If you are experiencing problems downloading PDF or HTML fulltext, our helpdesk recommend clearing your browser cache and trying again. If you need help in clearing your cache, please click here . Still need help? Email help@ingentaconnect.com

Readers Forum: Preliminary Optimization of Turbojet‐Cruise VTol Aircraft

$30.00 plus tax (Refund Policy)

Buy Article:


The subject of turbojet airplane range is handled in many classical texts, such as Reference 1. Generally, it is assumed that the wing area has already been chosen from stalling speed considerations, and the range is specified by the product of the parameters L/D and cruise speed. When the wing area is a variable, however, as for a VTOL aircraft where stall speed is unimportant, it is desirable to re‐examine the basic range equation to establish an optimum value of wing area.

Document Type: Research Article

DOI: http://dx.doi.org/10.4050/JAHS.10.24

Affiliations: Technical Department, Hughes Tool Company — Aircraft Division, Culver City, California

Publication date: April 1, 1965

More about this publication?
  • The Journal of the American Helicopter Society is the world's only scientific journal dedicated to vertical flight technology. It is a peer-reviewed technical journal published quarterly by AHS International and presents innovative papers covering the state-of-the-art in all disciplines of rotorcraft design, research and development. (Please note that AHS members receive significant discounts on articles and subscriptions.)

    Journal subscribers who are AHS members log in here if you are not already logged in.

    Authors can find submission guidelines and related information on the AHS website.

Related content



Share Content

Access Key

Free Content
Free content
New Content
New content
Open Access Content
Open access content
Subscribed Content
Subscribed content
Free Trial Content
Free trial content
Cookie Policy
Cookie Policy
ingentaconnect website makes use of cookies so as to keep track of data that you have filled in. I am Happy with this Find out more