NASA STTR 2019-I Solicitation

Proposal Summary

 19-1- T15.01-3721
 Distributed Electric Propulsion (DEP) Vehicles toward Urban Air Mobility (UAM) and Regional Airliners
 Vortex Control for Low-Noise DEP Urban Aircraft
Name:  SurfPlasma
Name:  University of Florida
Street:  8722 Northwest 9th Place
Street:  207 Grinter Hall, PO Box 115500
City:  Gainesville
City:  Gainesville
State/Zip:  FL 32606-7156
State/Zip:  FL 32611-5500
PHONE:  (810) 516-0991
PHONE:  (352) 392-9267

Principal Investigator (Name, E-mail, Mail Address, City/State/Zip, Phone)

William Lear
8722 NW 9th Pl Gainesville, FL 32606 - 7156
(352) 672-2763

Business Official (Name, E-mail, Mail Address, City/State/Zip, Phone)

Dr. Subrata Roy
8722 NW 9th Pl Gainesville, FL 32606 - 7156
(810) 516-0991
Estimated Technology Readiness Level (TRL) :
Begin: 2
End: 3
Technical Abstract (Limit 2000 characters, approximately 200 words)

Suppression of noise from aircraft is a vital NASA goal, especially important for the vision of Urban Air Mobility. Small urban aircraft may utilize Distributed Electric Propulsion along with advanced structural and electric motor/storage technologies to achieve the necessary flight capability. However, these aircraft utilize propellers or fans to achieve the necessary thrust, with attendant community noise issues. We propose to suppress perceived noise, especially during takeoff and landing in urban areas, by limiting the formation of vortical structures near the propulsor tips and trailing edges.


Tip vortices are common for airfoils, best illustrated by aircraft wings. The pressure difference between top and bottom creates a secondary flow, with a resulting vortex that increases noise and reduces lift. Winglets are effective in countering this effect. However, rotating airfoils – propellers and fans – cannot utilize winglets. Instead we propose to limit the secondary flow and tip vortex by utilizing thin, surface-mounted plasma actuators placed near the rotating blade tip.


SurfPlasma Inc. is a world leader in plasma actuator technology, having developed boundary layer control devices for many applications, including technology effective in the control of high speed air flows, relevant to aircraft propulsors even at low vehicle speeds. Also demonstrated is a technique for providing the required voltage to rotating systems. The overall objective of the current project is to demonstrate feasibility of plasma actuator-based flow control in rotating systems in order to achieve significant suppression of rotor-induced noise, without loss of thrust.


Development of this technology will benefit society by helping to enable more efficient intra-city personal transportation, with low infrastructure impact. Noise suppression technology would enhance acceptance of UAM vehicles and increase livability in urban areas and eventually impact larger aircraft and terrestrial fans.

Potential NASA Applications (Limit 1500 characters, approximately 150 words)

Serpentine DBD actuators are a promising vortex control concept consistent with the mission described by NASA’s Strategic Implementation Plan. In the present proposal, they promise to help enable the vision of UAM by removing community noise as a major obstacle. This technology could in addition benefit many future NASA collaborative projects such as takeoff and landing of the various NASA ARMD N+2 to N+3 concepts, including the D8 Double Bubble, the Blended Wing Body, and the Hybrid Wing Body.

Potential Non-NASA Applications (Limit 1500 characters, approximately 150 words)

With a potential market size of 500B, about two dozen companies including BoeingAirbus, and Uber are designing aerial taxi planes. Almost all promise to build an electric aircraft to eliminate noise and pollution associated with helicopters and jetliners. Successful implementation of this technology would help enable them to operate flexibly in many environments, including the UAM scenario.

Duration: 13

Form Generated on 06/16/2019 22:58:23