EXCELLENT OPPORTUNITIES EXIST FOR REDUCING THE DRAG OF AIRCRAFT BY INCREASING THE EXTENT OF LAMINAR BOUNDARY-LAYER FLOW OVER THE CONFIGURATION.

Award Information
Agency:
National Aeronautics and Space Administration
Branch
n/a
Amount:
$48,866.00
Award Year:
1984
Program:
SBIR
Phase:
Phase I
Contract:
n/a
Award Id:
1680
Agency Tracking Number:
1680
Solicitation Year:
n/a
Solicitation Topic Code:
n/a
Solicitation Number:
n/a
Small Business Information
28 Research Drive, Hampton, VA, 23666
Hubzone Owned:
N
Minority Owned:
N
Woman Owned:
N
Duns:
n/a
Principal Investigator:
CORNELIS P. VAN DAM
INVESTIGATOR
() -
Business Contact:
() -
Research Institution:
n/a
Abstract
EXCELLENT OPPORTUNITIES EXIST FOR REDUCING THE DRAG OF AIRCRAFT BY INCREASING THE EXTENT OF LAMINAR BOUNDARY-LAYER FLOW OVER THE CONFIGURATION. RECENT TECHNOLOGICAL ADVANCES IN AIRPLANE CONSTRUCTION TECHNIQUES AND MATERIALS EMPLOYING BONDED AND MILLED ALUMINUM SKINS AND COMPOSITE MATERIALS ALLOW FOR THE PRODUCTION OF AERODYNAMIC SURFACES WITHOUT SIGNIFICANT ROUGHNESS AND WAVINESS, PERMITTING LONG RUNS OF NATURAL LAMINAR FLOW (NLF). ALSO, IMPROVED AERODYNAMIC DESIGN AND ANALYSIS METHODS FACILITATE THE SHAPING OF AIRPLANE SURFACES TO OBTAIN FLOW CONDITIONS FAVORABLE TO NLF. A MAJOR PORTION OF THE RESEARCH EFFORT FOR OBTAINING AND MAINTAINING LAMINAR FLOW ON AIRPLANE SURFACES HAS FOCUSED ON THE DELAY OF LAMINAR-TO-TURBULENT BOUNDARY-LAYER TRANSITION ON AIRPLANE LIFTING SURFACES. BODY SHAPING TO INCREASE THE EXTENT OF LAMINAR FLOW ON AIRPLANE FUSELAGES HAS RECEIVED MUCH LESS ATTENTION IN THE LITERATURE. A SIGNIFICANT REDUCTION IN AIRPLANE DRAG CAN BE OBTAINED, HOWEVER, WHEN NLF IS ACHIEVED ON THE FUSELAGE OF AN AIRPLANE. THE PHASE I OBJECTIVES ARE TO EVALUATE THE VARIOUS COMPUTATIONAL DESIGN AND ANALYSIS METHODS WHICH CAN BE APPLIED FOR THE DEVELOPMENT OF LOW-DRAG AERODYNAMIC FUSELAGE SHAPES AND TO ADDRESS THE ANALYTICAL DESIGN OF BODY SHAPES OF SEVERAL FUSELAGES AT FREE-STREAM UNIT REYNOLDS NUMBERS OF 1.5-3.0 MILLION PER FOOT. THE MOST PROMISING CONFIGURATION(S) WILL BE WIND-TUNNEL AND/OR FLIGHT TESTED DURING PHASE II.

* information listed above is at the time of submission.

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