File:FAA-8083-3A Fig 15-9.png

From Wikimedia Commons, the free media repository
Jump to navigation Jump to search

FAA-8083-3A_Fig_15-9.png ‎(522 × 427 pixels, file size: 29 KB, MIME type: image/png)

Captions

Captions

Add a one-line explanation of what this file represents
File:Transonic flow patterns.svg is a vector version of this file. It should be used in place of this PNG file when not inferior.
File:FAA-8083-3A Fig 15-9.png → File:Transonic flow patterns.svg
For more information, see Help:SVG.
In other languages
Alemannisch ∙ Bahasa Indonesia ∙ Bahasa Melayu ∙ British English ∙ català ∙ čeština ∙ dansk ∙ Deutsch ∙ eesti ∙ English ∙ español ∙ Esperanto ∙ euskara ∙ français ∙ Frysk ∙ galego ∙ hrvatski ∙ Ido ∙ italiano ∙ lietuvių ∙ magyar ∙ Nederlands ∙ norsk bokmål ∙ norsk nynorsk ∙ occitan ∙ Plattdüütsch ∙ polski ∙ português ∙ português do Brasil ∙ română ∙ Scots ∙ sicilianu ∙ slovenčina ∙ slovenščina ∙ suomi ∙ svenska ∙ Tiếng Việt ∙ Türkçe ∙ vèneto ∙ Ελληνικά ∙ беларуская (тарашкевіца) ∙ български ∙ македонски ∙ нохчийн ∙ русский ∙ српски / srpski ∙ татарча/tatarça ∙ українська ∙ ქართული ∙ հայերեն ∙ বাংলা ∙ தமிழ் ∙ മലയാളം ∙ ไทย ∙ 한국어 ∙ 日本語 ∙ 简体中文 ∙ 繁體中文 ∙ עברית ∙ العربية ∙ فارسی ∙ +/−
New SVG image

Summary

[edit]
Description

High speed airplanes designed for subsonic flight are limited to some Mach number below the speed of sound to avoid the formation of shock waves that begin to develop as the airplane nears Mach 1.0. These shock waves (and the adverse effects associated with them) can occur when the airplane speed is substantially below Mach 1.0. The Mach speed at which some portion of the airflow over the wing first equals Mach 1.0 is termed the critical Mach number (MACHCRIT).. This is also the speed at which a shock wave first appears on the airplane.

There is no particular problem associated with the acceleration of the airflow up to the point where Mach 1.0 is encountered; however, a shock wave is formed at the point where the airflow suddenly returns to subsonic flow. This shock wave becomes more severe and moves aft on the wing as speed of the wing is increased, and eventually flow separation occurs behind the well-developed shock wave. [Figure 15-9]
Source (2004) Airplane Flying Handbook. U.S. Government Printing Office, Washington D.C.: U.S. Federal Aviation Administration, p. 15-7. FAA-8083-3A.
Author
This file is lacking author information.

Licensing

[edit]
Public domain
This image or file is a work of a Federal Aviation Administration employee, taken or made as part of that person's official duties. As a work of the U.S. federal government, the image is in the public domain in the United States.

English | italiano | македонски | മലയാളം | Nederlands | русский | sicilianu | українська | 中文 | +/−

File history

Click on a date/time to view the file as it appeared at that time.

Date/TimeThumbnailDimensionsUserComment
current07:05, 20 October 2007Thumbnail for version as of 07:05, 20 October 2007522 × 427 (29 KB)Mingray (talk | contribs){{Information |Description=High speed airplanes designed for subsonic flight are limited to some Mach number below the speed of sound to avoid the formation of shock waves that begin to develop as the airplane nears Mach 1.0. These shock waves (and the ad
07:05, 20 October 2007Thumbnail for version as of 07:05, 20 October 2007522 × 427 (29 KB)Mingray (talk | contribs){{Information |Description=High speed airplanes designed for subsonic flight are limited to some Mach number below the speed of sound to avoid the formation of shock waves that begin to develop as the airplane nears Mach 1.0. These shock waves (and the ad

You cannot overwrite this file.

The following page uses this file:

File usage on other wikis

The following other wikis use this file:

Retrieved from "https://commons.wikimedia.org/w/index.php?title=File:FAA-8083-3A_Fig_15-9.png&oldid=235413609"