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### Step 1: Thrust Required vs. Velocity Plot

The thrust required at different velocities (200 ft/s, 300 ft/s, and 400 ft/s) has been plotted, and the results are as follows:

- At 200 ft/s: **1322.9 lbf**
- At 300 ft/s: **1040.52 lbf** (This is the minimum thrust required)
- At 400 ft/s: **1270.67 lbf**

### Step 2: Minimum Thrust and Corresponding Velocity
- **Minimum thrust required:** \(1040.52\) lbf
- **Velocity at which it occurs:** \(300\) ft/s

Next, I will proceed with calculating the minimum power required and the other remaining parts of the problem.### Step 3: Minimum Power Required
- **Minimum power required:** \(312,156 \, \text{ft-lbf/s}\)
- **Minimum power required (in horsepower):** \(567.56 \, \text{HP}\)

Next, I will calculate the stalling velocity considering the given wing sweep angle and the remaining parts.### Step 4: Stalling Velocity
- **Stalling Velocity:** \(175.84 \, \text{ft/s}\)

This stalling speed was calculated assuming a typical maximum lift coefficient \((C_{L\text{max}})\) of 1.6.

Now, I'll proceed with calculating \(C_{L\text{max}}\), \(V_{\text{LOmax}}\), \((R/C)_{\text{max}}\), and \(V_{(R/C)_{\text{max}}}\).For the next steps, I need some additional assumptions and details that are usually required to calculate parameters like \(C_{L\text{max}}\), \(V_{\text{LOmax}}\), \((R/C)_{\text{max}}\), and \(V_{(R/C)_{\text{max}}}\). These typically depend on specific aerodynamic properties and conditions that may not be fully specified in the problem.

Would you like to proceed with some standard assumptions, or do you have specific details that should be considered? Additionally, I can continue with the estimation of maximum range and endurance based on available data.

Let me know how you'd like to proceed!

Explore the detailed calculation of thrust and power in aerodynamics. Includes thrust required at different velocities, minimum power calculations, and stalling velocity determination. Suitable for advanced engineering studies.

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