Fundamentals of Aerodynamics 7th
Edition by John D. Anderson — EXAM
STUDY GUIDE 2026/2027 ACCURATE
QUESTIONS WITH CORRECT DETAILED
SOLUTIONS || 100% GUARANTEED PASS
NEWEST VERSION
Description: This revision set covers the core concepts from John D.
Anderson’s Fundamentals of Aerodynamics (7th Edition), spanning fundamental
principles, inviscid incompressible flow, airfoil and finite wing theory, compressible flow,
normal and oblique shocks, and nozzle flows. Keywords: aerodynamics, Anderson,
inviscid flow, airfoil, finite wing, compressible flow, shock waves, boundary layer,
Prandtl-Meyer, normal shock.
Q1. What is the primary source of all aerodynamic forces and moments on a body?
A) Temperature distribution only
B) Pressure and shear stress distributions over the surface ✅
C) Gravity and buoyancy
D) Vorticity in the wake only
Q2. The Reynolds number physically represents the ratio of which two forces?
A) Pressure to viscous forces
B) Inertial to viscous forces ✅
C) Gravitational to inertial forces
D) Elastic to surface tension forces
,Q3. What does the no-slip condition state at a solid surface?
A) Velocity is maximum at the wall
B) Velocity is zero at the wall ✅
C) Pressure equals freestream pressure
D) Temperature gradient is zero
Q4. Which equation represents the conservation of mass for a fluid element?
A) Momentum equation
B) Energy equation
C) Continuity equation ✅
D) Bernoulli equation
Q5. The momentum equation applied to a steady, inviscid flow with no body
forces yields which equations?
A) Navier-Stokes equations
B) Euler equations ✅
C) Laplace equation
D) Heat equation
Q6. For a two-dimensional body, the drag per unit span can be calculated from a
wake survey using which expression?
A) D′ = ρ ∫ u₁(u₁ − u₂) dy ✅
B) D′ = ρ ∫ (u₁ − u₂)² dy
C) D′ = ½ ρ ∫ u₂² dy
D) D′ = ρ u₁ u₂
Q7. What is dynamic pressure defined as?
A) q = ρV
B) q = ½ ρV² ✅
C) q = ρV²
D) q = ½ ρV
, Q8. The lift coefficient is defined as:
A) CL = L / (qS) ✅
B) CL = L / (q²S)
C) CL = LqS
D) CL = L / (ρVS)
Q9. A cambered airfoil generates lift at zero angle of attack because:
A) It has no pressure difference
B) The camber creates an asymmetric pressure distribution ✅
C) Viscosity alone produces lift
D) The trailing edge is sharp
Q10. The Kutta condition states that:
A) Flow leaves the trailing edge smoothly with finite velocity ✅
B) Flow separates at the leading edge
C) Circulation is always zero
D) Pressure at the trailing edge equals freestream
Q11. Thin airfoil theory predicts that the lift slope for a symmetric airfoil is:
A) 2π per radian ✅
B) π per radian
C) 4π per radian
D) 0.5π per radian
Q12. The aerodynamic center of an airfoil is the point about which:
A) Lift is always zero
B) Pitching moment is independent of angle of attack ✅
C) Drag is minimum
D) Center of pressure is fixed
Q13. For a cambered airfoil, the zero-lift angle of attack is:
A) Always zero
B) Positive
Edition by John D. Anderson — EXAM
STUDY GUIDE 2026/2027 ACCURATE
QUESTIONS WITH CORRECT DETAILED
SOLUTIONS || 100% GUARANTEED PASS
NEWEST VERSION
Description: This revision set covers the core concepts from John D.
Anderson’s Fundamentals of Aerodynamics (7th Edition), spanning fundamental
principles, inviscid incompressible flow, airfoil and finite wing theory, compressible flow,
normal and oblique shocks, and nozzle flows. Keywords: aerodynamics, Anderson,
inviscid flow, airfoil, finite wing, compressible flow, shock waves, boundary layer,
Prandtl-Meyer, normal shock.
Q1. What is the primary source of all aerodynamic forces and moments on a body?
A) Temperature distribution only
B) Pressure and shear stress distributions over the surface ✅
C) Gravity and buoyancy
D) Vorticity in the wake only
Q2. The Reynolds number physically represents the ratio of which two forces?
A) Pressure to viscous forces
B) Inertial to viscous forces ✅
C) Gravitational to inertial forces
D) Elastic to surface tension forces
,Q3. What does the no-slip condition state at a solid surface?
A) Velocity is maximum at the wall
B) Velocity is zero at the wall ✅
C) Pressure equals freestream pressure
D) Temperature gradient is zero
Q4. Which equation represents the conservation of mass for a fluid element?
A) Momentum equation
B) Energy equation
C) Continuity equation ✅
D) Bernoulli equation
Q5. The momentum equation applied to a steady, inviscid flow with no body
forces yields which equations?
A) Navier-Stokes equations
B) Euler equations ✅
C) Laplace equation
D) Heat equation
Q6. For a two-dimensional body, the drag per unit span can be calculated from a
wake survey using which expression?
A) D′ = ρ ∫ u₁(u₁ − u₂) dy ✅
B) D′ = ρ ∫ (u₁ − u₂)² dy
C) D′ = ½ ρ ∫ u₂² dy
D) D′ = ρ u₁ u₂
Q7. What is dynamic pressure defined as?
A) q = ρV
B) q = ½ ρV² ✅
C) q = ρV²
D) q = ½ ρV
, Q8. The lift coefficient is defined as:
A) CL = L / (qS) ✅
B) CL = L / (q²S)
C) CL = LqS
D) CL = L / (ρVS)
Q9. A cambered airfoil generates lift at zero angle of attack because:
A) It has no pressure difference
B) The camber creates an asymmetric pressure distribution ✅
C) Viscosity alone produces lift
D) The trailing edge is sharp
Q10. The Kutta condition states that:
A) Flow leaves the trailing edge smoothly with finite velocity ✅
B) Flow separates at the leading edge
C) Circulation is always zero
D) Pressure at the trailing edge equals freestream
Q11. Thin airfoil theory predicts that the lift slope for a symmetric airfoil is:
A) 2π per radian ✅
B) π per radian
C) 4π per radian
D) 0.5π per radian
Q12. The aerodynamic center of an airfoil is the point about which:
A) Lift is always zero
B) Pitching moment is independent of angle of attack ✅
C) Drag is minimum
D) Center of pressure is fixed
Q13. For a cambered airfoil, the zero-lift angle of attack is:
A) Always zero
B) Positive
