RESEARCH OBJECTIVES OF TRANSONIC AERODYNAMICS BRANCH

FOR NEXT FIVE YEARS

Develop advanced methods for achieving favorable aerodynamic

interference between wing and engine nacelles.

Develop practical variable geometry airfoil and wing configu

rations to achieve significant regions of laminar boundary

layer over a wide region of flight conditions.

Develop variable geometry fighter wing configurations with

improved maneuver ability, subsonic cruise and supersonic

capability in one configuration.

Develop advanced aerodynamic control systems for various

types of aircraft.

Develop advanced high lift systems for supercritical airfoils

at high Reynolds numbers.

Continue development of improved airfoils for general aviation

and helicopter applications.

Exploit yet unanticipated new aerodynamic concepts.

PROJECTED EXPERIMENTAL TRANSONIC RESEARCH IN 1982

Airfoil Research.- Investigations of advanced high lift systems and

improved airfoils for general aviation applications^including agricultural

airplanes,will be conducted in the low turbulence pressure tunnel. Investi

gations of airfoils for low Reynolds number, high speed applications such

as helicopters will continue in the 6- by 28-inch tunnel. Investigations

of airfoils designed for high Reynolds number, high speed applications such

as span loader type aircraft will continue in the 8- by 26-inch cryogenic

tunnel. Investigations of airfoils intended to achieve substantial regions

of laminar boundary layer on the surfaces will be continued in the 8-foot

transonic pressure tunnel.

Configuration Research.- Investigations of means for improving the

aerodynamic efficiency of high subsonic speed cruise aircraft will continue

in the 8-foot transonic pressure tunnel. Included will be research on

advanced methods for achieving favorable aerodynamic interference between

the wing and engine nacelle, variable geometry wing configurations intended

to achieve significant regions of laminar boundary layer on the surfaces

over a wide range of flight conditions.and as yet unanticipated new concepts,

Also, investigations will be conducted of variable geometry fighter configu

rations intended to achieve improved maneuverability, subsonic cruise, and

supersonic capability in one configuration.

The National Transonic Facility will conduct investigations of all

types of configurations in full scale Reynolds numbers.

TSAB INPUT TO OBJECTIVES FOR APPROVED AERONAUTICS1 DIRECTORATE PROGRAM

i

OBJECTIVE

Develop means for improving the cruise

efficiency of transport and high performance

general aviation aircraft.

Provide data bank for feasible controls on

high efficiency transport configuration with

supercritical wing.

3. Perform investigations in the 8-foot transonic

pressure tunnel in support of other NASA

organizations and government agencies as

required.

4. Improve analytical methods for the design and

prediction of characteristics of airfoils.

5. Improve quality and capability of airfoil

experimental equipment and techniques.

6. Design and investigate improved airfoils for

all classes of aircraft.

RESULTS EXPECTED BY MARCH 30, 1980

1. Demonstrate by wind tunnel tests favorable

aerodynamic interference for at least one

high efficiency supercritical wing-powered

nacelle combination.

2.a. Complete second phase of investigation of

horizontal tail configurations,

b. Essentially complete construction of semispan

model for initial investigation of lateral

controls.

3. Investigate characteristics of fighter

configurations with forward swept wings for

Dept. of Defense.

4. Develop means for reliably predicting low

speed maximum lift.

5. Determine effect of sidewall boundary layer

on measured airfoil characteristics in 6- by

19-inch transonic wind tunnel.

6. Investigate flapped, general aviation airfoil

designed to achieve significant extent of

laminar boundary layer.

TRANSONIC AERODYNAMICS BRANCH ACCOMPLISHMENTS

DESIGNED AND INVESTIGATED SUPERCRITICAL WING FOR NAVY ALCM

(AIR LAUNCHED CRUISE MISSILE) )

DESIGNED AND INVESTIGATED A FAMILY OF MEDIUM SPEED AIRFOILS

AND A GENERAL AVIATION LAMINAR FLOW AIRFOIL

DESIGNED AND INVESTIGATED NATURAL LAMINAR FLOW GLOVE FOR

TACT AIRPLANE

COMPLETED WALL INTERFERENCE, ACOUSTIC AND TURBULENCE

MEASUREMENTS IN THE 8-FOOT TPT

CONDUCTED AIRFOIL CONFERENCE

TsAB COOPERATIVE PROGRAMS

1. KC-135 Winglet Flight Research and Demonstration (LRC, DFRC, USAF/FDL)

2. Navy ALCM Supercritical Wing Investigation (LRC, General Dynamics)

3. TACT Natural Laminar Flow Glove Investigation (LRC, DFRC)

4. Forward Sweep Wing Maneuvering Aircraft Investigation (LRC, USAF/FDL(General Dynamics, Rockwell)

5. Blown Canard-Wing Maneuvering Aircraft Investigation (LRC, USN,(Rockwell)

6. Laser Angle of Attack Concept Investigation (LRC, Boeing)

7. Design and Investigations of Rotorcraft Airfoils (Army Structures Lab)

TsAB PROBLEMS, PERSONNEL, ETC.

Performance Aerodynamics Group

1. The urgent need of last year to obtain at least one programmer -

operator for the Eight-Foot TPT has become a critical need this

year. With the continuing (and worsening) problem with contractdata reduction we are required to do practically all data reduc

tion on site and with a two-shift tunnel operation the workload

is too much for our staff.

2. Our funding situation is likewise critical. We have committed

all funds available to us under 505-11-13-02. Of the two other

RTR's, our funds available under 505-11-23-13 have been reduced

to 25K of which we have spent about 15K, and under 516-53-03-11

(ACEE) we have committed about 75 percent of our available funds

(279K) to date. The remainder will be spent to complete the

propulsion/airframe integration model, the increased twist high

aspect ratio supercritical wing and additional pylons for the

P/A integration model. We are, therefore, left with no funds

for required tunnel systems and equipment.

3. Operating problems are involved with failure of peripheral

8-Foot TPT equipment. We are attempting to replace and refur

bish many of the coolers, pumps, etc., but the fund limitations

noted above have forced delays in procurement of a number of

i terns.

4. Although not a critical problem at present, we have a need for

one or two "fresh out" engineers. At present we have no engi

neers at the assistant project level and all project engineers

are loaded! (We will also effectively lose Stu Flechner andPete Jacobs for at least a total of 7 man-months this year).

Airfoil Research Group

1. Clerical support is needed for the Airfoil Research Group.

The basic needs are telephone answering services for 16 people

in the group offices and the LTPT/6x28 facility, filing and

record keeping, some on-site typing and possibly some help

with figure preparation.

2. The copying machine at ARG is performing marginally at best.

The machine is in a state of disrepair much of the time, and

the copies are poor when it does run. This machine is used

by Training Branch personnel and Defence Contract Audit Agency

personnel as well as ARG and OSD personnel.

TsAB PROBLEMS, PERSONNEL, ETC.- Cont'd:

3. There is a great deal of discussion at LRC and in other aerodynamiccircles concerning the need for more low Reynolds-number airfoiltesting (RPV's Mars airplanes and high-altitude vehicles, etc.).The LTPT will be well suited for this type of testing when therennovation is completed. However, more personnel will be neededin this area to accomplish this additional research.

DESIGN PRESSURE DISTRIBUTIONS

FOR MEDIUM-SPEED AIRFOILS

R = 14 x 106 - 0.30 (CALCULATED)

AA = 0.72 M = 0.68

MS(1) - 0313 MS(1) - 0317

SECTION DATA FOR 13 PERCENT LOW AND MEDIUM_SPEEDAIRFOILS

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