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The cost of designing a brand new wing for a jetliner, compared to modifying an existing one—with or without the changes to the production line—how is it estimated?

Related questions (bonus): Are there various methods? Does the cruise speed (wind tunnel cost) and MTOW (size) affect the cost?


Context of question (optional to read):

Speaking to Flight in 1987, Gary Smythe, chief customer engineer for the MD-11/DC-10, talked about the reason behind the minimal changes to the MD-11 wing compared to the DC-10.

To have gone for an all-new wing design "would add $10 million a copy to the price of an MD-11." That course of action would defeat the whole Douglas "low total ownership cost" approach.

Given that they projected 300 sales, that means the design (and manufacturing changes) would have cost \$3 billion (\$6.5 billion in 2017). The MD-11 had subpar performance for the Pacific market early on, and that was one of the reasons attributed to its low sales.

The same thing happened with the MD-90 with its MD-80 wing. Because of this and despite having a cleaner wing of same area, same engines (V2500), and about the same seats as the A320, it could not achieve transcontinental range (both for the US and Europe), and it had longer takeoff runs.

An expensive re-wing was announced in Farnborough 1996, but was awaiting to be "sanctioned". There is no mention of the projected cost.

"It would be an all-new wing, not a revised version of the present one," says the president of MDC's Douglas Aircraft division, Mike Sears. The present wing design is a revision of the MD-80 wing. The MD-90's range is limited to intra-continental operations in the USA (Flight, 1996).

Only a few months later Boeing merged with MDC.

enter image description here
(Own work via boeing.com and airbus.com) Comparing the MD-90 and A320 wing and planform. Note that the MD-90 is one seat narrower.

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  • $\begingroup$ It looks like the MD-90 has a much greater wetted surface area than the A320 (from your nice-looking graphic), indicating much greater drag. $\endgroup$ – user7241 Dec 25 '17 at 12:00
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This is what I could find, but perhaps there are other methods as well.


A 153-page research (SM thesis) titled Valuation Techniques for Commercial Aircraft Program Design by Jacob Markish at MIT breaks down the valuation of the design of commercial aircraft.

The non-recurring (development) cost of a wing is broken down into engineering, manufacture engineering (ME), tool design, tool fabrication, and support.

For the wing (and the other parts), it's a dollar value per pound.

The engineering of a wing (clean slate) costs \$7,093 per pound. The total for the wing is $17,731 (per pound). If it is not a clean slate design, say the DC-10 / MD-11 example, then it's 20% of the engineering, 5% of the tool design/fabrication, 50% of the ME and support.

The heaviest (OEW) MD-11 weighs 291,120 lb. With the wing 23% of that based on the research, and accounting for inflation (from the year 2000), the total development cost would have been $783 million (in 1987) for the wing if MDC had went with a new design.

MDC spent less than that for the whole "engineering, tools and flight testing," a cool \$700 million. Plus "$2.5 billion in inventory for initial production." (latimes.com, 1990)

Based on this method, the value is $328 million (in 1996 dollars) to redesign the MD-90 wing (full value, not just engineering).

Seeing how the table below shows how expensive the empennage and systems are, and with the major changes done to those areas on the MD-11, one can see why they went this way.

enter image description here


Note: The thesis arrives at a correlation between weight and cost based on publicly available figures, however it does remain a simplification. Regarding a comment about the weight of composites vs. metals: a composite airliner is generally not lighter.

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The design of a new wing requires many steps:

  1. Structural design of the wing. This task in man-hour driven, which is generally a function of wing weight. While at the first step the wing weight is unknown, but an initial guess is available from past experience or other aircraft. in Roakam's design book part VIII, based on aircraft design programs a function for design man-hour versus weight is provided. This estimation is also relates the cruise speed and aircraft weight.

  2. Structural test: The wing should be tested for the most critical flight and ground load cases. The most critical flight load cases almost contains 2.5g maneuver at Maximum Zero Fuel Weight (MZFW).

  3. Wind Tunnel test: The wing should be tested for low-speed (high lift) performance and for high-speed (cruise) performance. if the cruise speed is in the transonic regime, special wind tunnels with higher cost per hour test is required.

In the roskam's book an initial estimation of the aircraft testing cost is provided.

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