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"{' , RESUME

JIM A. PENLAND

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Jim A. Penland graduated from Brevard Junior College in 1943, served as a bomber

pilot in the United States Air Corps in the Southwest Pacific Theater during World _ War .

II, and received the Bachelor of Science degree in Mechanical Engineering, Aeronautical . ~ :. .~

Option, from North Carolina State College in 1948. He joined the Langley I..aIIoratoryof

the' NACA (no~ NA?A) that year where he has been' engaged continuously ·ia !typer-sonic

aerodynamiC, and configuration research. He was associated with the X-l5 research

airplane project from its conception and participated ~n the hyp~rsonic tesllag of t~

many variations of this conf~gurati.onr. He was engaged in Studies of adianced air -

breathing hypersonic cruise . transports and airbreathing launch v~icles_.prior. to h.is

retirement from the NASA-Langley Research Center after about 35 years of service. Ate

has authored or coauthored 41 technical papers which attest.to his many conttibutions 1.0

a broad spectrum of aerospace v;hicles. Of particular note are his ml'es in the

development and use of advanced research facilities to obtain model data and the

-----'-~~~~......AI.in.LIt .... ecLjrpfo'Jru;e....,tation and use oLthes..e_da:ta.i0-Pr-e_dic:t......vehlcle...JLe.rf.mmance over the: compI,~e'-"'te,...,·~~~~_

spectrum of flight ranging from low subsonic to hypervelocity flight l"egmes.. Mr c

Penland holds a c~mmercial pilot'scertificate, and is active in the Experimenlall Aircraft

. Association and The Academy of Model Aeronautics.

-...... ('\

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Current Employei":

Length of Employment:

Consultant:

Security Clearance:

General Experience

Dates Supervisors

1948 - 1960

(C. H. McLellan)

Related Experience

Dates Supervisors

1948 - 1980

(c. H. McLellan) (A. L. Nagel) (W. J. Nelson)

(F. S. Kirkham) (R. A. Jones)

Dates Supervisors

1953 - 1980

(c. H. McLellan) (A. L. Nagel)

(F. S. Kirkham)

I

PRINCIPAL ENGINEER/CONS~ JIM A. PENLAND I

Self Employed I Consultant

6 years

(available time negotiable)

Secret

Experience

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/~~ L-4-d --..v if 1Ia.-v ~

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Active in the developmental design of supersonic and hypersonic wind tunnels, their instrumentation, calibration, and operation. Supervised engineers and technicians in day-to-day operational tests to obtain force and moment data, pressure distributions, and heat transfer data. Participated in the development and design of wind tunnel test procedures and models for all speed environments.

Experience ;

Extensive experience with the validation of aerodynamic theory with experiment and use of the high speed computer to determine integrated aerodynamic parameters. Familiar with high vacuum techniques, including mechanical and diffusion pumps, measuring procedures and problems at high Knudson numbers, and thermal transpiration. Understanding of flight characteristics of full scale subsonic aircraft from forty-two years as licensed pilot.

Experience

Contributions made to the hypersonic impact theory, to thermally destructible model design, to hypersonic configuration wing design, and to the extrapolation of wind tunnel data to flight through use of boundary layer theory. Made numerous aerodynamic force, stability, and control studies on preliminary and final versions of the X-15, X-I?, ICBM re-entry shapes, the Mercury and Apollo modules, the Sprint missile, airbreathing hypersonic transports, and the X-24C configurations.

FEB 11198E - 25-

Specialized Experience

Dates Supervisors

1948 - 1962

(C. H. McLellan)

Publications

See attached list.

Formal conference papers were presented on the aerodynamics of the X-15, re-entry shapes, the hypersonic transport, and the X-24C project.

Experience

Participated in the development of methods of flow visualiza­tion for all speed ranges, including, Schlieren, shadowgraph, '. afterglow, vapor screen, oil flow, temperature sensitive paint, tuft study, and smoke flow. Wrote specifications for optical windows, mirrors, and optics for hypersonic schlieren systems. Experienced in photographic experimental processes to enhance photographs made under low light conditions. Was on design team of the LRC ll-inch M=7, and the continuous flow M=lO hypersonic tunnels including the model support systems with combined angle of attack and angle of side slip capability.

- 26-tEa 11 1986

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PUBLICATIONS

Jim A. Penland

1. Penland, J. A.: A Profi1e of Jet Progress. Published in Southern Enginee~ North Carolina State College, Vol. X, No.1, November 1947, pp. 12-14 and page 20. (Student Publication) •

2. Penland, J. A., Ridyard, H. W., and Fetterman, D. E.: Static Longitudinal Stability Data From an Exploratory Mach Number of 6.86 of an Airplane Configuration Trapezoidal Planform. NACA RM L54L03B, January 1955.

Lift, Drag, and Investigation at a Having a Wing of

0 • ••

3. Ridyard, H. W.,. Fetterman, D. E., and Penland, J. A.: Static Lateral Stability Data From an Exploratory Investigation at a Mach Number of 6.86 of an Airplane Configuration Having a Wing of Trapezoidal Planform. NAC~ RM L55A21a, February 1955.

4. Fetterman, D. E., Penland, J. A., and Ridyard, H. W.: Static Longitudinal and Lateral Stability and Control Characteristics of an Airplane Configuration Having a Wing of Trapezoidal Planform. NACA RM L55C04, ...

"

:

April 1955. ' .•

5. Penland, J. A., Fetterman, D. E., and Ridyard, H. W.: Static Longitudinal and Lateral Stability and Control Characteristics of an Airplane Configuration Having a Wing of Trapezoidal Planform with Various Tail Airfoil Sections and Tail Arrangements at a Mach N~mber of 6.86. NACA RM L5517, August 1955.

6.

7.

Penland, J. A. and Fetterman, D. E.: The Effects at a Mach Number of 6.86 of Drag Brakes on the Lift, Drag, and Pitching Moment of an Ogive Cylinder. NACA ru1 L55K23, March 1956.

Penland, J. A.: Aerodynamic Characteristics of Mach Number 6.86 and Angles of Attack up to 90°. 1957. (Formerly RM L54A14~ 1~54)

a Circular Cylinder at -'. NACA 'I'N 386'" January.,-

8. Penland, J. A. and Armstrong, W.O.: Preliminary Aerodynamic Data

9.

Pertinent to Manned Satellite Reentry Configurations. NACA Conference on High-Speed Aerodynamics, f.ioffett Field, California, March 1958 •.

Penland, J. A. and Armstrong, W. 0.: Preliminary Pertinent to l-lanned Satellite Reentry Configurations. July 19513.

Aerodynamic Data NaCA RM L58E13a,

10. Penland, J. A. and Fettenman, D. B.: High-Speed Static Stability USAF-USN-~iACA Conference on

Los Anqeles, California. Characteri~tics of the x-tS Airplane. Progress of X-15 Project, July 28-29, 1958,

-27-

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11. Lord, D. R. , Smi th, F. M. , and Penland, J. A. : Aerodynamic Characteristics of Various Missile Configurations at Angles of Attack from 0° to 90° for ~1ach Numbers from 2 to 7. 40th Meeting of the BuI:tblebee Aerodynamics Panel, May 1959.

12. Penland, J. A. and Carroll, C. M.: Static Longitudinal and Lateral Stability Parameters of Three Flared-Skirt Two-Stage Missile Configurations at a Mach Number of 6.86. NACA RM L57015, June 1959.

13. Penland, J. A. and Armstrong, W. 0.: Static Longitudinal Aerodynamic Characteristics of Several Wing and Blunt-Body Shapes Applicable for Use as Reentry Configuratio~~ at a Mach Number of 6.8 and Anqles of Attack up to 90°. NASA TM X-65, Octoher 1959.

14. Fetterman, and Penland, - J. A.: Static Longitudinal, Directional, and Lateral Stability and Control Data from an Investigation at a Mach Number of 6.83 of Two Developmental X-15 Airplane Configurations. NASA TM X-209, March 1960.

15. Penland, J. A. and Fetterman, D. E.Static Longitudinal, Directional, .and LA.t-:r3l St"lbil tty and Control Data at a Mach Number of 6.83 of the Final Configuration of the X-15 Research Airplane. NASA TM X-236, April 1960.

16. Penland, J. A.: Static Longitudinal Stability of a Missile Configuration with Various Nos-e Shapes and Flared Afterbodies at a l1ach NuI!lher of 6.82. NASA TM X-274, June 1960.

17. Penland, J. A.: Aerodynamic Force Characteristics _of a Series of Lifting Cone and Cone-Cylinder Configurations at a Mach Number of 6.83 and Angles of Attack up to 130°. NASA TN D-840, June 1961.

18. Penland, J. A. (Provided Results and Discussions): Compiled by Robert w. Rainey: Summary of Aerodynamic Character~stl.CS of Low-Ll.ft-Drag-Rarro Reentry Vehicles from Subsonic to Hypersonic Speeds. NASA TN X-588, SeptelT'ber 1961.

19. Penland, J. A.: A Study of the Aerodynamic Characteristics of a Fixed Geometry Paraqlider Configuration and Three Canopies with- Simulated Variable Canopy Inflation at a Mach Number of 6.6. NASA TN D-1022, March 1962. -:

20. l?enland, J. A.: The Hypersonic Aerodynamic Characteristics of the X-2 Research Airplane at H = 6.~n. Hemo for Files, October 1962.

21. "Penland, J. A.: Theoretical and Experimental Longitudinal and Lateral Static Stability and Control Characteristics of a Series ofAxisvmmetric High Drag Reentry Vehicles. NASA Tn X-770, Harch 1963.

22. Penland, J. A.: A Study of the Stability and Location of the Center of Pressure on Sharp, Right Circular Conp.s at Hypersonic Speeds. NASA TN 0-2283, Hay 1964.

23. Penland, J. A.: MaxiMum Lift-Drag Ratio Characteristics at Rectanqular and Delta Wings at Mach 1i.9. NASA TN D-2925, August 1965.

:

-28- FEB 11 7986

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24. Penland, J. A.: Effect of Body Nose Bluntness, Control Planform Area, and Leadinq Enge Bluntness no Aerodynamic Control of a 5° Semi vertex Cone at M = 6.9. NASA TN D-3460. June 1966.

25. Penland, J. A., Edwards, C. L. W., Witcofski, R. D.,. and Marcum, D. C.: A Comparative Aerodynamic Evaluation of Two Hypersonic Cruise Aircraft Configurations Oed ved from Trade-Off Studies. NASA TM X-1436, October 1967 (CONFIDENTIAL)

. 26. Penland, J. A. and Bernot, P. T.: Aerodynamic Characteristics of Three

Axisymmetric Low-Fineness-Ratio Reentry Shapes at Mach 6.9. NASA TN 0-4122, August 1967.

27. Rainey, R. W. and Penland, J.A.: Newtonian Aerodynamics of Bodies of Revolution and Toe-in - Rolled-Out Surfaces. NASA L,YP 549, February 1968.

28. Penland, J. A. and Romeo, D. J.: Advances in Capabili ty--Wind Tunnel to . Flight Reynolds No. 71-132. AIAA 9th Aerospace Sciences Meeting,

Hypersonic Extrapolation Number. AIAA Paper January 1971.

29. Penland, J. A. and Romeo, D. J.: Advances in Hypersonic Extrapolation Capability--Wind Tunnel to Flight Reynolds Number. Journal of Aircraft, Vol. 8, No. 11, November 1971, pp. 881-884.

30. Penland, J. A., Creel, T. R., .Jr., Howard, Longitudinal, Lateral, and Directional Characteristics of a Research Airplane Concept a 65 0 Swept Delta Wing. NASA TN D-7633.

F. G.: Low Speed Static Stability and Control

Having a Large Fuselage and

32. Penland, J. A.. Jr. : LO''''-SpeedAerodynamic

:

Characteristics and Creel, T. R. ,

of a Lifting-Body NASA TN D-7851.

Hypersonic Research Aircraf t ~.-Configuration.

33. Penland, J. A., Fournier, R. H., and Marcum, D. C., Jr.: Aerodynamic Characteristics of a 70 0 Swept Delta Wing Hypersonic Research Airplane at Mach 1.50 to 2.86. NASA TN 0-8065, December 1975.

34. Weidner, J. P., Small, Hypersonic Research Conference, Palo Alto,

w. J., and Penland, J. Airplane Concepts. California, July 1976.

A.: Scramjet Integration on AlAA/SAE 12th Propulsion

35. Weidner, J. P., Small, W. J., and Penland, J. A.: Scramjet Inteqration on of Aircraft, Vol. 14, Hypersonic Research Airplane Concepts. Journal

No.5, t1ay 1977.

36. Penland, .J. A., Dillon, J. L., and Pittman, J. L.: An Aerodynamic Anaiysis of Several Hypersonic Research Concepts from H = 0.2 to 6.0. AIM 16th Aerospace Sciences Meeting, Huntsville, Alabama, January 1978.

.,

-29-fEB 11 1986

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37. Penland, Je 1\..., Creel, T. R., Jr., and. Dillon, J. L.: Aerodynamic

38.

Characteristics of a Model of a Hypersonic Research Airplane Concept Having a 70° Swept Double-Delta Wing al: Mach No. 0.2. NASA TP-1252,

May 19'm.

Penland, J. A., Dillon, J. L., and PittJ:lan, Analysis of Several Hypersonic Research Airplane 6. o. Journal of Aircr~ft, November 1978.

J. L. : M Aerodynamic Concepts from"11 = 0.2 to

39. Penland, J. A., Hallissy, J. B., and Dillon, J. L.: Aerodynamic Characteristics of a Hypersonic Research Airplane Concept Having a' 700

Double-Delta Wing at Mach Number from 0.8 to 1.2 with SUmmary of Data from 0.2 to 6.0. NASA TP-1552, December 1979. :

40. Penland, J. A., Marcum, D. C. Jr., and Stack,' S. H.: Wall-Temperature Effects on the Aerodynamics of a Hydrogen-Fueled Transport Concept in Mach 8 Blowdown and Shock Tunnels. NASA TP-2159, July 1983.

41. Penland, J. A. and Pittman, J. L.: Aerodynamic Characteristics of a Dist5.nct wi Y1g-Body Configuratj on at Mach 6. Experiment, Theory, and the Hypersonic Isolation Principle. NASA TP 2467, August 1985.

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... "

-" .:

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BIOGRAPHY

Jim A. Penland

Jim A. Penland graduated from Brevard Junior College in 1943, served

as a bomber pilot in the United States Air Corps in the Southwest Pacific

Theater during World War II, and received the Bachelor of Science degree

in Mechanical Engineering, Aeronautical Option, from North Carolina State

College in 1948. He joined the Langley Laboratory of the NACA (now NASA)

that year where he has been engaged continuously in hypersonic aerodynamic

and configuration research. He was associated with the X-15 research

airplane project from its conception and participated in the hypersonic

testing of the many variations of this configuration. ct. t:yMe 4(Jj5

engaged in studies of advanced airbreathing hypersonic cruise transports .;Ji:

and airbreathing launch vehicles~ He has authored or coauthored ~ ~I

technical papers. He holds a commercial pilots' certificate, and is I

active in the Experimental Aircraft Associationx ~J T/,~ A L;!dJl'oi

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It II

I

I I­I

t~EGG.G

CURRENT EMPLOYER:

EMPLOYMENT STA'lUS:

EDUCATION:

JIM A. PENLAND

POS I ]'16N ~ ~-~-4 r,l~.~.' __ -f-

COMPANY PROPRIETARY

CemmitteQ. to Engineering Incorporated ....-tor Consul tant:to r -1', ... +

F\1-~:1 Time as required (or some %) fy~ ~ .' ;) "

~ .n-Le:- '~'71 ",-

B.S., Mechanical ~neeringt North Carolina State U., ~, 1948

.. ~

QUAL • I ;-- ~ tff· IFICATION SUMMARY: -ih'j Ie:; .'1 D04Jreet":...:? I'--- 1'. £ .' ~-

SECURITY CLEARANCE:

EMPLOYMENT HISTORY:

POSITION EMPLOYER (YEARS)

,:;':,,? years general experience !; ()? years specialized experience

SECRET

RESPONSIBILITIES

(Unable to decipher it from what we have in hand. )

LABOR CATEGORY AND STATEMENT OF WORK QUALIFYING EXPERIENCE:

RFP REF. (YEARS) EXPERIENCE

- - - -- -- -----.H~1.1_2L.~ $2. ________ ~HeI'e.-we-need-as-man¥'-specific--references--using--H--- -----C.11 ... , " .J.o statement for which nominated and as many C .1\.1. ',is- different C references as possible for each

different bullet.)

HONORS/PUBLICATIONSjOTHER RELEVANT DATA:

Penland, J. A.: A Profile of Jet Progress. Published in southern Engineer, North Carolina state College, Vol. X, No.1, November 1947, pp. 12-14 and page 20. (Student Publication)

Penland, J. A., Ridyard, H. W., and Fetterman, D. E.: Lift, Drag, and Static Longitudinal Stability Data From an Explorato~ Investigation at the Mach Number of 6.86 of an Airplane' Configuration Having a Wing of Trapezoidal Planform. NACA RM'L54L03B, Jaunary 1955.

1

COMPANY PROPRIETARY

COMPANY PROPRIETARY

Ridyard, H. W., Fetterman, D. E., and Penland, J. A.: __ Static Lateral. Stability Data from an Exploratory Investigation at a Mach Number of 6.86 of an Airplane Configuration Having a Wing of Trapezoidal Planform. NACA RM L55A2la, February 1955.

Fetterman, D. E., Penland, J. A., and Ridyard, H. W.: Static Longi­tudinal and Lateral Stability and Control Characteristics of an Airplane Configuration Having a Wing of Trapezoidal Planform. NACA RM L55C04, April 1955.

Penland, J. A., Fetterman, D. E., and Ridyard, H. W.: Static Longi­tudinal and Lateral Stability and Control Characteristics of an Airplane Configuration Having a Wing of Trapezoidal Planform wi th Various Tail Airfoil Sections and Tail Arrangments at a Mach Number of 6.86. NACA RM L5517, August 1955.

Penland, J. A. and Fetterman, D. E.: The Effects at a Mach Number of 6.86 of Drag Brakes on the Lift, Drag, and Pitching Moment of an Ogive Cylinder. NACA RM L55K23, March 1956.

Penland, J. A.: Aerodynamic Characteristics of a Circular Cylinder at Mach Number 6.86 and Angles of Attack up to 90°. NACA TN 3867, January 1957. (Formerly RM L54A14, 1954)

Penland, J. A. and Armstrong, W. 0.: Preliminary Aerodynamic Data Per­tinent to Manned Satellite Reentry Configurations. NACA Conference on High-Speed Aerodynamics, Moffett Field, california, March 1958.

Penland, J. A. and Armstrong, W. 0.: Preliminary Aerodynamic Data Pertinent to Manned Satellite Reentry Configurations. NACA RM L58E13a, July 1958.

____________ Penland,_ J~A. __ and.~etterman,_D_._E._: ___ High=Spe_e_d$_tati_c __ S_t.abilij:.y _CDii.I= _____________ _ acteristics of the X-IS Airplane. USAF-USN-NACA Conference on Progress of X-IS Project, July 28-29, 1958, Los Angeles, California.

Lord, D. R., Smith, F. M., and Penland, J. A.: Aerodynamic Characteris­tics of Various Missile Configurations at Angles of Attack from 0° to 90° for Mach Numbers from 2 to 7. 40th Meeting of the Bumblebee Aerodynamics Panel, May 1959.

Penland, J. A. and Carroll, C. M.: Static Longitudinal and Lateral Stability Parameters of Three Flared-Skirt Two-Stage Missile Con­figurations at a Mach Number of 6.86. NACA RM L57015, June 1959.

Penland, J. A. and Armstrong, W. 0.: Static Longitudinal Aerodynamic Characteristics of Several Wing and Blunt-Body Shapes Applicable for Use as Reentry Configurations at a Mach Number of 6.8 and Angles of Attack up to 90°. NASA 'I'M X-65, October 1959.

2

COMPANY PROPRIETARY

<::-n~EGI:.G COMPANY PROPRIETARY

Fetterman, and Penland, J. A.: static Longitudinal, pirectional, and Lateral stability and Control Data from an Investigation at a Mach NUmber of 6.83 of Two Developmental X-1S Airplane Configurations. NASA 'I'M X-209, March 1960.

Penland, J. A. and Fetterman, D. E.: Static Longitudinal, Directional, and Lateral stability and Control Data at a Mach NUmber of 6.83 of the Final Configuration of the X-1S Research Airplane. NASA 'I'M X-236, April 1960.

Penland, J. A.: Static Longitudinal Stability of a Missile Configuration with various Nose -Shapes and Flared Afterbodies at a Mach Ntnnber of 6.82. NASA 'I'M X-274, June 1960.

Penland, J. A.: Aerodynamic Force Characteristics of a Series of Lifting Cone and Cone-Cylinder Configurations at a Mach Number of 6.83 and Angles of Attack up to 130°. NASA TN 0-840, June 1961.

Penland, J. A. (Provided Results and Discussions): Compiled by Robert w. Rainey: Summary of Aerodynamic Characteristics of Low-Lift-Drag-Ratio Reentry Vehicles from Subsonic to Hypersonic Speeds. NASA 'IN X-588, September 1961.

Penland, J. A.: A Study of the Aerodynamic Characteristics of a Fixed Geometry paraglider Configuration and Three Canopies with Simulated variable Canopy Inflation at a Mach Number of 6.6. NASA 'IN 0-1022, March 1962.

Penland, J. A.: The Hypersonic Aerodynamic Characteristics of the x-2 Research Airplane at M = 6.83. Memo for Files, October 1962.

Penland, J. A.: Theoretical and Experimental Longitudinal and Lateral - - -- - -- - - - - - -stati-c- -Stabil-i-ty- arlQ--Control-CharacteI"isti cs.-of---a--Series--of-Axisymme-tric------_________ _

High Drag Reentry Vehicles. NASA 'I'M X-770, March 1963.

Penland, J. A.: A Study of the Stability and Location of the Center of Pressure on Sharp, Right Circular Cones at Hypersonic Speeds. NASA TN 0-2283, May 1964.

Penland, J. A.: Maximum Lift-Drag Ratio Characteristics at Rectangular and Delta Wings at Mach 6.9. NASA TN 0-2925, August 1965.

Penland, J. A.: Effect of Body Nose Bluntness, Control Planform Area, and Leading Edge Bluntness lie Aerodynamic Control of a 5° Semivertex Cone at M = 6.9. NASA 'IN 0-3460, June 1966.

Penland, J. A., Edwards, C. L. W., Wi tcofski, R. D., and Marcwn, D. C.: A Comparative Aerodynamic Evaluation of Two Hypersonic Cruise Aircraft Configurations Derived from Trade-Off Studies. NASA 'I'M X-1436, October 1967 (€ONFI~) - /)Ec,(,A{f/F1~!>

3

COMPANY PROPRIETARY

c:;.",> E13&.G COMPANYPROPR~TARY

Penland, J. A. and Bernot, P. T.: Aerodynamic Charactedstics -of- Three Axisymmetric Low-Fineness-Ratio Reentry Shapes at Mach 6.9. NASA 'IN 0-4122, August 1967.

Rainey, R. W. and Penland, J. A.: Newtonian Aerodynamics of Bodies of Revolution and Toe-in-Rolled-out Surfaces. NASA LWP 549, February 1968.

Penland, J. A. and Romeo, D. J.: Advances in Hypersonic Extrapolation Capability-Wind Tunnel to Flight Reynolds Number. AIAA Paper No. 71-132. AIAA 9th Aerospace Sciences Meeting, January 1971.

Penland, J. A. and Romeo, D. J.: Advances in Hypersonic Extrapolation Capability--:Wind Tunnel to Flight Reynolds NUmber. Journal of },Jrcraft, Vol. 8, No. 11, November 1971, pp. 881-884.

Penland, J. A., Creel, T. R., Jr., Howard, F. G.: Low Speed Static Longitudinal, Lateral, and Directional Stability and Control Characteristics of a Research },J rp1ane Concept Having a Large Fuselage and a 65° SWept Delta Wing. NASA 'IN 0-7633.

Creel, T. R. , Jr. and Penland, J. A.: Low-Speed Aerodynamic Char­acteristics of a Hypersonic Research Airplane Concept Having a 70° SWept Delta Wing. NASA 'I'M X-71974, August 1974.

Penland, J. A. and Creel, T. R., Jr.: Low-Speed Aerodynamic Char­acteristics of a Lifting-Body Hypersonic Research },Jrcraft Configuration. NASA 'IN 0-7851.

Penland, J. A., Fournier, R. H., and Marcum, D. C., Jr.: Aerodynamic Characteristics of a 70° Swept Delta Wing Hypersonic Research Airplane at Mach 1.50 to 2.86. NASA 'IN 0-8065, December 1975.

-- --- -- - - - -- -We-icmer-,- J.P.-,--Small-,-W.- -.1-.-,- and-Fenland,--J.--A.-: - -Scramjet- Integratioo------- - --- - - --on Hypersonic Research Airplane Concepts. AIM/SAE 12th propulsion Conference, Palo Alto, California, July 1976.

Weidner, J. P., Small, W. J., and Penland, J. A.: Scramjet Integration on Hypersonic Research Airplane Concepts. Journal of Aircraft, Vol. 14, No.5, May 1977.

Penland, J. A., Dillon, J. L., and Pittman, J. L.: An Aerodynaritic Analysis of Several Hypersonic Research Concepts from M = 0.2 to 6.0. AIAA 16th Aerospace Sciences Meeting, Huntsville, Alabama, January 1978.

Penland, J. A., Creel, T. R., Jr., and Dillon, J. L.: Aerodynamic Characteristics of a Model of a Hypersonic Research Airplane Concept Having a 70° Swept Double-Delta Wing at Mach No. 0.2. NASA TP-1252, May 1978.

4

COMPANY PROPRIETARY

~n~EGt:G COMPANY PROPRIETARY

Penland, J. A., Dillon, J. L., and Pittman, J. L.: -- An AeI'odynamiC

J Analysis ?f Several Hyperson~c Research Airplane Concepts ~rom MPen~and, J. A., 01. 11 on , J. L., and Pl.ttman, J. L.: An AerodynamJ.c Analysl.s of Several Hypersonic Research Concepts from M = 0.2 to 6.0. AIAA 16th Aerospace Sciences Meeting, Huntsville, Alabama, January 1978.

Penland, J. A., Hallissy, J. B. , and Dillon, J. L. : Aerodynamic Characteristics of a Hypersonic Research Airplane Concept Having a 70° Double-Delta Wing at Mach Number from 0.8 to 1.2 with Summary of Data from 0.2 to 6.0. NASA TP-1552, December 1979.

Penland, J. A., Marcum, D. C. Jr., and Stack, S. H.: wall-Temperature Effects on the Aerodynamics of a Hydrogen-Fueled Transport Concept in Mach 8 Blowdown and Shock Tunnels. NASA TP-2159, July 1983.

Penland, J. A. and Pittman, J. L.: Aerodynamic Characteristics of a Distinct Wing-Body Configuration at Mach 6 Experiment, Theory, and the Hypersonic Isolation Principle. NASA TP 2467, August 1985.

EXPECTED ELIGIBILITY FOR PROMOTION TO NEXT HIGHER CATEGORY:

5

COMPANY PROPRIETARY

Fetterman, D. E., Penland, J. A., and Ridyard, H. W.: __ Static'Longi­tudinal and Lateral Stability and Control Characteristics of an Airplane Configuration Having a Wing of Trapezoidal Planform. NACA RM L55C04, April 1955.

Penland, J. A., Fetterman, D. E., and Ridyard, H. W.: Static Longi­tudinal and Lateral Stability and Control Characteristics of an Airplane Configuration Having a Wing of Trapezoidal Planform with various Tail Airfoil Sections and Tail Arrangments at a Mach Number of 6.86. NACA RM L5517, August 1955.

Penland, J. A. and Fetterman, D. E.: The Effects at a Mach Number of 6.86 of Drag Brakes on the Lift, Drag, and Pitching Moment of an Ogive Cylinder. NACA RM L55K23, March 1956.

Penland, J. A.: Aerodynamic Characteristics of a Circular Cylinder at Mach Number 6.86 and Angles of ·Attack up to 90°. NACA 'IN 3867, January 1957. (Formerly RM L54A14, 1954)

Penland, J. A. and Armstrong, W. 0.: preliminary Aerodynamic Data Per­tinent to Manned Satellite Reentry Configurations. NACA Conference on High-Speed Aerodynamics, Moffett Field, California, March 1958.

Penland, J. A. and Armstrong, W. 0.: Preliminary Aerodynamic Data Pertinent to Manned Satellite Reentry Configurations. NACA RM L58E13a, July 1958.

Penland, J. A. and Fetterman, D. E.: High-Speed Static Stability Char­acteristics of the X-15 Airplane. USAF-USN-NACA Conference on Progress of X-15 Project, July 28-29, 1958, Los Angeles, California.

Lord, D. R., Smith, F. M., and Penland, J. A.: Aerodynamic Characteris--- - - --- -~ - - --tics-of-Va-rious-Missi-l-e-eonii-gur-a t-i-ons- a~ -An<:Jles-ef- At-t-aek- -f -r-em-G o--te- 90-°-- - -~- - - ----- - -

for Mach Numbers from 2 to 7. 40th Meeting of the Bumblebee Aerodynamics Panel, May 1959.

Penland, J. A. and Carroll, C. M.: Static Longitudinal and Lateral Stability Parameters of Three Flared-Skirt TWo-Stage Missile Con­figurations at a Mach Number of 6.86. NACA RM L57015, June 1959.

Penland, J. A. and Armstrong, W. 0.: Static Longitudinal Aerodynamic Characteristics of Several Wing and Blunt-Body Shapes Applicable for Use as Reentry Configurations at a Mach Number of 6.8 and Angles of Attack up to 90°. NASA 'I'M X-65, October 1959.

Fetterman, and Penland, J. A.: Static Longitudinal, Directional, and Lateral Stability and Control Data from an Investigation at a Mach Number of 6.83 of 'IWo Developmental X-15 Airplane Configurations. NASA 'lM X-209, March 1960.

Penland, J. A. and Fetterman, D. E.: Static Longitudina,l, Directional,. and Lateral Stability and Control Data at a Mach Number of 6.83 of the Final Configuration of the X-15 Research Airplane. NASA TM X-236, April 1960.

Penland, J. A.: Static Longitudinal stability of a Missile Configuration with Various Nose Shapes and Flared Afterbodies at a Mach Number of 6.82. NASA 'I'M X-274, June 1960.

Penland, J. A.: Aerodynamic Force Characteristics of a Series of Lifting Cone and Cone-cylinder Configurations at a Mach Number of 6.83 and Angles of Attack up to 130 0

• NASA 'IN 0-840, June 1961.

Penland, J. A. (Provided Results and Discussions): Compiled by Robert W. Rainey: SUll1IIlary of Aerodynamic Characteristics of Low-Lift-Drag-Ratio Reentry Vehicles from Subsonic to Hypersonic Speeds. NASA TN x-S88, September 1961.

Penland, J. A.: A Study of the Aerodynamic Characteristics of a Fixed Geometry Paraglider Configuration and Three Canopies with Simulated Variable Canopy Inflation at a Mach Number of 6.6. NASA 'IN 0-1022, March 1962.

Penland, J. A.: The Hypersonic Aerodynamic Characteristics of the X-2 Research Airplane at M = 6.83. Memo for Files, October 1962.

Penland, J. A.: Theoretical and Experimental Longitudinal and Lateral Static Stability and Control Characteristics of a Series of Axisymmetric High Drag Reentry Vehicles. NASA 'I'M X-770, March 1963.

Penland, J. A.: A Study of the Stability and Location of the Center of Pressure on Sharp, Right Circular Cones at Hypersonic Speeds. NASA TN

-- - --- - - B-2283,-May-1-964-.----------- - - --------- ---- - - ------______________________________ _

Penland, J. A.: Maximum Lift-Drag Ratio Characteristics at Rectangular and Delta Wings at ,Mach 6.9. NASA 'IN 0-2925, August 1965.

Penland, J. A.: Effect of Body Nose Bluntness, Control Planform Area, and Leading Edge Bluntness no Aerodynamic Control of a 5° Semivertex Cone at M = 6.9. NASA 'IN 0-3460, June 1966.

Penland, J. A., Edwards, C. L. W., Witcofski, R. D., and Marcum, D. C.: A Comparative Aerodynamic Evaluation of Two Hypersonic Cruise Aircraft Configurations Derived from Trade-Off Studies. NASA TM X-1436, October 1967 (CONFIDENTIAL)

Penland, J. A. and Bernot, P. T.: Aerodynamic Characteristics of Three Axisymmetric Low-Fineness-Ratio Reentry Shapes at Mach 6.9. NASA 'IN 0-4122, August 1967.

Rainey, R. W. and Penland, J. A.: Newtonian Aerodynamics of Bodies of Revolution and Toe-in-Rolled-out Surfaces. NASA LWP 549, February 1968.

Penland, J. A. and Romeo, D. J.: Advances in Hypersonic Extrapolation Capability-Wind Tunnel to Flight Reynolds Number. AIM paper No. 71-132. AIM 9th Aerospace Sciences Meeting, January 1971.

Penland, J. A. and Romeo, D. J.: Advances in Hypersonic Extrapolation Capability--:Wind Tunnel to Flight Reynolds Number. Journal of Aircraft, Vol. 8, No. 11, November 1971, pp. 881-884.

Penland, J. A., Creel, T. R., Jr., Howard, F. G.: Low Speed Static Longitudinal, Lateral, and Directional Stability and Control Characteristics of a Research Airplane Concept Having a Large Fuselage and a 65° Swept Delta Wing. NASA 'IN 0-7633.

Creel, T. R. , Jr. and Penland, J. A.: Low-Speed Aerodynamic Char­acteristics of a Hypersonic Research Airplane Concept Having a 70° Swept Delta Wing. NASA 'I'M X-71974, August 1974.

Penland, J. A. and Creel, T. R., Jr.: Low-Speed Aerodynamic Char­acteristics of a Lifting-Body Hypersonic Research Aircraft Configuration. NASA 'IN 0-7851.

Penland, J. A., Fournier, R. H., and Marcum, D. C., Jr.: Aerodynamic Characteristics of a 70° Swept Delta Wing Hypersonic Research Airplane at Mach 1.50 to 2.86. NASA 'IN 0-8065, December 1975.

Weidner, J. P., Small, W. J., and Penland, J. on Hypersonic Research Airplane Concepts. Conference, Palo Alto, California, July 1976 .

A.: Scramjet Integration AIAA/SAE 12th Propulsion

.. - - - - -Weidner,-J-.- -P-.'- Small-,- W·. - J.-,- and-Penland,- J. -A.-:-_Scramjet_ Integration_ on Hypersonic Research Airplane Concepts. Journal of Aircraft, Vol. 14, No.5, May 1977.

Penland, J. A., Dillon, J. L., and pittman, J. L.: An Aerodynamic Analysis of Several Hypersonic Research Concepts from M = 0.2 to 6.0. AIM 16th Aerospace Sciences Meeting, Huntsville, Alabama, January 1978.

Penland, J. A., Creel, T. R., Jr., and Dillon, J. L.: Aerodynamic Characteristics of a Model of a Hypersonic Research Airplane Concept Having a 70° SWept Double-Delta Wing at Mach No. 0.2. NASA TP-1252, May 1978.

Penland, J. A., Dillon, J. L., and Pittman, J. L.: An Aerodynamic Analysis of Several Hypersonic Research Airplane Concepts from M = 0.2 to 6.0. Journal of Aircraft, November 1978.

Penland, J. A., Hallissy, J. B., and Dillon, J. L.: Aerodynamic

/

/ Characteristics of a Hypersonic Research Airplane Concept Having a 70 0

Double-Delta Wing at Mach Number from 0.8 to 1.2 with Sunnnary of Data from 0.2 to 6.0. NASA TP-1552, December 1979.

Penland, J. A., Marcum, D. C. Jr., and Stack, S. H.: Wall-Temperature Effects on the Aerodynamics of a Hydrogen-Fueled Transport Concept in Mach 8 Blowdown and Shock Tunnels. NASA TP-2159, July 1983.

Penland, J. A. and Pittman, J. L.: Aerodynamic Characteristics of a Distinct Wing-Body Configuration at Mach 6 Experiment, Theory, and the Hypersonic Isolation Principle. NASA TP 2467, August 1985.