Editing Drag coefficient (section)

=== Aircraft ===
As noted above, aircraft use their wing area as the reference area when computing <math>c_\mathrm d</math>, while automobiles (and many other objects) use projected frontal area; thus, coefficients are '''not''' directly comparable between these classes of vehicles. In the aerospace industry, the drag coefficient is sometimes expressed in drag counts where 1 [[drag count]] = 0.0001 of a <math>c_\mathrm d</math>.<ref>Basha, W. A. and Ghaly, W. S., "Drag Prediction in Transitional Flow over Airfoils," Journal of Aircraft, Vol. 44, 2007, p. 824–32.</ref>

{| class="wikitable" style="font-size:98%; width:450px;"
! ''c''<sub>d</sub>
!Drag Count!! Aircraft type<ref>{{cite web|url=http://www.aerospaceweb.org/question/aerodynamics/q0184.shtml |title=Ask Us – Drag Coefficient & Lifting Line Theory |publisher=Aerospaceweb.org |date=2004-07-11 |access-date=2010-12-07}}</ref>
|-
| 0.021
|210||[[F-4 Phantom II]] (subsonic)
|-
| 0.022
|220||[[Learjet 24]]
|-
| 0.024
|240||[[Boeing 787]]<ref>{{cite web |url=http://www.lissys.demon.co.uk/samp1/index.html |title=Boeing 787 Dreamliner : Analysis |publisher=Lissys.demon.co.uk |date=2006-06-21 |access-date=2010-12-07 |url-status=live |archive-url=https://web.archive.org/web/20100813094712/http://www.lissys.demon.co.uk/samp1/index.html |archive-date=2010-08-13 }}</ref>
|-
| 0.0265
|265||[[Airbus A380]]<ref>{{cite web |url=http://www.dept.aoe.vt.edu/~mason/Mason_f/A380Dean.pdf |title=Airbus A380 |date=2005-05-02 |access-date=2014-10-06 |url-status=live |archive-url=https://web.archive.org/web/20150923213641/http://www.dept.aoe.vt.edu/~mason/Mason_f/A380Dean.pdf |archive-date=2015-09-23 }}</ref>
|-
| 0.027
|270||[[Cessna 172]]/[[Cessna 182|182]]
|-
| 0.027
|270||[[Cessna 310]]
|-
| 0.031
|310||[[Boeing 747]]
|-
| 0.044
|440||[[McDonnell Douglas F-4 Phantom II|F-4 Phantom II]] (supersonic)
|-
| 0.048
|480||[[F-104 Starfighter]]
|}