Aerospace: New Applications
https://www.maplesoft.com/applications/category.aspx?cid=2890
en-us2021 Maplesoft, A Division of Waterloo Maple Inc.Maplesoft Document SystemMon, 20 Sep 2021 23:52:03 GMTMon, 20 Sep 2021 23:52:03 GMTNew applications in the Aerospace categoryhttps://www.maplesoft.com/images/Application_center_hp.jpgAerospace: New Applications
https://www.maplesoft.com/applications/category.aspx?cid=2890
Speed of Sound in Various Fluids
https://www.maplesoft.com/applications/view.aspx?SID=154641&ref=Feed
This application computes and tabulates the speed of sound in various fluids at standard temperature and pressure, as provided by the ThermophysicalData package (which uses the open-source CoolProp project for fluid properties).
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The list of fluids include water, ethanol, air, ammonia and several others. However, you can use any of the fluids in the ThermophysicalData package (this help page contains a list of available fluids).
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This application also demonstrates the use of the DocumentTools package for tabulating and formatting results.<img src="https://www.maplesoft.com/view.aspx?si=154641/thumb.png" alt="Speed of Sound in Various Fluids" style="max-width: 25%;" align="left"/>This application computes and tabulates the speed of sound in various fluids at standard temperature and pressure, as provided by the ThermophysicalData package (which uses the open-source CoolProp project for fluid properties).
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The list of fluids include water, ethanol, air, ammonia and several others. However, you can use any of the fluids in the ThermophysicalData package (this help page contains a list of available fluids).
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This application also demonstrates the use of the DocumentTools package for tabulating and formatting results.https://www.maplesoft.com/applications/view.aspx?SID=154641&ref=FeedFri, 08 May 2020 04:00:00 ZSamir KhanSamir KhanCompressor Power for a Supersonic Wind Tunnel at Steady-state and Start-up
https://www.maplesoft.com/applications/view.aspx?SID=154548&ref=Feed
This application calculates the compressor power (at steady-state and at start-up) for a fixed geometry supersonic wind tunnel. The test section will operate at Mach 2.5, simulate an altitude of 21 km and has a circular cross-sectional area with a diameter of 30 cm. A supersonic fixed-area diffuser follows the test section.
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A cooler between the compressor and the nozzle ensures that the air at the compressor inlet and in the test section have the same stagnation temperature.
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The air entering the compressor and in the test section has the same stagnation temperature. The compressor is isentropic, and friction and boundary layer effects are not considered.<img src="https://www.maplesoft.com/view.aspx?si=154548/wind_tunnel.png" alt="Compressor Power for a Supersonic Wind Tunnel at Steady-state and Start-up" style="max-width: 25%;" align="left"/>This application calculates the compressor power (at steady-state and at start-up) for a fixed geometry supersonic wind tunnel. The test section will operate at Mach 2.5, simulate an altitude of 21 km and has a circular cross-sectional area with a diameter of 30 cm. A supersonic fixed-area diffuser follows the test section.
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A cooler between the compressor and the nozzle ensures that the air at the compressor inlet and in the test section have the same stagnation temperature.
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The air entering the compressor and in the test section has the same stagnation temperature. The compressor is isentropic, and friction and boundary layer effects are not considered.https://www.maplesoft.com/applications/view.aspx?SID=154548&ref=FeedMon, 12 Aug 2019 04:00:00 ZSamir KhanSamir KhanUS Standard Atmosphere 1976
https://www.maplesoft.com/applications/view.aspx?SID=154545&ref=Feed
Standard atmospheric models describe how the properties of air change with altitude. The properties reflect conditions typically expected at that altitude, and do not vary with current climatic conditions. The results are typically used for flight studies, rocketry and ballistics.
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This application implements the US Standard Atmosphere model for the lower atmosphere, published by the US Committee on Extension to the Standard Atmosphere (COESA) in 1976.
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The model gives the pressure, temperature, density and viscosity of air as a function of geopotential altitude, and is valid from a geopotential altitude of 0 m to 84852 m.
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Reference: <A HREF="https://ntrs.nasa.gov/search.jsp?R=19770009539" TARGET="_blank">US Standard Atmosphere 1976</A><img src="https://www.maplesoft.com/view.aspx?si=154545/US_Standard_Atmosphere_1976.png" alt="US Standard Atmosphere 1976" style="max-width: 25%;" align="left"/>Standard atmospheric models describe how the properties of air change with altitude. The properties reflect conditions typically expected at that altitude, and do not vary with current climatic conditions. The results are typically used for flight studies, rocketry and ballistics.
<BR><BR>
This application implements the US Standard Atmosphere model for the lower atmosphere, published by the US Committee on Extension to the Standard Atmosphere (COESA) in 1976.
<BR><BR>
The model gives the pressure, temperature, density and viscosity of air as a function of geopotential altitude, and is valid from a geopotential altitude of 0 m to 84852 m.
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Reference: <A HREF="https://ntrs.nasa.gov/search.jsp?R=19770009539" TARGET="_blank">US Standard Atmosphere 1976</A>https://www.maplesoft.com/applications/view.aspx?SID=154545&ref=FeedThu, 18 Jul 2019 04:00:00 ZSamir KhanSamir KhanUnpowered Glide Analysis of a Baron 58 Light Aircraft
https://www.maplesoft.com/applications/view.aspx?SID=154544&ref=Feed
This application presents an unpowered glide analysis of a Baron 58 aircraft.
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An aircraft with no engine power will glide to the ground. The best glide angle is the flight angle at which the airplane will travel the greatest distance, and occurs at the maximum lift-to-drag ratio.
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For the parameters used in this application, a Baron 58 aircraft has a maximum lift-to-drag ratio of about 12.2. This means an unpowered Baron will fall 1 m for every 12.2 m of travel. This application also calculates the best glide velocity, drag and lift coefficients, and the dynamic pressure.<img src="https://www.maplesoft.com/view.aspx?si=154544/Drag_force.png" alt="Unpowered Glide Analysis of a Baron 58 Light Aircraft" style="max-width: 25%;" align="left"/>This application presents an unpowered glide analysis of a Baron 58 aircraft.
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An aircraft with no engine power will glide to the ground. The best glide angle is the flight angle at which the airplane will travel the greatest distance, and occurs at the maximum lift-to-drag ratio.
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For the parameters used in this application, a Baron 58 aircraft has a maximum lift-to-drag ratio of about 12.2. This means an unpowered Baron will fall 1 m for every 12.2 m of travel. This application also calculates the best glide velocity, drag and lift coefficients, and the dynamic pressure.https://www.maplesoft.com/applications/view.aspx?SID=154544&ref=FeedThu, 18 Jul 2019 04:00:00 ZSamir KhanSamir Khan