The document summarizes a CFD analysis of NASA's ADP fan geometry conducted by Yidi Tang. The analysis included constructing computational grids of over 5.5 million cells and simulating three operating conditions (SLTO, approach, cutback). The computed flow rates and bypass ratios showed good agreement with NASA's test data. The validated CFD model could be used to analyze the fan performance and validate a body force model.

1. CFD Analysis of NASA’s ADP Fan
(Full report available upon request)
Yidi Tang (Ted)
1

2. Overview and Objectives
Meridional drawing of the ADP Fan geometry
• ADP is an abbreviation of Advanced Ducted
Propulsor which consists of Fan Rotor, Fan
Exit Guide Vane (FEGV) and Core Inlet Guide
Vane (CIGV)
• My job is to construct 3d computational grids
conforming to this geometry and implement
CFD analysis with StarCCM and validate the
results with NASA’s calculation and test data
2

3. Grids Features
Total Cells: 5.5M
Far-field is 60-time length
scale of ADP
3
3D grids
on stator
3D grids
on rotor

4. CFD Analysis
• Three working conditions are included in CFD calculation: SLTO (Sea-
level take off), approach and cutback. According to NASA’s report, the
main variable is rotation speed of the rotor
• Ambient conditions are set to Standard Sea-level Conditions
4

5. CFD Analysis
5
0
10
20
30
40
50
60
70
80
90
100
1 1.05 1.1 1.15 1.2 1.25 1.3 1.35
PercentPassageHeight
Dimensionless Total Pressure (Ref.2)
Fan Total Pressure Radial Profiles
Ted
NASA
Test
0
10
20
30
40
50
60
70
80
90
100
1 1.02 1.04 1.06 1.08 1.1 1.12
PercentPassageHeight
Dimensionless Total Temperature (Ref.2)
Fan Total Temperature Radial Profiles
Ted
NASA
Test
SLTO
RPM 8750
Cutback
RPM 7525
Approach
RPM 5425
SLTO
RPM 8750
Cutback
RPM 7525
Approach
RPM 5425

6. CFD Analysis
Operating Point Measured Flow
Rate (lbs/sec)
Computed Flow
Rate (lbs/sec)
Measured By-pass
Ratio
Computed By-pass
Ratio
SLTO 79.20 79.95 11.50 11.69
Cutback 68.10 69.21 10.70 10.95
Approach 49.10 50.50 9.90 10.26
6

7. Summary
• Under the limitations of computation ability and grids size (5.5 M), a
practical and accurate computational model has been successfully
established, whose results show a good agreement with NASA’s test
data and simulation data;
• The results of these simulations could be used to validate a body
force computational model;
7

8. References
• (1) Jeracki, R. J. (February 2006). Comprehensive Report of Fan Performance From Duct Rake
Instrumentation on 1.294 Pressure Ratio, 806 ft/sec Tip Speed Turbofan Simulator Models. Glenn
Research Center, Cleveland, Ohio: NASA TM-2006-213863;
• (2) Tweedt, D. L. (October 2014). Computational Aerodynamic Simulations of an 840 ft/sec Tip
Speed Advanced Ducted Propulsor Fan System Model for Acoustic Methods Assessment and
Development. Cleveland, Ohio: NASA CR-2014-218129;
• (3) Antoine, P. (June 2015). CFD Analysis of NASA ADP Fan. Syracuse University, Syracuse, New
York;
8