Toker, Kemal Atılgan

Profile Picture
Profile URL
https://hdl.handle.net/20.500.14411/8127
Name Variants
T., Kemal Atilgan
Toker, Kemal Atılgan
T.,Kemal Atılgan
Kemal Atilgan, Toker
T.,Kemal Atilgan
Toker,K.A.
Toker, Kemal Atilgan
K., Toker
Kemal Atılgan, Toker
K.,Toker
K.A.Toker
Job Title
Doktor Öğretim Üyesi
Email Address
Main Affiliation
Airframe and Powerplant Maintenance
Status
Former Staff
Website
ORCID ID
Scopus Author ID
Turkish CoHE Profile ID
Google Scholar ID
WoS Researcher ID

Sustainable Development Goals

SDG data is not available
This researcher does not have a Scopus ID.
This researcher does not have a WoS ID.
Scholarly Output

1

Articles

0

Views / Downloads

0/0

Supervised MSc Theses

0

Supervised PhD Theses

0

WoS Citation Count

0

Scopus Citation Count

0

WoS h-index

0

Scopus h-index

0

Patents

0

Projects

0

WoS Citations per Publication

0.00

Scopus Citations per Publication

0.00

Open Access Source

0

Supervised Theses

0

Google Analytics Visitor Traffic

JournalCount
AIAA AVIATION 2014 -19th AIAA International Space Planes and Hypersonic Systems and Technologies Conference -- AIAA AVIATION 2014 -19th AIAA International Space Planes and Hypersonic Systems and Technologies Conference 2014 -- 16 June 2014 through 20 June 2014 -- Atlanta, GA -- 1074551
Current Page: 1 / 1

Scopus Quartile Distribution

Quartile distribution chart data is not available

Competency Cloud

GCRIS Competency Cloud

Filters

20141
Reset filters

Settings

Type: Conference Object

Scholarly Output Search Results

Now showing 1 - 1 of 1
  • Thumbnail Image
    Conference Object
    Design and Optimization of a Notional Scramjet by Means of Stream Thrust Analysis and Design of Experiments
    (American Institute of Aeronautics and Astronautics Inc., 2014) Akpolat,M.T.; Toker,K.A.; Genç,M.S.
    Within the scope of this study, a 0-dimensional code is developed by using Stream Thrust Analysis in order to evaluate scramjet cycle performance with respect to selected performance parameters (specific impulse, overall efficiency) and combustion chamber exit temperature. By using the results of this code an analysis employing "Design of Experiments" (DoE) is performed to determine the most effective input parameters and/or interactions on the scramjet performance. The results showed that most effective input parameter for all of the selected parameters is fuel/air ratio. Selected parameters are evaluated first individually then simultaneously. The purpose of evaluating the performance parameters simultaneously is to determine the input parameter set which gives the highest values of specific impulse and overall efficiency while giving the lowest value of combustion chamber exit temperature. As a result the input parameter sets for different cases are determined.