🔬 AERODYNAMICS LAB
KTU · Toms College of Engineering · TCE Mattakara
Aerodynamic Forces & Moments — Symmetrical Aerofoil
q = ½ρV² | CL = L/(q·S) | CD = D/(q·S) | Cm = M/(q·S·c)
Table 1 — Force Measurements
| Sl | α (°) | h₁ | h₂ | V | Lift L (kg) | Drag D (kg) | Side F (kg) | CL | CD | CS |
|---|
Table 2 — Moment Measurements
| Sl | α (°) | Speed | Pitching M | Rolling M | Yawing M | Cm |
|---|
Cm (Pitching Moment Coeff) vs Alpha
Aerodynamic Forces & Moments — Cambered Aerofoil
q = ½ρV² | CL = L/(q·S) | CD = D/(q·S) | Cm = M/(q·S·c)
Table 1 — Force Measurements
| Sl | α (°) | h₁ | h₂ | V | Lift L (kg) | Drag D (kg) | Side F (kg) | CL | CD | CS |
|---|
Table 2 — Moment Measurements
| Sl | α (°) | Speed | Pitching M | Rolling M | Yawing M | Cm |
|---|
Pressure Distribution — Symmetrical Aerofoil
q = h₀−h∞ | ΔP = hᵢ−h∞ | Cp = ΔP/q | Plot: −Cp vs X/C
Pressure Port Readings
| Port | Surface | x/c | h₀ (mm) | h∞ (mm) | hᵢ (mm) | q=h₀−h∞ | ΔP=hᵢ−h∞ | Cp | −Cp |
|---|
−Cp vs X/C — Upper & Lower Surface
Pressure Distribution — Cambered Aerofoil
q = h₀−h∞ | ΔP = hᵢ−h∞ | Cp = ΔP/q | Plot: −Cp vs X/C
Pressure Port Readings
| Port | Surface | x/c | h₀ | h∞ | hᵢ | q | ΔP | Cp | −Cp |
|---|
−Cp vs X/C — Upper & Lower Surface
Pressure Distribution — Smooth Cylinder
Cp = (hᵢ−h∞)/(h₀−h∞) | Theoretical: Cp_th = 1−4sin²θ
Pressure Readings — Smooth Cylinder
| Sl | θ (°) | h₀ | h∞ | hᵢ | q=h₀−h∞ | ΔP=hᵢ−h∞ | Cp=ΔP/q | Cp_th=1−4sin²θ |
|---|
Cp vs θ — Smooth Cylinder: Experimental vs Theoretical
Pressure Distribution — Rough Cylinder
Cp = (hᵢ−h∞)/(h₀−h∞) | Plot: Rough + Smooth (Exp 7) superimposed
⚠ Velocity should match Experiment 7. Run Exp 7 first to see smooth cylinder curve superimposed.
Pressure Readings — Rough Cylinder
Cp vs θ — Rough vs Smooth Cylinder Comparison