Esami svolti Aerodinamica e gestione termica del veicolo

3D

R = 2m β = 4m b = 1,6m ur = 60 m/s

ΘS = 60°

prato ho c_d = 1,4 ⋅ ΘS ρ_std = ρ_o Ψ = 360°/Θ

1. D' σ std turbolibre = C_F1 2Rbθβρu = 17 N

Re = 1,066 ⋅ 10⁶

C_F1 = 1,00074/√Re = 0,00829

2. W_rel specchio

w_s = σ/sub>z/dθ = σ/sub>υ/dθ = 7,473 ⋅ 10^-5

6(x - 1) = 5 - x = 0,3263

3. Δ'p nelle zone a barra

cpos: 1 - 4σ = 95% = 2

4. Dire zone a barra = $Barra - Zona cbe‘ zone = 2

3 = 530N

5. Velocita con Bernoulli il valore di velocità in P serv

p_tabl + h + v - P_tab = g: 0 Q = v = ρ_s = o

cσ = c - ρs = v - h²

4y ^29/30 = 66,53 m²

21/02/23 400 Epic

Profilo numerico C = 0.3 m L = 1.2 m V = 60 m/s Re = 753378 a_s = 15 BL: TURB Blasius

1. z/c 2.0 Xr/c>x>1 Cf = 0.0375 Re^-1/5 = 0.005
2. Casi α=5° For CL=1: q_cl'[h_lc]² - 0.4 q_lc_lc + 0.5 cize: teoria profili neutri - z/c > 0.5

13/03/23 58 4208

Profilo simul. C=1.2 m c=0.2 Lind 40: e=44 m/s n=74631

Ap[1/2]= 2ρv0[1-ξ/c]= Appross. con bordo pieno

Ht^' = 2ρv0∫p n ξ/c ds = ∫p.pro n m×ds = ΔP1I1 cos α = 2ρv0 cos α ∫ 1- ξ/c dz = 2ρv0 cos α [z-T²/2c 0]=

2ρv0 cos α c/2 = 1306 N/m

1. z/c 2.0: L¹ = 1306 = C_L×a_L a_Lind 1.2.0.2.1
2. M 1_T E= 1_L SDR CAM NCO

M_ldet = 9cm E_y y 9λο C_c xii 575.6 N

(f - ξ/c e) [ΔP ds] = [1 + ξ dp/di] = {[ξ/c 0] = [c-ξ²/2 0] f ∫ 0 c = c/ξp ∫ 0 e/c x/c

M.sub = 9ζ0 C/2 =[: 1140,1 X/]

ES. 5/M 20 p 90

φ = 32500 Re

μ = 250 m/s

y = 6 mm

l = 25 m

σ_st = 735

leakrat = 3/4

m = 8.2 · 10^-3 kg

CD_10⁶ = 0.0285

CD_forebody = 0.03

Cf = 0.075 Re

1) Dg leakrat =? Cf = 0.005847 • 0.6 • 250² • 24 5² • 48.75 · 10³

= 0.7311

Re = _{μ l}/^3/4_c = 3215000 turbolento

Cf = 0.005847

2) CD₈ =?

CD_b = 0.0270

CD_x = 0.005847

CD_∞ 0.25 cd bf

CD_tot = Cf + CD + CD_b = cd = CD_∞ + CD_f

D = Cd • ρ • y_∞ • S = 0.253

D_tot = _{ψ_OC} CD_10⁶ r²₀ = 0.318 N

Dt_gas = ȳ ∞ r² • CD_f = 0.253 N

D_base = D_tot + D₀₆ - D_fgc. = 0.338 N

D_sure = -Cpbase Q_∞ r_∞ = CP =

_EP/^{CD_bcp = CD_b}

= 0.290 CD₄