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COMPUTATIONAL TECHNIQUE AND DESIGN GUIDE DEFINING DEPARTURE/SPIN RESISTANT FOREBODY CONFIGURATIONS DEVELOPMENT

Award Information
Agency: Department of Defense
Branch: Air Force
Contract: N/A
Agency Tracking Number: 2106
Amount: $269,000.00
Phase: Phase II
Program: SBIR
Solicitation Topic Code: N/A
Solicitation Number: N/A
Timeline
Solicitation Year: N/A
Award Year: 1986
Award Start Date (Proposal Award Date): N/A
Award End Date (Contract End Date): N/A
Small Business Information
400 Jericho Turnpike
Jericho, NY 11753
United States
DUNS: N/A
HUBZone Owned: No
Woman Owned: No
Socially and Economically Disadvantaged: No
Principal Investigator
 Billy P Barnhart
 (516) 433-0710
Business Contact
Phone: () -
Research Institution
N/A
Abstract

AIRPLANE FOREBODY DESIGN HAS CONSISTENTLY DEMONSTRATED SIGNIFICANT INFLUENCES ON BOTH STATIC AND ROTATIONAL AERODYNAMICS AND, CONSEQUENTLY, ON HIGH ANGLE-OF-ATTACK FLIGHT CHARACTERISTICS AND SPIN BEHAVIOR. AN EXTENSIVE HIGH ANGLE-OF-ATTACK DATA BASE FOR MILITARY CONFIGURATIONS HAS BEEN GENERATED USING THE ROTARY BALANCE AT THE NASA LANGLEY 20-FOOT SPIN TUNNEL. THIS DATA BASE WILL BE UTILIZED TO CORRELATE STATIC AND ROTATIONAL AERODYNAMIC CHARACTERISTICS WITH FOREBODY DESIGN PARAMETERS. THE RESULTS OF THIS ANALYSIS WILL BE FORMULATED INTO A PRELIMINARY DESIGN GUIDE, WHICH WILL DEMONSTRATE THE RELATIONSHIP OF HIGH ANGLE-OF-ATTACK AERODYNAMIC CHARACTERISTICS WITH FOREBODY DESIGN. THIS TYPE OF INFORMATION IS REQUIRED AS A PRE-REQUISITE FOR THE FORMULATION OF COMPUTATIONAL TECHNIQUES.

* Information listed above is at the time of submission. *

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