# Aerodynamics Questions and Answers – Nonlifting Flow over Arbitrary Bodies

This set of Aerodynamics Interview Questions and Answers for Experienced people focuses on “Nonlifting Flow over Arbitrary Bodies”.

**1. Is numerical solution of source and vortex panel techniques has revolutionized the analysis of low speed flows?**

**a) True**

b) False

**Explanation**: The analysis of low-speed flows has been revolutionised by the numerical solution of potential flows using both source and vortex panel techniques. The numerical solution’s goal is to present the fundamental concepts of the source panel approach, which is a way for numerically solving non-lifting flows over any arbitrary body.

**2. Is small section of the source sheet can be treated as a distinct source of strength?**

a) False

**b) True**

**Explanation:**An minuscule percentage of the sheet’s strength. This small area of the source sheet can be used as a separate source of strength. The flow is separated from dx by a distance. ‘P’s’ carterian coordinates are (x, y). This is the small area of the strength xds source sheet that generates an infinitesimally small potential.

**3. Is complete velocity potential at point ‘p’ is obtained by entire source sheet from a to b?**

**a) True**

b) False

**Explanation:** The whole velocity potential is determined by integrating from a to b at point p, and it can shift from positive to negative along the sheet, implying that the source sheet is really a combination of line source and line sinks.

**4. Is arbitrary shape body can use in free stream velocity?**

**a) True**

b) False

**Explanation:** The source sheet is used to cover the surface of an arbitrary body whose strength fluctuates in such a way that when the uniform flow and the source sheet work together, the airfoil surface becomes the flow’s stream line.

**5. Why source strength ‘X’ per unit length is constant over a given panel?**

**a) It allows it to varies from one panel to next panel**

b) It does not allow it to varies from one panel to next panel

c) It remains in the same panel

d) The length will be changes from panel to panel

**Explanation:** If there are n panels, keep the source strength ‘X’ per unit length constant over each panel but allow it to change from one to the next. ‘Xn’ is the source panel strength per unit length. As a result, a numerical boundary constraint is applied by determining the midway of each panel.

**6. Is boundary condition is applied at the control point?**

a) False

**b) True**

**Explanation:** At the control sites, the boundary condition is applied since the normal component of the flow velocity is zero. This freestream velocity component is perpendicular to the panel, and ‘n’ is the unit volume of the ith panel directed out of the body.

**7. Is vector (v) is positive when directed away from the body?**

**a) True**

b) False

**Explanation:** Because the control point itself can be the contribution to the j=1 panel, the direction of the outward unit normal vector is positive when directed away from the body, and it is carried out in the denominator at a unique point arises on the ith panel.

**8. What is the normal component of the flow velocity at the rth control point?**

**a) Sum of the freestream**

b) Sum of source line

c) Sum of the sink line

d) Sum of the source and sink line

**Explanation:** At the rth control point, the normal component of the flow velocity is the total of that owing to the free stream and that due to the source panels. The source panel method’s cruse is the boundary condition, which states that this sum must be zero.

**9. Purpose of non-lifting flow over an arbitrary body is _____________**

**a) to find a numerical method**

b) to find a mathematical method

c) to find a lifting body

d) to find a drag body

**Explanation**: The goal of non-lifting flow over arbitrary bodies is to create a numerical approach for a high-speed digital computer to solve the problem. The source panel is the name of the technique. Low-speed flow analysis has been revolutionised by the numerical solution of potential flows using both source and vortex panel techniques.

**10. The combination of elementary flows is to synthesize the flow over this specified body?**

**a) False**

b) True

**Explanation:** The flow across an arbitrary body is determined by the distribution of singularities, which, when combined with a uniform stream, produce the flow. The goal of this basic flow is to demonstrate such a direct method, which is now limited to non-lifting flows.

**11. Is source panel method became the standard aerodynamic tool in industry?**

a) False

**b) True**

**Explanation:** On a high-speed digital computer, the numerical procedure for an adequate solution. This technique is known as the source panel method, and it has been used in industry and most research laboratories since the late 1960s.

The Numerical Source Panel Method for Nonlifting Flows over Arbitrary Bodies. Rather, we want a direct technique, which allows us to specify the geometry of an arbitrary body and solve for the distribution of singularities that, when combined with a uniform stream, produce the flow across the body. The analysis of low-speed flows has been revolutionised by the numerical solution of potential flows using both source and vortex panel techniques. The numerical solution’s goal is to present the fundamental concepts of the source panel approach, which is a way for numerically solving non-lifting flows over any arbitrary body.