scholarly journals An Experimental Investigation of the Vortex Merging over a Cranked-Delta Wing at Subsonic Speed

2021 ◽  
Vol 5 (1) ◽  
Author(s):  
Zafarghandi Fatemeh Mahdavi ◽  
Soltani Mohammad Reza
Keyword(s):  
Experimental Investigation ◽  
Delta Wing ◽  
Vortex Merging ◽  
Subsonic Speed

Experimental Investigation on Blunt-Edged UTM Delta Wing VFE-2 Configurations at Low Reynolds Number

2018 ◽  
Vol 12 (3) ◽  
pp. 255
Author(s):  
Muhammad Zal Aminullah Daman Huri ◽  
Shabudin Bin Mat ◽  
Mazuriah Said ◽  
Shuhaimi Mansor ◽  
Md. Nizam Dahalan ◽  
...  
Keyword(s):  
Experimental Investigation ◽  
Reynolds Number ◽  
Delta Wing ◽  
Low Reynolds Number ◽  
Low Reynolds

Measured Pressure Distributions and Shock Shapes on a Simple Delta Wing

1981 ◽  
Vol 32 (3) ◽  
pp. 188-198 ◽  
Author(s):  
L.C. Squire
Keyword(s):  
Experimental Investigation ◽  
Mach Number ◽  
Delta Wing ◽  
Numerical Calculations ◽  
Test Case ◽  
Pressure Distributions ◽  
Shock System ◽  
Mach Numbers ◽  
Measured Pressure

SummaryThis note presents the results of an experimental investigation of the flow over a simple delta wing designed for a Mach number of 3.5. Complete pressure distributions were measured for incidences of 0°, 10° and 20° at Mach numbers of 2.5 and 3.5. A number of schlieren photographs of the shock system around the wing were obtained at the same conditions and surface streamline patterns were studied at M = 3.5. The measurements were made to support numerical calculations which use this wing as a test case.

Experimental investigation of high-incidence delta-wing flow control

2017 ◽  
Vol 58 (9) ◽  
Author(s):  
Andrei Buzica ◽  
Julius Bartasevicius ◽  
Christian Breitsamter
Keyword(s):  
Experimental Investigation ◽  
Flow Control ◽  
Delta Wing ◽  
High Incidence

Alleviation of pitch-up on delta wings using distributed porosity

1999 ◽  
Vol 103 (1025) ◽  
pp. 339-347 ◽  
Author(s):  
L. W. Traub ◽  
B. Moeller ◽  
S. F. Galls
Keyword(s):  
Experimental Investigation ◽  
Flow Field ◽  
Delta Wing ◽  
Leading Edge ◽  
Surface Flow ◽  
Force Balance ◽  
Flow Visualisation ◽  
Surface Porosity ◽  
Delta Wings ◽  
Field Surveys

Abstract An experimental investigation was undertaken to determine the effectiveness of distributed surface porosity for the alleviation of pitch-up on a delta wing. Tests were undertaken using a 65° sweep delta wing with distributed porosity evaluated at various locations on the wing. Force balance, on and off surface flow visualisation and flow field surveys using a multi-hole probe were undertaken. The data shows that distributed porosity applied along the wing leading edge at the apex is effective in eliminating pitch-up whilst incurring a minimal performance cost. Trailing edge porosity generally degraded performance.

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