Clark Y-14 Wing Performance: Deployment of High-lift Devices (Flaps and Slats)

Überblick

Source: David Guo, College of Engineering, Technology, and Aeronautics (CETA), Southern New Hampshire University (SNHU), Manchester, New Hampshire

A wing is the major lift-generating apparatus in an airplane. Wing performance can be further enhanced by deploying high-lift devices, such as flaps (at the trailing edge) and slats (at the leading edge) during takeoff or landing.

In this experiment, a wind tunnel is utilized to generate certain airspeeds, and a Clark Y-14 wing with a flap and slat is used to collect and calculate data, such as the lift, drag and pitching moment coefficient. A Clark Y-14 airfoil is shown in Figure 1 and has a thickness of 14% and is flat on the lower surface from 30% of the chord to the back. Here, wind tunnel testing is used to demonstrate how the aerodynamic performance of a Clark Y-14 wing is affected by high-lift devices, such as flaps and slats.

Figure 1. Clark Y-14 airfoil profile.

Verfahren
  1. For this procedure, use an aerodynamics wind tunnel with a test section of 1 ft x 1 ft and a maximum operating airspeed of 140 mph. The wind tunnel must be equipped with a data acquisition system (able to measure angle of attack, normal force, axial force and pitching moment) and a sting balance.
  2. Open the test section, and install the wing on the sting balance. Start with clean wing configuration.
  3. Place a handheld inclinometer on the sting balance, and adjust the pitch angle adjustment knob to set the sting balance

Log in or to access full content. Learn more about your institution’s access to JoVE content here

Ergebnisse

The results of the clean wing configuration are shown in Table 1. Figures 6 - 8 show all three coefficients vs angle of attack, α, for all four configurations. From Figure 6, both the flap and slat enhanced the lift coefficient, but in different ways. Comparing the clean wing and the slat lift curve, the two curves are almost overlapping at low angles of attack. The clean wing lift curve peaks to about 0.9 at 12°, but the slat curve continues to rise to 1. 4 at 18°. This in

Log in or to access full content. Learn more about your institution’s access to JoVE content here

Anwendung und Zusammenfassung

Lift generation can be enhanced by the deployment of high-lift devices, such as flaps and slats. Most airplanes are equipped with flaps, and all commercial transport airplanes have both flaps and slats. It is critical to characterize the performance of a wing with flaps and slats during aircraft development.

In this demonstration, a Clark Y-14 wing with a flap and a slat was evaluated in a wind tunnel. The forces and moment measurements were collected to determine the lift, drag and pitching m

Log in or to access full content. Learn more about your institution’s access to JoVE content here

Referenzen
  1. John D. Anderson (2017), Fundamentals of Aerodynamics, 6th Edition, ISBN: 978-1-259-12991-9, McGraw-Hill
Tags
Clark Y 14Wing PerformanceHigh lift DevicesFlapsSlatsLift generating ApparatusWing GeometryPressure DifferentialSurface AreaWing Cross SectionAirfoilChord LineCamberPositive CamberWind SpeedTakeoffLandingLeading EdgeTrailing EdgeSlatFlapLift CoefficientDrag Coefficient

pringen zu...

0:01

Concepts

3:18

Evaluating the Performance of a Clark Y-14 Wing in a Wind Tunnel

6:13

Results

Videos aus dieser Sammlung:

article

Now Playing

Clark Y-14 Wing Performance: Deployment of High-lift Devices (Flaps and Slats)

Aeronautical Engineering

13.2K Ansichten

article

Aerodynamisches Verhalten eines Modellflugzeugs: Die DC-6B

Aeronautical Engineering

8.1K Ansichten

article

Charakterisierung von Propellern: Variationen von Pitch, Durchmesser und Blattzahl, und deren Einfluss auf die Leistung

Aeronautical Engineering

26.0K Ansichten

article

Verhalten der Tragflächen: Druckverteilung über einem Clark Y-14-Flügel

Aeronautical Engineering

20.8K Ansichten

article

Turbulence Sphere-Methode: Bewertung der Strömungsqualität im Windkanal

Aeronautical Engineering

8.6K Ansichten

article

Querzylindrische Strömung: Messung der Druckverteilung und Einschätzung des Strömungswiderstandskoeffizient

Aeronautical Engineering

16.0K Ansichten

article

Analyse einer Düse: Variationen in Machzahl und Druck entlang einer konvergierenden und einer konvergierend-divergierenden Düse

Aeronautical Engineering

37.7K Ansichten

article

Schlieren-Imaging: Eine Technik zur Visualisierung der Eigenschaften von Überschallströmungen

Aeronautical Engineering

11.2K Ansichten

article

Strömungsvisualisierung in einem Wassertunnel: Beobachtung des Vorderkantenwirbels über einem Deltaflügel

Aeronautical Engineering

7.8K Ansichten

article

Surface Dye Flow Visualisierung: Eine qualitative Methode zur Beobachtung von Stromlinien in Überschallströmungen

Aeronautical Engineering

4.8K Ansichten

article

Pitotrohr: Ein Gerät zur Messung der Luftströmungsgeschwindigkeit

Aeronautical Engineering

48.4K Ansichten

article

Konstant-Temperatur-Anemometrie: Ein Werkzeug zur Untersuchung der turbulenten Grenzschichtströmung

Aeronautical Engineering

7.1K Ansichten

article

Druckwandler: Kalibrierung mit einem Pitotrohr

Aeronautical Engineering

8.4K Ansichten

article

Echtzeit-Flugsteuerung: Eingebettete Sensorkalibrierung und Datenerfassung

Aeronautical Engineering

10.0K Ansichten

article

Multicopter-Aerodynamik: Charakterisierung der Schubkraft bei einem Hexacopter

Aeronautical Engineering

9.0K Ansichten

JoVE Logo

Datenschutz

Nutzungsbedingungen

Richtlinien

Forschung

Lehre

ÜBER JoVE

Copyright © 2025 MyJoVE Corporation. Alle Rechte vorbehalten