A498 Project
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This document summarizes the conceptual design process for a Boeing 737 aircraft using Raymer Design Software. The student spent 24 hours understanding the software, gathering data, generating a solid model, and presenting results. Key parameters selected were a cruise Mach number of 0.7 for optimal drag and altitude of 35,000 feet for maximum lift-to-drag ratio. Airfoil selection was based on optimal lift coefficient of 1.3 at Mach 0.7. Results from the basic RDS-EZ software matched closely with the more accurate RDS-Student analysis.
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- 1. Conceptual Design of Boeing 737 Using Raymer Design Software v6.3e by Daniel P. Raymer By Sandeep Kumar Masters student in Aerospace Engineering
- 2. Contents • Project Cost • Geometry Data • Design Layout Module • RDS-EZ • Mach Number Selection • Cruise Altitude Selection • Airfoil Selection • Flight Envelope • RDS-Student • Comparison of results
- 3. Number of hours Spent Understanding the software = 4 hrs Data Gathering = 8 hrs Generation of Solid Model = 3 hrs RDS-EZ = 1 hr RDS-Student = 4 hrs Presentation = 4 hrs Total = 24 hrs Project Cost (in terms of Time)
- 4. Boeing 737 Geometry Data and Parameters (Source: Boeing website and Ref. 1)
- 5. Boeing 737 Geometry Data and Parameters (contd.) (Source: Boeing website and Ref. 1)
- 7. RDS-EZ
- 8. • Induced Drag factor increases after Mach number = 0.8 • Favorable Mach number range is 0.7 to 0.8 • Parasitic Drag factor increases after Mach number =0.7 • Favorable Mach number range is 0.6 to 0.7 Hence, optimum Mach number is in the neighborhood of 0.7 Mach Number Selection
- 9. Cruise Altitude Selection • With increase in altitude, drag force reduces • Negligible reduction in drag above 30000 ft. at Mach number 0.7 • L/D ratio decreases with increase in altitude • Decrease is drastic above 40000 ft. • L/D maximum at 40000 ft. for Mach number 0.7 Hence, optimum altitude of 35000 ft. is selected with a service ceiling at 41000 ft.
- 10. Flight level 350 Passenger Load = Total Load – Fuel load = 82209.5-38629.3 = 43580.2 Max Range = 3115 nm Hence, Range/pax = .0715 Cruise Altitude Selection (contd.)
- 11. Airfoil Selection • At Mach Number 0.7, L/D increase slightly with increase in velocity for Cl values between 1.089 to 1.4 (This implies small increment in velocity increases lift) (Source: airfoiltools.com) Cl-α for Boeing 737 Mid-span Airfoil The Wing is designed such that it has an optimum Cl value of 1.3 • At Mach Number 0.7 L/D increase slightly with increase in velocity for Cl values between 1.089 to 1.4
- 13. RDS-Student • More accurate Aerodynamic analysis was carried out with actual data and parameters for Boeing 737-800 • However, the results are very similar to the RDS-EZ results
- 14. RDS-EZ RDS-Student Comparison of the results
- 18. • Perkins, H. Douglas, Jack Wilson, and Daniel P. Raymer. "An Evaluation of Performance Metrics for High Efficiency Tube-and-Wing Aircraft Entering Service in 2030 to 2035." (2011) References