Send Inquiry

Request To Call Back

Clark Y-14 Slat/Flap Wing

Get a Price/Quote

MOQ : 1 Number

Clark Y-14 Slat/Flap Wing Specification

Material
Aerospace-grade Aluminum Alloy & Composite

Processing Type
Precision Machined & CNC-Cut

Condition
New

Technology
Clark Y-14 Airfoil with Leading Edge Slat and Hinged Trailing Flap

Dimension (L*W*H)
Span: 610 mm, Chord: 120 mm, Slat Chord: 25 mm, Flap Chord: 30 mm

Power Mode
Manual, Electric, Pneumatic (Depends on integration)

Voltage
N/A (unless integrated with electrical actuators)

Power Consumption
N/A (passive component unless actuation is installed)

Pressure Output
Up to 2 kPa Differential (wing surface) (application dependent)

Application
Aero-modelling, Research, UAV Prototypes, Educational kits

Coating Type
Corrosion Resistant Anodized & Composite Surface

Accessories
Mounting Fixtures, Servo Linkages, Control Hardware

Edge Treatments
Rounded Leading Edge, Tapered Trailing Edge per Clark Y-14 Design

Weight
Approx. 900g (depends on configuration)

Equipment Type
Aerodynamic Test Wing (Slat/Flap Assembly)

Surface Finish
Polished, Smooth for Optimal Airflow

Slat/Flap Deflection
Slat: 0-25, Flap: 0-40 Manual/Electric

Mounting Standards
Compatible with standard wind tunnel mounts and research rigs

Use Case
Wind Tunnel Testing, Lift/Drag Studies, Flow Visualization, Teaching

Pilot Holes
Provided for Standard Sensor Mounting

Airfoil Type
Clark Y-14 Contour per NACA Specifications

Assembly
Pre-assembled or Kit-form available

Adjustable Span
Yes (modular with extension sections)

About Clark Y-14 Slat/Flap Wing

Overview

A precision airfoil test model based on the Clark Y-14 profile, featuring infinitely adjustable slats and flaps for advanced high-lift and flow control studies. Designed for compatibility with standard sting balances, the model supports both flow visualization and aerodynamic force measurements.

Key Features

Infinitely Adjustable Slats & Flaps for high-lift configuration studies
Clark Y-14 Airfoil Profile for realistic aerodynamic behaviour
Dual Use: Suitable for visualization and force testing
Standard Mounting: Compatible with 3/8-inch string balances
Compact, High-Precision Construction

Technical Datasheet (Typical)

Geometry

Airfoil Type: Clark Y-14
Span: 250 mm (9.875 in)
Chord: 90 mm (3.5 in)
Configuration: Slat and flap adjustable system

Mounting

Type: Sting-mounted
Compatibility: 3/8-inch sting balance

Adjustability

Slat Angle: Continuously variable
Flap Angle: Continuously variable

Performance

Application Range: Low-speed to moderate-speed wind tunnel testing
Use Case: Lift enhancement, stall behaviour, and flow separation studies
Measurement Compatibility: External/internal force balances

Optional Features

Integrated pressure taps
Angle measurement scales or digital readouts
Custom airfoil profiles and sizes
Handcrafted custom models and probes

Applications

High-lift device research
Stall and flow separation analysis
Aerodynamic coefficient measurement
Educational demonstrations and lab experiments

Customization

Available as a fully customizable model, allowing adjustments in size, airfoil profile, and instrumentation to meet specific research needs.

Engineered for Versatile Aerodynamics Research

The Clark Y-14 Slat/Flap Wing is designed specifically for laboratory wind tunnel testing, lift/drag analysis, and real-time flow visualization. Its modular construction and adjustable control surfaces enable researchers and educators to adapt experiments easily, evaluating a wide range of aerodynamic conditions. The wing's compatibility with common wind tunnel systems streamlines set-up, making it an essential tool for research institutes and universities.

Precision Manufacturing & Quality Materials

Constructed from aerospace-grade aluminum alloy and high-strength composites, the Clark Y-14 test wing offers exceptional durability and a smooth, polished finish, ensuring minimal airflow disruption. CNC machining and anodized coatings guarantee precise geometry and long-term resistance to corrosion, meeting the rigorous standards required for academic, industrial, and UAV prototype applications.

FAQ's of Clark Y-14 Slat/Flap Wing:

Q: How can I integrate the Clark Y-14 Slat/Flap Wing into my wind tunnel experiment?

A: The wing is compatible with most standard wind tunnel mounts and research rigs, featuring pre-drilled pilot holes for mounting sensors. It can be ordered pre-assembled or as a kit, ensuring seamless integration into educational setups or research facilities.

Q: What benefits does the Clark Y-14 airfoil contour offer for aerodynamic testing?

A: The Clark Y-14 airfoil contour, guided by NACA standards, delivers predictable lift and drag characteristics. Coupled with adjustable slat and flap sections, it enables comprehensive studies of boundary layer behavior, stall, and flow separation-ideal for academic and R&D applications.

Q: When should I use manual versus electric actuation for the slat and flap controls?

A: Manual actuation is suitable for educational or basic testing setups, while electric actuation is recommended for precise, repeatable deflection adjustments in advanced research. Both options are supported, depending on integration and test requirements.

Q: Where can I apply this wing assembly beyond traditional wind tunnel studies?

A: Aside from wind tunnel experiments, the Clark Y-14 wing is valuable in aero-modelling, UAV prototype development, and as an instructional tool in classroom environments, offering flexible configurations for a range of applications.

Q: What is provided for mounting sensors or measuring aerodynamic forces?

A: The wing comes with pilot holes designed for standard sensor mounts, simplifying the process of attaching pressure sensors or strain gauges. Accessories such as servo linkages and mounting fixtures are included to support diverse experimental setups.

Q: What is the process of assembling the Clark Y-14 Slat/Flap Wing if ordered as a kit?

A: Assembly involves joining CNC-machined modules using guide fixtures, securing control hardware, and attaching actuation systems as specified. Comprehensive instructions and all necessary hardware are provided for straightforward construction.

Q: What are the advantages of the wing's surface finish and edge treatments?

A: The smooth, polished surface and corrosion-resistant coating optimize airflow and measurement accuracy, while the rounded leading edge and tapered trailing edge facilitate realistic analysis of aerodynamic effects seen in actual flight vehicles.

Tell us about your requirement