PROPOSAL REQUIREMENTS

The technical proposal must be complete and should contain at least the following information:

1. Description of the technical approaches to comply with each of the requirements specified in the RFP.
2. A clear description of the phasing of tasks.
3. Descriptions, sketches, drawings and discussions of new techniques should be presented in sufficient detail to permit engineering evaluation of the proposal.
4. Exceptions to the proposed technical requirements should be identified and explained.
5. Trade-off studies performed to achieve the final design.
6. Description of design tools used to develop the design.
Clarity and completeness of the technical approach are primary factors in the evaluation of the proposals.

Basis for judging

Technical Content

  1. Fulfilling of the original requirements
  2. Correctness of theory, validity of reasoning used
  3. Pertinent validation analysis
  4. Presentation
  5. Originality

Mock-up

  1. The mock-up must be built according to the specifications

Supporting data

The technical proposal must convincingly demonstrate that the analysis methodology is realistic and that the design satisfies the requirements. The proposal should:

  1. Present the validation dataset collected, show how it was used, and explain any method calibration performed.
  2. Justify the final design, and describe the technologies, and technical approach used to meet the mission requirements.
  3. Provide carpet and sizing plots used to guide the design selection. Describe sensitivity studies used.
  4. Include a dimensioned 3-view general arrangement drawing.
  5. Show a weight breakdown of the major components and systems.
  6. Show weight and cg envelope.
  7. Show estimated component drag build-ups (parasite) and drag polars.
  8. Show estimated propulsion performance including engine power, fuel flow, and propulsive efficiency for all conditions.
  9. Show estimated/computed stability for all flight and loading conditions. The following stability derivatives (they will be checked in the transonic/supersonic wind tunnel at the VKI)
    • Clα Lift due to angle of attack derivative
    • Cdα Drag due to angle of attack derivative
    • Cmα Pitching moment due to angle of attack derivative
    • Clu Lift due to speed derivative
    • Cdu Drag due to speed derivative
    • Cmu Pitching moment due to speed derivative
    • Cyb Side force due to sideslip derivative
    • Cnb Yawing moment due to sideslip derivative
  10. Polar Curve cd(cl)
  11. Include descriptions of the major aircraft systems (size, weight, power consumption, …).
  12. Describe any advanced technologies or design approaches and their relative benefits as used to obtain performance improvements.
  13. Provide the cost estimation for production runs of 10 and 100 units.
  14. Provide fixed and hourly cost estimates.