The shock waves on a vehicle in supersonic flight cause a component of drag called supersonic wave drag
Want to see the full answer?
Check out a sample textbook solutionChapter 1 Solutions
Fundamentals of Aerodynamics
Additional Engineering Textbook Solutions
Fluid Mechanics: Fundamentals and Applications
Heating Ventilating and Air Conditioning: Analysis and Design
Degarmo's Materials And Processes In Manufacturing
Fox and McDonald's Introduction to Fluid Mechanics
Introduction to Heat Transfer
Thermodynamics: An Engineering Approach
- Helium is heated as it flows subsonically through a 10 cm × 10 cm square duct. The properties of helium at the inlet are maintained at Ma1 = 0.6, P1 = 350 kPa, and T1 = 420 K at all times. Disregarding frictional losses, determine the highest rate of heat transfer to the air in the duct without affecting the inlet conditions.arrow_forward1. a. Consider a low-speed subsonic wind tunnel designed with a reservoir cross-sectional area A1 = 2 m2 and a test-section cross-sectional area A2 = 0.5 m2. The pressure in the test section is P2 = 1 atm. Assume constant density equal to standard sea level density, calculate the pressure (in kPa) required in the reservoir, P1, necessary to achieve a flow velocity V2 = 40 m/s in the test section. b. calculate the mass flow rate (in kg/s) through the wind tunnel.arrow_forwardAn aircraft is flying at supersonic speed. At a component of an aircraft where the flow is perpendicular (normalshock), the density ratio is 5. Solve for: a.Mach Number Downstream b. Pressure Ratio c. Temperature Ratio d. Mach Number upstreamarrow_forward
- An aircraft is flying at supersonic speed. At a component of an aircraft where the flow is perpendicular, the density ratio is 5. Solve for: a.Mach Number Downstream b. Pressure Ratio c. Temperature Ratio d. Mach Number upstreamarrow_forwardAir enters a diffuser with a velocity of 200m/s. Determine the speed of sound in m/s at the diffuser inlet at 30°C. Determine the speed of sound Mach number at the diffuser inlet at 30°C.arrow_forwardTwo war planes travel one above the other at a speed of 3600kmph at two different altitudes. The first one travels at an altitude of 1km above earths surface and the second one travels at an altitude of 11km. The air temperature at 1km altitude is 20°C. The air temperature continuously drops by 6°C for each 1000m altitudes we go up. Determine the Mach number of both aircrafts at their respective altitudes. Assume R = 287 J/kgK; γ=1.4arrow_forward
- From Table A.3, the density of glycerin at standard conditionsis about 1260 kg/m3 . At a very high pressure of 8000 lb/in2 , itsdensity increases to approximately 1275 kg/m3 . Use this datato estimate the speed of sound of glycerin, in ft/s.arrow_forwardThe speed of an aircraft is given to be 950 km/h. If the speed of sound at that location is 315 m/s, the Mach number is (a) 0.63 (b) 0.84 (c) 1.0 (d) 1.07 (e) 1.20arrow_forwardAt one point in a streamline of isentropic airflow, the velocity, pressure, and unit weight are 80 m/s, 405 kPa,and 0.046 kN/m^3 respectively. The velocity of flow at a second point in the streamline is 165 m/s. Determine the pressure at the second point.arrow_forward
- Consider a typical air flow around a cruising jetliner at 10km altitude. The speed is now 810 km/h, while the ambient conditions are 0.414 kg/m³ , 0.261 atm and -50°C. At the stagnation point, the temperature rises over by 25°C, while the density and pressure changes by more than 30% and 45 % respectively. Classify the following situations as compressible/incompressible flowarrow_forwardAir at V_1 = 800 m/s, p_1 = 100 kPa, and T_1 = 300 K passes through a normal shock. Calculate the velocity V_2, temperature T_2, and pressure p_2 after the shock. What would be the values of T_2 and p_2 if the same velocity change were accomplished isentropically?arrow_forwardRace cars at the Indianapolis Speedway average speeds of185 mi/h. After determining the altitude of Indianapolis,fi nd the Mach number of these cars and estimate whethercompressibility might affect their aerodynamics.arrow_forward
- Elements Of ElectromagneticsMechanical EngineeringISBN:9780190698614Author:Sadiku, Matthew N. O.Publisher:Oxford University PressMechanics of Materials (10th Edition)Mechanical EngineeringISBN:9780134319650Author:Russell C. HibbelerPublisher:PEARSONThermodynamics: An Engineering ApproachMechanical EngineeringISBN:9781259822674Author:Yunus A. Cengel Dr., Michael A. BolesPublisher:McGraw-Hill Education
- Control Systems EngineeringMechanical EngineeringISBN:9781118170519Author:Norman S. NisePublisher:WILEYMechanics of Materials (MindTap Course List)Mechanical EngineeringISBN:9781337093347Author:Barry J. Goodno, James M. GerePublisher:Cengage LearningEngineering Mechanics: StaticsMechanical EngineeringISBN:9781118807330Author:James L. Meriam, L. G. Kraige, J. N. BoltonPublisher:WILEY