vent  \; relatif

\vec{R_{z}}

\vec{R_{a}}

\vec{R_{x}}

\vec{P}

\vec{T}

\vec{P_{//}}

\vec{P_{⊥}}

R_{z}=P_{⊥} \; et \; T=R_{x} \; + \; P_{//}

L'avion est en montée rectiligne 
à vitesse constante (MRU)

R_{z}=P_{⊥} \; et \; T=P_{//} \; - \; R_{x}

L'avion est en descente rectiligne 
à vitesse constante (MRU)

R_{z}=P \; et \; T=R_{x}

L'avion vole en palier à vitesse constante (MRU)

Vitesse

afficher les intensités des forces

γ

\vec{R_{a}}=\vec{R_{z}}+\vec{R_{x}}

\vec{P}=\vec{P_{⊥}}+\vec{P_{//}}

afficher la portance et la trainée

afficher la résultante aérodynamique

afficher le poids

afficher les composantes du poids

Le \; vol \;en \;palier, \;la \;montée \;, \;la \;descente \;à \;vitesse \;constante

α

pente

incidence

m = 680 (slider from 500 to 1500, step 50)
γ = 0.24434609527920614 rad (slider from -20° to 20°, step °)
A = (4.68, 0.46)
C = (10.94, 0.92)
D = (4.68, 2.54)
poly1, a, d, c = Polygon(D, C, A)
G = Centroid(poly1)
G': G + (0.1 * Vector[A, D])
B = Midpoint(A, D)
B': (x(C), y(B))
b = Line(B, B')
b' = Rotate(b, (-γ), G')
P: (9.81 * m)
e = OrthogonalLine(G', b')
N = Point(b')
O = Point(b')
Q = (12.2504, 2.5156)
R = (14.4504, 3.0556)
U = (18.7304, 2.3356)
W = (18.1104, 0.0356)
Z = (12.6304, 0.0156)
u = Vector(N, O)
E = (-1.2496, -7.2844)
F = (25.6904, -7.3244)
p: (5.0E-4 * (0, (-P)))
G_1: G' + p
v = Vector(G', G_1)
f = OrthogonalLine(G', b')
g = OrthogonalLine(G_1, f)
h = OrthogonalLine(G_1, b')
H = Intersect(f, g)
I = Intersect(b', h)
w = Vector(G', H)
i = Vector(G', I)
j: abs(w)
b_1 = Segment(H, G_1)
c_1 = Segment(G_1, I)
R_z = 6430 (slider from 6000 to 7000, step 10)
r_z: (5.0E-4 * R_z)
k = Circle(G', r_z)
J = Intersect(k, e, 2)
l = Vector(G', J)
r_x: (0.5 * r_z)
q = Circle(G', r_x)
K = Intersect(q, b', 2)
n = Vector(G', K)
R_1: G' + l + n
r = Vector(G', R_1)
s = Segment(J, R_1)
T: G' - n - i
u_1 = Vector(G', T)
P_{⊥}: (2000 * abs(w))
texte1: "R_{z}=" + (LaTeX[R_z]) + " \; N"
texte2: "P=" + (LaTeX[P]) + " \; N"
texte3: "P_{⊥}=" + (LaTeX[P_{⊥}]) + " \; N"
P_{//} = If(-0.3°  <  γ  <  0.3°, 0, round((2000 * abs(i))))
texte16: "P_{//}=" + (LaTeX[P_{//}]) + " \; N"
R_x: (ceil((500 * r_x / 10)) * 10)
texte17: "R_{x}=" + (LaTeX[R_x]) + " \; N"
t = If(-0.3°  <  γ  <  0.3°, R_x, If[γ > 0.3°, R_x + P_{//}, abs((-R_x) + P_{//})])
a_1 = Segment(K, R_1)
L = (9.135689256198352, 5.034442975206611)
M = (12.722466115702488, 5.084029752066114)
S = (12.722466115702488, 4.1088231404958675)
V = (9.152218181818187, 4.075765289256198)
A_1 = (1.0695735537190052, -1.6101851239669431)
B_1 = (1.0861024793388399, 5.249319008264462)
o = true
C_1 = Point(b')
D_1 = Point(b)
d_1 = CircleArc(G', C_1, D_1)
E_1 = Point(b)
F_1 = Point(b')
e_1 = CircleArc(G', E_1, F_1)
H_1 = Midpoint(D_1, C_1)
I_1 = Midpoint(E_1, F_1)
f_1 = true
g_1 = false
h_1 = false
i_1 = true
α = 0.1064650843716541 rad (slider from 0 to 10°, step 0.1°)
image1' = Rotate(image1, (-γ) - α, G)
J_1 = Point(b')
K_1 = Rotate(J_1, (-α), G')
β = Angle(K_1, G', J_1)
j_1 = Line(K_1, G')
k_1 = Ray(G', J_1)
l_1 = Ray(G', K_1)
p_1 = CircleArc(G', K_1, J_1)
L_1 = Midpoint(J_1, K_1)
M_1 = (8.805110743801658, -1.907705785123968)
N_1 = (9.747259504132236, -1.2630776859504143)
O_1 = (10.755523966942155, -1.2630776859504143)
P_1 = (11.284449586776866, -2.3209289256198358)
Q_1 = (9.780317355371906, -2.436631404958679)
q_1 = Conic(M_1, N_1, O_1, P_1, Q_1)
S_1 = (11.86296198347108, -1.9242347107438027)
T_1 = (13.102631404958686, -1.1804330578512408)
U_1 = (15.300978512396703, -1.1969619834710754)
V_1 = (16.60676363636365, -2.072995041322315)
W_1 = (14.226598347107446, -2.767209917355373)
r_1 = Conic(S_1, T_1, U_1, V_1, W_1)
t_1: (10 * ceil(t / 10))
texte18: "T=" + (LaTeX[t_1]) + " \; N"