Preprint Article Version 1 This version is not peer-reviewed

Design and Construction of NACA-4415 Airfoil with Various Shaped Surface Modifications

Version 1 : Received: 19 April 2017 / Approved: 19 April 2017 / Online: 19 April 2017 (11:53:38 CEST)

A peer-reviewed article of this Preprint also exists.

Rubiat Mustak,Md.Habib Ullah Khan,Md. Harun-Or-Rashid Molla,“Design and construction of NACA-4415 airfoil with various shaped surface modifications”, Asia Pacific Journal of Engineering Science and Technology,Volume-3,Issue-1,Pages PP.28-38,2017. Rubiat Mustak,Md.Habib Ullah Khan,Md. Harun-Or-Rashid Molla,“Design and construction of NACA-4415 airfoil with various shaped surface modifications”, Asia Pacific Journal of Engineering Science and Technology,Volume-3,Issue-1,Pages PP.28-38,2017.

Journal reference: Asia Pacific Journal of Engineering Science and Technology (APJEST) 2017, 3, 4
DOI: 10.5281/zenodo.546254

Abstract

A fluid flowing over an object has a tendency to drag the object along its flow direction. An object passing through a fluid which is stationary there is a tendency to slow the object down. For a stationary object in a fluid which is flowing there is a tendency to move the object in the fluid flowing direction .These tendencies of flowing fluid is known as drag. While moving through air airplanes also subjected to several drags. Airplanes subjected to pressure drag or form drag due to flow separation which is based on the pressure difference between the upstream and downstream surfaces of the object. Airplanes also subjected to Skin friction drag which results from the viscous shear of the fluid flowing over the object surface. In order to overcome these drags airplane wings cross section airfoils are designed very carefully. National Advisory Committee for Aeronautics, or NACA, developed and tested "families" of airfoils. Some of the most successful of these were the NACA four-digit and five-digit series. The necessary coordinates for designing NACA airfoil profiles are available in online. UIUC also provide coordinates for designing NACA airfoil profiles. But the present work describes the way of designing NACA four digit airfoils without taking any coordinates from available sources like google or any other search engines. Using C programming with the help of NACA provided equations a generalized source code is designed .Which will provide coordinates for designing any NACA four digit airfoil profiles .With the help of this obtained profile the wing model is also constructed using solid works. Using solid works model the real model was constructed using wood. The chord of regular surface airfoil is 21 cm and the span is also 21 cm. The airfoil profile taken for the model construction is NACA-4415 which is a four digit cambered airfoil.The present work also show some figures of an airfoil by applying certain surface modifications in form of dimples.

Subject Areas

airfoil; dimple; drag; lift

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Comment 1
Received: 20 April 2017
Commenter: Pantho
The commenter has declared there is no conflict of interests.
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Comment 2
Received: 20 April 2017
Commenter: Pantho
The commenter has declared there is no conflict of interests.
Comment: This article shows a totally new concept of surface modification.it,s good.further study can be useful.
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