Transonic Small-Disturbance Theory/Integral Boundary Layer Airfoil Data for the Low-Fidelity Common Research Model

Creators

Jeffrey D. Taylor, Utah State UniversityFollow
Douglas Hunsaker, Utah State UniversityFollow

Description

Lift, Drag, and Moment Coefficient data for the Low-Fidelity Common Research Model wing airfoil sections.

Author ORCID Identifier

Jeffrey D. Taylor https://orcid.org/0000-0003-3719-0955

Douglas Hunsaker https://orcid.org/0000-0001-8106-7466

OCLC

1236212414

Document Type

Dataset

DCMI Type

Dataset

File Format

.txt

Publication Date

12-1-2020

Funder

NASA, National Aeronautics and Space Administration

Publisher

Utah State University

Award Number

NASA, National Aeronautics and Space Administration 80NSSC18K1696

Methodology

The airfoil profile files contain the x and y coordinates of the airfoil surface, normalized by the local chord for the airfoil sections located at 0, 10, 15, 20, 25, 30, 35, 37, 40, 45, 50, 55, 60, 65, 70, 75, 80, 85, 90, 95, and 100% semispan of the Common Research Model wing. Data were extracted from a CAD file of the uCRM-9 wing geometry described in [Brooks, T. R., Kenway, G. K. W., and Martins, J. R. R. A., “Benchmark Aerostructural Models for the Study of Transonic Aircraft Wings,” AIAA Journal, Vol. 56, No. 7, July 2018 pp. 2840- 2855. (doi:10.2514/1.J056603)] and available at https://data.mendeley.com/datasets/gpk4zn73xn/1 (doi:10.17632/gpk4zn73xn.1)

The airfoil database files contain the Lift, Drag, and Moment Coefficient data for the Low-Fidelity Common Research Model wing airfoil sections. Data were collected for the airfoil sections located at 0, 10, 15, 20, 25, 30, 35, 37, 40, 45, 50, 55, 60, 65, 70, 75, 80, 85, 90, 95, and 100% semispan, as a function of flap deflection of a parabolic flap spanning the aft 30% of the chord, angle of attack, Reynolds number, and Mach number. The data were obtained using the Transonic Small-Disturbance Theory/Integral Boundary layer method from [Fujiwara, G. E. C., Chaparro, D., and Nguyen, N., “An Integral Boundary Layer Direct Method Applied to 2D Transonic Small-Disturbance Equations,” AIAA 2016-3568, 34th AIAA Applied Aerodynamics Conference, Washington, D. C., 13-17 June 2016. (doi:10.2514/6.2016-3568)]

*See [Taylor, J.D. and Hunsaker D.F., "Characterization of the Common Research Model Wing for Low-Fidelity Aerostructural Analysis," AIAA SciTech 2021 Virtual Forum, 11-15 & 18-22 January 2021] for additional details about the data collection process.

Related Content

Taylor, J.D. and Hunsaker D.F., "Characterization of the Common Research Model Wing for Low-Fidelity Aerostructural Analysis," AIAA SciTech 2021 Virtual Forum, 11-15 & 18-22 January 2021.

Language

eng

Code Lists

See README.txt file.

Comments

The dataset includes 42 txt files. Twenty-one of these files contain the x and y coordinates of the 21 airfoil sections at the spanwise locations listed above (with zero flap deflection). The other 21 files contain airfoil data with the corresponding flap deflection, angle of attack, Reynolds number, and Mach number for each of the 21 airfoil sections (listed above) of the Low-Fidelity Common Research Model. The files are named as follows:

airfoil profiles:

uCRM-9_wr0_profile.txt: x and y coordinates, normalized by the local wing chord, for the airfoil section located at 0% semispan (wing root)

uCRM-9_wr10_profile.txt: x and y coordinates, normalized by the local wing chord, for the airfoil section located at 10% semispan

uCRM-9_wr15_profile.txt: x and y coordinates, normalized by the local wing chord, for the airfoil section located at 15% semispan

uCRM-9_wr20_profile.txt: x and y coordinates, normalized by the local wing chord, for the airfoil section located at 20% semispan

uCRM-9_wr25_profile.txt: x and y coordinates, normalized by the local wing chord, for the airfoil section located at 25% semispan

uCRM-9_wr30_profile.txt: x and y coordinates, normalized by the local wing chord, for the airfoil section located at 30% semispan

uCRM-9_wr35_profile.txt: x and y coordinates, normalized by the local wing chord, for the airfoil section located at 35% semispan

uCRM-9_wr37_profile.txt: x and y coordinates, normalized by the local wing chord, for the airfoil section located at 37% semispan (Yehudi Break)

uCRM-9_wr40_profile.txt: x and y coordinates, normalized by the local wing chord, for the airfoil section located at 40% semispan

uCRM-9_wr45_profile.txt: x and y coordinates, normalized by the local wing chord, for the airfoil section located at 45% semispan

uCRM-9_wr50_profile.txt: x and y coordinates, normalized by the local wing chord, for the airfoil section located at 50% semispan

uCRM-9_wr55_profile.txt: x and y coordinates, normalized by the local wing chord, for the airfoil section located at 55% semispan

uCRM-9_wr60_profile.txt: x and y coordinates, normalized by the local wing chord, for the airfoil section located at 60% semispan

uCRM-9_wr65_profile.txt: x and y coordinates, normalized by the local wing chord, for the airfoil section located at 65% semispan

uCRM-9_wr70_profile.txt: x and y coordinates, normalized by the local wing chord, for the airfoil section located at 70% semispan

uCRM-9_wr75_profile.txt: x and y coordinates, normalized by the local wing chord, for the airfoil section located at 75% semispan

uCRM-9_wr80_profile.txt: x and y coordinates, normalized by the local wing chord, for the airfoil section located at 80% semispan

uCRM-9_wr85_profile.txt: x and y coordinates, normalized by the local wing chord, for the airfoil section located at 85% semispan

uCRM-9_wr90_profile.txt: x and y coordinates, normalized by the local wing chord, for the airfoil section located at 90% semispan

uCRM-9_wr95_profile.txt: x and y coordinates, normalized by the local wing chord, for the airfoil section located at 95% semispan

uCRM-9_wr100_profile.txt: x and y coordinates, normalized by the local wing chord, for the airfoil section located at 100% semispan (wing tip)

airfoil_data:

wr_0_dataset.txt: airfoil data for the airfoil section located at 0% semispan (wing root)

wr_10_dataset.txt: airfoil data for the airfoil section located at 10% semispan

wr_15_dataset.txt: airfoil data for the airfoil section located at 15% semispan

wr_20_dataset.txt: airfoil data for the airfoil section located at 20% semispan

wr_25_dataset.txt: airfoil data for the airfoil section located at 25% semispan

wr_30_dataset.txt: airfoil data for the airfoil section located at 30% semispan

wr_35_dataset.txt: airfoil data for the airfoil section located at 35% semispan

wr_37_dataset.txt: airfoil data for the airfoil section located at 37% semispan (Yehudi Break)

wr_40_dataset.txt: airfoil data for the airfoil section located at 40% semispan

wr_45_dataset.txt: airfoil data for the airfoil section located at 45% semispan

wr_50_dataset.txt: airfoil data for the airfoil section located at 50% semispan

wr_55_dataset.txt: airfoil data for the airfoil section located at 55% semispan

wr_60_dataset.txt: airfoil data for the airfoil section located at 60% semispan

wr_65_dataset.txt: airfoil data for the airfoil section located at 65% semispan

wr_70_dataset.txt: airfoil data for the airfoil section located at 70% semispan

wr_75_dataset.txt: airfoil data for the airfoil section located at 75% semispan

wr_80_dataset.txt: airfoil data for the airfoil section located at 80% semispan

wr_85_dataset.txt: airfoil data for the airfoil section located at 85% semispan

wr_90_dataset.txt: airfoil data for the airfoil section located at 90% semispan

wr_95_dataset.txt: airfoil data for the airfoil section located at 95% semispan

wr_100_dataset.txt: airfoil data for the airfoil section located at 100% semispan (wing tip)

Disciplines

Aerospace Engineering

License

This work is licensed under a Creative Commons Attribution 4.0 License.

Identifier

https://doi.org/10.26078/8nv8-yj03

Recommended Citation

Taylor, J. D., & Hunsaker, D. (2020). Transonic Small-Disturbance Theory/Integral Boundary Layer Airfoil Data for the Low-Fidelity Common Research Model. Utah State University. https://doi.org/10.26078/8NV8-YJ03

Checksum

5511dea3260f372194c075bb23fcf80b