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Aero Research

Summary

Boundary Layer

Non-Linear Aero

Drag Reduction

Forebody Vortex

Enhanced NLF

Helicopter Blade

Model Fabrication

LabVIEW Programs

Research Papers

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Water Tunnels

Summary

Model 2436

Model 1520

Model 0710

Model 2403

Custom Designs

Model Support

Force Balances

Class Experiments

Installations

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All Products

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Programming

LabVIEW

Real-Time

Man-in-the-Loop

HW-in-the-Loop

 

 

Rolling Hills Research Corporation

Copyright @2014

All Rights Reserved

 

 

RHRC AWARDED NASA SMALL BUSINESS INNOVATIVE RESEARCH CONTRACT

 

 

October 4, 2006 - Rolling Hills Research Corporation has been selected by NASA for a $600,000 Small Business Innovative Research (SBIR) contract.  This will be the second phase of the research program, following a highly successful Phase I research program performed earlier this year. 

 

NASA selected a total of 120 SBIR research proposals from small high technology firms in 27 states, for a total of approximately $72 million.  The goals of the program are to stimulate technological innovation, increase the use of small businesses in meeting federal research and development needs and increase private sector commercialization of innovations derived from federally funded research.

 

A robust flow control method promising significantly increased performance and virtual shape control for natural laminar flow (NLF) sections was demonstrate during the Phase I research program. Significant aerodynamic, systems, and control benefits are possible through the integration of virtual aerodynamic shaping technology into modern aircraft. Virtual aerodynamic shaping involves using flow control technology to manipulate the flow field to achieve a desired result regardless of the geometry. A high-payoff approach to significantly increased air vehicle performance is virtual shaping of extended run natural laminar flow sections. The objective of this research is to incorporate a robust and simple flow control system that requires no external power to design and virtually shape an extended natural laminar flow section offering radical performance enhancement in the form of increased lift-to-drag and maximum lift. Additionally, the system will produce a wing design enabling a hinge-less, full-span virtual shaping capability which can be used for fully pilot reactive roll control, span load tailoring, and gust load alleviation. The system will provide significantly enhanced performance for the air vehicle throughout the entire flight envelope.

 

Dr. Mike Kerho will be the Principal Investigator for this research program.

 

 
 

 

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