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EngineeringComputer ScienceComputer Science questions and answersI am using MATLAB to show the plot of NACA 5-digit airfoil (NACA 23012), below is my unsuccessful MATLAB code, very bad.Question: I am using MATLAB to show the plot of NACA 5-digit airfoil (NACA 23012), below is my unsuccessful MATLAB code, very bad. I am using MATLAB to show the plot of NACA 5-digit airfoil (NACA 23012), below is my unsuccessful MATLAB code, very bad. If you don't know what NACA 5-digit airfoil is, below is an description: I know it's quite complicated, but if anyone can help me write the correct MATLAB code, I will be so appreciated. the plot will look something like this: Show transcribed image textThis question hasn't been solved yet!Previous question Next questionTranscribed image text: 2 11/30/18 2:12 AM C: Users |CHENH5 \Desktoplplot 4.m for f 1:length(x) if x(f) P c dx (f) ((2*M) /(1-P) A2) (P-x(f)) end %upper and lower limits of the theta-atan (dx (f) xu (f)=x(f)-yt(f) *sin (theta); yu (f)-yc(f)tyt (f) *cos (theta) xl (f)=x ( f ) +yt ( f ) *sin ( the ta); yl (f),-ус ( f )-yt(f)"cos (theta); airfoil (xu, yu) ; (xl,yl) end tplot of airfoil plot (xu, yu,'' hold on plot (xl,yl,'r) plot ( x,yc,'g') axis equal Havin prablemm rea ouv Transcribed image text: 2 11/30/18 2:12 AM C: Users |CHENH5 \Desktoplplot 4.m for f 1:length(x) if x(f) P c dx (f) ((2*M) /(1-P) A2) (P-x(f)) end %upper and lower limits of the theta-atan (dx (f) xu (f)=x(f)-yt(f) *sin (theta);
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Question Consider an infinite wing with a NACA 1412 airfoil section and chord length of 3 ft. The wing is at an angle of attack of 5 degrees in an airflow velocity of 100 ft/s at standard sea-level conditions. Calculate the lift, drag, and moment about the quarter chord per unit span: (23.9 lb, 0.25 lb, -2.68 ft·lb)Consider a rectangular wing mounted in a low-speed subsonic wind tunnel. The wing model completely spans the test section so that the flow "sees" essentially an infinite wing. If the wing has a NACA 23012 airfoil section and a chord of 0.3 m, calculate the lift, drag, and moment about the quarter-chord per unit span when the airflow pressure, temperature, and velocity are at atm, 303 K, and 42 m/s respectively. The angle of attack is 8 degrees. (301 N, 3.07 N, -1.1 N·m)The wing model in Problem 2 is now pitched to a new angle of attack, where the lift of the entire wing is measured as 200 N by the wind tunnel balance. If the wingspan is 2, what is the angle of attack? (deg)Consider a rectangular wing with a NACA 0009 airfoil section spanning the test section of a wind tunnel. The test section airflow conditions are standard sea level with a velocity of 120 mph. The wing is at an angle of attack of 4 degrees, and the wind tunnel balance measures a lift of 29.5 lb. What is the area of the wing? (2 ft^2) Consider an infinite wing with a NACA 1412 airfoil section and chord length of 3 ft. The wing is at an angle of attack of 5 degrees in an airflow velocity of 100 ft/s at standard sea-level conditions. Calculate the lift, drag, and moment about the quarter chord per unit span: (23.9 lb, 0.25 lb, -2.68 ft·lb)Consider a rectangular wing mounted in a low-speed subsonic wind tunnel. The wing model completely spans the test section so that the flow "sees" essentially an infinite wing. If the wing has a NACA 23012 airfoil section and a chord of 0.3 m, calculate the lift, drag, and moment about the quarter-chord per unit span when the airflow pressure, temperature, and velocity are at atm, 303 K, and 42 m/s respectively. The angle of attack is 8 degrees. (301 N, 3.07 N, -1.1 N·m)The wing model in Problem 2 is now pitched to a new angle ofNACA 5 digit airfoil generator (NACA AIRFOIL)
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EngineeringComputer ScienceComputer Science questions and answersI am using MATLAB to show the plot of NACA 5-digit airfoil (NACA 23012), below is my unsuccessful MATLAB code, very bad.Question: I am using MATLAB to show the plot of NACA 5-digit airfoil (NACA 23012), below is my unsuccessful MATLAB code, very bad. I am using MATLAB to show the plot of NACA 5-digit airfoil (NACA 23012), below is my unsuccessful MATLAB code, very bad. If you don't know what NACA 5-digit airfoil is, below is an description: I know it's quite complicated, but if anyone can help me write the correct MATLAB code, I will be so appreciated. the plot will look something like this: Show transcribed image textThis question hasn't been solved yet!Previous question Next questionTranscribed image text: 2 11/30/18 2:12 AM C: Users |CHENH5 \Desktoplplot 4.m for f 1:length(x) if x(f) P c dx (f) ((2*M) /(1-P) A2) (P-x(f)) end %upper and lower limits of the theta-atan (dx (f) xu (f)=x(f)-yt(f) *sin (theta); yu (f)-yc(f)tyt (f) *cos (theta) xl (f)=x ( f ) +yt ( f ) *sin ( the ta); yl (f),-ус ( f )-yt(f)"cos (theta); airfoil (xu, yu) ; (xl,yl) end tplot of airfoil plot (xu, yu,'' hold on plot (xl,yl,'r) plot ( x,yc,'g') axis equal Havin prablemm rea ouv Transcribed image text: 2 11/30/18 2:12 AM C: Users |CHENH5 \Desktoplplot 4.m for f 1:length(x) if x(f) P c dx (f) ((2*M) /(1-P) A2) (P-x(f)) end %upper and lower limits of the theta-atan (dx (f) xu (f)=x(f)-yt(f) *sin (theta);
2025-03-28Question Consider an infinite wing with a NACA 1412 airfoil section and chord length of 3 ft. The wing is at an angle of attack of 5 degrees in an airflow velocity of 100 ft/s at standard sea-level conditions. Calculate the lift, drag, and moment about the quarter chord per unit span: (23.9 lb, 0.25 lb, -2.68 ft·lb)Consider a rectangular wing mounted in a low-speed subsonic wind tunnel. The wing model completely spans the test section so that the flow "sees" essentially an infinite wing. If the wing has a NACA 23012 airfoil section and a chord of 0.3 m, calculate the lift, drag, and moment about the quarter-chord per unit span when the airflow pressure, temperature, and velocity are at atm, 303 K, and 42 m/s respectively. The angle of attack is 8 degrees. (301 N, 3.07 N, -1.1 N·m)The wing model in Problem 2 is now pitched to a new angle of attack, where the lift of the entire wing is measured as 200 N by the wind tunnel balance. If the wingspan is 2, what is the angle of attack? (deg)Consider a rectangular wing with a NACA 0009 airfoil section spanning the test section of a wind tunnel. The test section airflow conditions are standard sea level with a velocity of 120 mph. The wing is at an angle of attack of 4 degrees, and the wind tunnel balance measures a lift of 29.5 lb. What is the area of the wing? (2 ft^2) Consider an infinite wing with a NACA 1412 airfoil section and chord length of 3 ft. The wing is at an angle of attack of 5 degrees in an airflow velocity of 100 ft/s at standard sea-level conditions. Calculate the lift, drag, and moment about the quarter chord per unit span: (23.9 lb, 0.25 lb, -2.68 ft·lb)Consider a rectangular wing mounted in a low-speed subsonic wind tunnel. The wing model completely spans the test section so that the flow "sees" essentially an infinite wing. If the wing has a NACA 23012 airfoil section and a chord of 0.3 m, calculate the lift, drag, and moment about the quarter-chord per unit span when the airflow pressure, temperature, and velocity are at atm, 303 K, and 42 m/s respectively. The angle of attack is 8 degrees. (301 N, 3.07 N, -1.1 N·m)The wing model in Problem 2 is now pitched to a new angle of
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2025-04-09