Problem Set 3 - 09 Feb 2024-1

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University of Texas, Arlington *

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5302

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Aerospace Engineering

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Feb 20, 2024

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1 MAE 3306 Flight Performance & Stability Spring Semester 2024 Ian Maynard • NH 125A E -Mail: ian.maynard@uta.edu HOMEWORK P ROBLEM S ET 3 D ISTRIBUTED : 09 F EBRUARY 2024 D UE DATE : 19 F EBRUARY 2024 Name: ID: Problem 1 Write a computer program that uses the vortex panel method that was [50%/100%] described in Sec. 1.6, and do the following: (1) Compute and plot the C p vs x/ c pressure distribution on a NACA 2412 airfoil. (2) Generate a table of the section lift coefficient 𝑪 ̃ 𝑳 , section leading edge pitching moment coefficient 𝑪 ̃ ? ?𝒆 , and the section quarter-chord pitching moment coefficient 𝑪 ̃ ? 𝒄/𝟒 as a function of angle of attack 𝜶 from -12° to 16° in 2° increments. (3) Plot 𝑪 ̃ 𝑳 and 𝑪 ̃ ? 𝒄/𝟒 as a function of angle of attack 𝜶 (4) In one plot, plot 𝑪 ̃ 𝑳 vs 𝜶 using thin airfoil theory, plot 𝑪 ̃ 𝑳 vs 𝜶 using the vortex panel method, and plot the experimental NACA 2412 𝑪 ̃ 𝑳 vs 𝜶 data from Fig. 1.6.6. Compare and discuss the results. Notes: Use 100 nodes with 99 panels. Verification Data: Using 100 nodes, at 𝛼 = 2 °, 𝐶 ̃ 𝐿 = 0.50247 , 𝐶 ̃ 𝑚 𝑙𝑒 = −0.18441 , and 𝐶 ̃ 𝑚 𝑐/4 = −0.05887 If you are not matching with these results, set your number of nodes to 12 and check your code’s results with the following: The A matrix for 12 nodes (note that python indexes start at 0, not 1):
2 Vector for solving for gamma (using 12 nodes): Gamma values (using 12 nodes): Summation vector for calculating Vx and Vy (using 12 nodes): This is a matrix of eleven (n-1) 2x1 matrices The upper surface Cp values (using 12 nodes): The lower surface Cp values (using 12 nodes): 𝐶 ̃ 𝐿 summation vector (using 12 nodes):
3 𝐶 ̃ 𝑚 𝐿𝐸 summation vector (using 12 nodes): Problem 2 Using the thin airfoil theory code developed in homework 2 and the vortex [50%/100%] panel method code developed in problem one above, do the following: (1) Digitize the experimental data points from Fig. 1.6.6 for the NACA 2412 using webplotdigitizer . (2) Recreate Fig. 1.6.6: In one plot, plot 𝑪 ̃ 𝑳 vs 𝜶 from -16° to 16° in 2° increments using (a) thin airfoil theory and (b) the vortex panel method for a NACA 2412 airfoil. Also plot the experimental data for the NACA 2412 airfoil. Discuss the results. (3) Digitize the experimental data points from figure 1.6.7 for the NACA 2421 using webplotdigitizer . (4) Recreate Fig. 1.6.7: In one plot, plot 𝑪 ̃ 𝑳 vs 𝜶 from -16° to 16° in 2° increments using (a) thin airfoil theory and (b) the vortex panel method for a NACA 2421 airfoil. Also plot the experimental data for the NACA 2421 airfoil. Discuss the results. (5) Digitize the experimental data points from figure 1.6.8 for the NACA 0015 using webplotdigitizer . (6) Recreate Fig. 1.6.8: In one plot, plot 𝑪 ̃ 𝑳 vs 𝜶 from -16° to 16° in 2° increments using (a) thin airfoil theory and (b) the vortex panel method for a NACA 0015 airfoil. Also plot the experimental data for the NACA 0015 airfoil. Discuss the results. Notes: Use 100 nodes with 99 panels for the vortex panel method
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4 Homework General Requirements: » Use MATLAB, Python, or another programming language to generate the answers and plots for all problems. » Keep the programming codes neat and organized. » Use professional plot formatting when generating plots. » Include all the programming code that you have coded for your homework in your submission. Homework Formatting Requirements: » Use engineering paper for all written solutions » The header should include the student’s last name, then first name, class information (MAE 3306), homework number, date, and page number information » Problem statement summaries are required (no need to rewrite entire problem statement if it is long, just summarize) » List the inputs given, show all work in deriving the solution, and box or highlight all final answers . Plotted answers DO NOT need to be boxed. ---------- o0o ----------