} \delta_a
Trim flight:
0=Cnββ+Cnδrδr+Cnδaδa 0 = C_{n_\beta} \beta + C_{n_{\delta_r}} \delta_r + C_{n_{\delta_a}} \delta_a
0=Clββ+Clδrδr+Clδaδa 0 = C_{l_\beta} \beta + C_{l_{\delta_r}} \delta_r + C_{l_{\delta_a}} \delta_a
From Table A.2:
a=1116.45ft/s a = 1116.45ft/s
V=0.158∗1116.45ft/s=176.4ft/s V = 0.158 * 1116.45ft/s = 176.4ft/s