Schaufele Annotations

 

Annotations are organized by chapter.  Not all chapters have annotations. Clicking on the appropriate link will open the annotation.

 

 

Chapter 1  Review of Basic Concepts:  Given a definition of an aircraft drag polar, a method is described for calculating the value of maximum L/D and value of C_L at which it occurs.

 

Chapter 3  Preliminary Estimate of Maximum Takeoff Gross Weight:  The Breguet range equation is derived.  An alternative (and preferred) method is described for calculating mission fuel fraction by factoring segment fuel fractions.

 

Chapter 4  Preliminary Wing Design:  Some additional notes on DC-9 lateral control surfaces are provided.

 

Chapter 6  Horizontal and Vertical Tail Sizing:  Some additional notes on DC-9 longitudinal control surfaces are provided.

 

Chapter 7 Landing Gear Design: Design and location of landing gear is affect by wing sweep and aspect ratio.

 

Chapter 8 Engine Sizing and Arrangement: Additional notes are provided on engine sizing to meet aircraft performance requirements.

The DC-9 has been one of the work-horses of the airline industry since 1965, and has been stretched and re-engined many times. Preliminary design was started in 1962, with first flight in February 1965.  The airplane entered service with Delta Airlines later that year.  The last delivery of one of its derivatives, the MD-87, was in December 1999.

 

The design is used in many of the examples in Schaufele's "The Elements of Aircraft Preliminary Design".

 

Chapter 10 Preliminary Weight and Balance Calculations: A tabular method is described for calculating weight and balance from a group weight statement.

 

Chapter 12 Detailed Drag Buildup for Cruise, Takeoff, and Landing: A tabular method, suitable for spreadsheet analyis, is described for zero-lift drag buildup. A spreadsheet method is also described for generating a drag map.

 

Chapter 13 Operational Envelope and Estimated Aircraft Buffet Boundary: Brief supplemental notes are provided

 

Chapter 15 Payload-Range Performance: Additional notes are provided for generating the payload-range plot, including a method for calculating fuel tank capacity.

 

Chapter 17 FAR Climb Gradient Requirements: FAR climb segments are defined. The procedure is described for calculating T/W as a function of the second segment climb requirement.

 

Chapter 19 Aircraft Pricing and Direct Operating Cost: Coefficients in the Liebeck DOC model have been updated from 1993 to 2009.