Graduate level ( Masters ) Document Preview: Page 1 of Name HOMEWORK # 4. Due* Thu 25 Oct 2012 ME/AE 510 Advanced Gas Dynamics Total no. pages.. Grade The first three problems, which are from Ch. 9 of J. Andersons text (Modern Compressible Flow, McGraw-Hill, 3rd Edition, 2003), as well as the fourth problem are based on the linearized flow approximation. It is recommended that you also refer to the handout uploaded in the folder Weeks6/7 15Oct2012. Problem 1. Problem 2. Problem 3. Page 2 of Problem 4. Using the linearized flow approximation, we can prove that the drag coefficient of supersonic wings increases with the square of both camber (e) and thickness parameters (d), see Figure 1(b) below. Considering the above fact together with the result of problem 3, what is the ideal airfoil profile of supersonic wings? What are the practical limitations that might prevent the wing design from reaching that ideal? Can some of these limitations be eliminated by using variable wings ? Figure 1 Geometric parameters for supersonic airfoil profile. (a) maximum camber (h) and maximum thickness (t). (b) Dimensionless camber (e=h/c) and thickness (d=t/c) parameters. The angle of attack is a, and c is the cord of the airfoil. GENERAL INSTRUCTIONS: DRAW ALL NECESSARY SCHEMATICS AND LABEL THEM WITH SYMBOLS, VECTORS, COORDINATE SYSTEMS, ETC WRITE ON ONE SIDE OF PAPER SHEET ONLY & START EVERY PROBLEM ON A NEW PAGE UNDERLINE OR FRAME EACH FINAL RESULT PLEASE ATTACH THIS PAGE ON THE FRONT OF YOUR HOMEWORK & STAPLE THE STACK ON THE UPPER LEFT CORNER FILL IN YOUR NAME AND NUMBER OF PAGES YOU ATTACH (NUMBER THEM). *Turn in by the beginning of class (10 am). Attachments: 2012-ME-510-H.pdf; Graduate level ( Masters ) Document Preview: Page 1 of Name HOMEWORK # 4. Due* Thu 25 Oct 2012 ME/AE 510 Advanced Gas Dynamics Total no. pages.. Grade The first three problems, which are from Ch. 9 of J. Andersons text (Modern Compressible Flow, McGraw-Hill, 3rd Edition, 2003), as well as the fourth problem are based on the linearized flow approximation. It is recommended that you also refer to the handout uploaded in the folder Weeks6/7 15Oct2012. Problem 1. Problem 2. Problem 3. Page 2 of Problem 4. Using the linearized flow approximation, we can prove that the drag coefficient of supersonic wings increases with the square of both camber (e) and thickness parameters (d), see Figure 1(b) below. Considering the above fact together with the result of problem 3, what is the ideal airfoil profile of supersonic wings? What are the practical limitations that might prevent the wing design from reaching that ideal? Can some of these limitations be eliminated by using variable wings ? Figure 1 Geometric parameters for supersonic airfoil profile. (a) maximum camber (h) and maximum thickness (t). (b) Dimensionless camber (e=h/c) and thickness (d=t/c) parameters. The angle of attack is a, and c is the cord of the airfoil. GENERAL INSTRUCTIONS: DRAW ALL NECESSARY SCHEMATICS AND LABEL THEM WITH SYMBOLS, VECTORS, COORDINATE SYSTEMS, ETC WRITE ON ONE SIDE OF PAPER SHEET ONLY & START EVERY PROBLEM ON A NEW PAGE UNDERLINE OR FRAME EACH FINAL RESULT PLEASE ATTACH THIS PAGE ON THE FRONT OF YOUR HOMEWORK & STAPLE THE STACK ON THE UPPER LEFT CORNER FILL IN YOUR NAME AND NUMBER OF PAGES YOU ATTACH (NUMBER THEM). *Turn in by the beginning of class (10 am). Attachments: 2012-ME-510-H.pdf
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