1. C OMBUSTION P ROF. S EUNG W OOK B AEK D EPARTMENT OF A EROSPACE E NGINEERING, KAIST, IN KOREA R OOM : Building N7-2 #3304 T ELEPHONE : 3714 Cellphone: 010 – 5302 - 5934 swbaek@kaist.ac.kr http://procom.kaist.ac.kr T A : Bonchan Gu R OOM : Building N7-2 #3315 T ELEPHONE : 3754 Cellphone: 010 – 3823 - 7775 ryan.bonchan@kaist.ac.kr P ROF. S EUNG W OOK B AEK D EPARTMENT OF A EROSPACE E NGINEERING, KAIST, IN KOREA R OOM : Building N7-2 #3304 T ELEPHONE : 3714 Cellphone: 010 – 5302 - 5934 swbaek@kaist.ac.kr http://procom.kaist.ac.kr T A : Bonchan Gu R OOM : Building N7-2 #3315 T ELEPHONE : 3754 Cellphone: 010 – 3823 - 7775 ryan.bonchan@kaist.ac.kr

2. P ROPULSION AND C OMBUSTION L ABORATORY C OMBUSTION E NGINEERING A SSUMPTION N EGLECT(A) BODY FORCE (B) THERMAL DIFFUSION (SORET EFFECT) (C) PRESSURE GRADIENT DIFFUSION (D) BULK VISCOSITY (E) RADIATION T HE Shvah-Zeldovitch F ORMULATION OF E QUATIONS OF M ULTI- C OMPONENT R EACTING G ASES S TEADY F LOW O VERALL C ONTINUITY I N M OST OF L OW S PEED C OMBUSTION P ROBLEMS V ISCOUS T ERMS ARE N EGLECTED, I F

3. P ROPULSION AND C OMBUSTION L ABORATORY C OMBUSTION E NGINEERING M OMENTUM E QUATION: J USTIFICATION O NE D IMENSIONAL S PECIES E QUATION C HEMICAL T IME

4. P ROPULSION AND C OMBUSTION L ABORATORY C OMBUSTION E NGINEERING : CHARACTERISTIC CHEMICAL LENGTH ~ ORDER OF DISTANCE IN WHICH REACTION IS COMPLETED ~ REACTION ZONE THICKNESS (MANY MOLECULAR COLLISIONS ARE NEEDED) I F v 0 IS A C HARACTERISTIC V ELOCITY, I NTEGRATE 1D M OMENTUM E QUATION O NCE

5. P ROPULSION AND C OMBUSTION L ABORATORY C OMBUSTION E NGINEERING IN R EGION WHERE V ISCOUS E FFECTS ARE I MPORTANT : VISCOUS TIME VISCOUS LENGTH :LENGTH IN WHICH TRANSLATIONAL AND RATATIONAL MODES ARE EQUILIBRIATED: ONE OR TWO COLLISIONS ~ MEAN FREE PATH

6. P ROPULSION AND C OMBUSTION L ABORATORY C OMBUSTION E NGINEERING : IN ATMOSPHERE D IMENSIONLESS V ARIABLES

7. P ROPULSION AND C OMBUSTION L ABORATORY C OMBUSTION E NGINEERING W HY B ECAUSE C ONTINUITY M OMENTUM

8. P ROPULSION AND C OMBUSTION L ABORATORY C OMBUSTION E NGINEERING : MASS If

9. P ROPULSION AND C OMBUSTION L ABORATORY C OMBUSTION E NGINEERING S TEADY S TATE E NERGY E QUATION N EGLECT KINETIC ENERGY VISCOUS WORK BODY FORCE RADIATION = HEAT FLUX = = SPECIFIC INTERNAL ENERGY (1) (2)

10. P ROPULSION AND C OMBUSTION L ABORATORY C OMBUSTION E NGINEERING S UBSTITUTE INTO

11. E NERGY E QUATION BECOMES P ROPULSION AND C OMBUSTION L ABORATORY C OMBUSTION E NGINEERING (3) (4) S PECIES C ONSERVATION, (5)

12. P ROPULSION AND C OMBUSTION L ABORATORY C OMBUSTION E NGINEERING P UT (5) IN (4), (6)

13. S ECOND T ERM IN (6), U SE P ROPULSION AND C OMBUSTION L ABORATORY C OMBUSTION E NGINEERING (7) U SE (8) (6) (9)

14. C OMBINE (8) & (9) T HEN (6) B ECOMES, P ROPULSION AND C OMBUSTION L ABORATORY C OMBUSTION E NGINEERING (10)

15. P ROPULSION AND C OMBUSTION L ABORATORY C OMBUSTION E NGINEERING A SSUME T HEN R ETURN TO S PECIES, C OMBINE E QUATIONS (5) & (7) (11) (12) R EMARKS : 1)Shvah-Zeldovitch FORM OF EQUATIONS. 2)Cp ’s & Cp i ’s ARE NOT NECESSARILY CONSTANT.

16. S INGLE R EACTION S TEP L AW OF M ASS A CTION THE RATE OF PRODUCTION OF A CHEMICAL SPECIES IS PROPORTIONAL TO THE PRODUCTS OF THE CONCENTRATION OF EACH REACTANT WITH EACH CONCENTRATION RAISED TO A POWER EQUAL TO ITS STOICHIOMETRIC COEFFICIENT. = CONCENTRATION OF SPECIES i = MOLES PER UNIT VOLUME PER SECOND FORMED OF SPECIES i P ROPULSION AND C OMBUSTION L ABORATORY C OMBUSTION E NGINEERING

17. A LSO W E C AN W RITE, k = SPECIFIC REACTION RATE CONSTANT P ROPULSION AND C OMBUSTION L ABORATORY C OMBUSTION E NGINEERING

18. = MOLECULAR WEIGHT OF SPECIES i P ROPULSION AND C OMBUSTION L ABORATORY C OMBUSTION E NGINEERING = RATE OF PRODUCTION FOR A NY S PECIES (MOLES/UNIT VOLUME/S)

19. P ROPULSION AND C OMBUSTION L ABORATORY C OMBUSTION E NGINEERING F OR S PECIES AND E NERGY E QUATIONS WITH S INGLE R EACTION, E ACH CAN BE R EDUCED TO THE F ORM F OR E NERGY E QUATION F OR S PECIES E QUATION

20. P ROPULSION AND C OMBUSTION L ABORATORY C OMBUSTION E NGINEERING L : A LINEAR OPERATOR : NON LINEAR: INVOLVES PRODUCTS OF ‘S O FTEN: A RRHENIUS T YPE S INCE R EMARKS ) MAY BE I MPLICITLY N ON- L INEAR B ECAUSE OF D EPENDENCE OF ON

21. P ROPULSION AND C OMBUSTION L ABORATORY C OMBUSTION E NGINEERING D IFFUSION F LAME A NY F LAME IN WHICH F UEL AND O XIDIZER ARE O RIGINALLY U NMIXED E XAMPLES) C ANDLE F LAME

22. P ROPULSION AND C OMBUSTION L ABORATORY C OMBUSTION E NGINEERING D ROPLET B URNING I NDIVIDUAL D ROPLET B URNING OXIDIZER

23. P ROPULSION AND C OMBUSTION L ABORATORY C OMBUSTION E NGINEERING B OUNDARY L AYER A DJACENT TO F UEL S URFACE OXIDIZER FUEL OXIDIZER

24. P ROPULSION AND C OMBUSTION L ABORATORY C OMBUSTION E NGINEERING J ET F LAME

25. P ROPULSION AND C OMBUSTION L ABORATORY C OMBUSTION E NGINEERING L AMINAR D IFFUSION F LAMES ARE C HARACTERIZED BY (1)REACTION RATES FAST COMPARED TO RATES OF MASS AND ENERGY TRANSFERS BY DIFFUSION AND CONVECTION (2)REACTION TENDS TO BE CONCENTRATED IN THIN FRONTS WHERE FUEL AND OXIDIZER ARE IN STOICHIOMETRIC PROPORTION. (3)RATE OF CONVERSION OF MIXTURE IS SLOWER THAN THAT IN PREMIXED FLAME

26. P ROPULSION AND C OMBUSTION L ABORATORY C OMBUSTION E NGINEERING (4) WHEN JET VELOCITY EXCEEDS A CERTAIN VALUE THE FLAME BECOMES TURBULENT F LAME H EIGHT J ET V ELOCITY Hottel and Hawtherns 3 RD SYMPOSIUM ON COMBUSTION (1949) LARMINARTRANSITIONTURBULENT

27. P ROPULSION AND C OMBUSTION L ABORATORY C OMBUSTION E NGINEERING L r d V0V0 O XIDIZER R ELATION BETWEEN F LAME HEIGHT L T UBE D IAMETER d F UEL V ELOCITY V 0 (OR F LOW R ATE ) M ASS F LOW ~ RATE AT WHICH FUEL AND OXIDIZER MIX BY DIFFUSION Q UALITATIVE A NALYSIS

28. P ROPULSION AND C OMBUSTION L ABORATORY C OMBUSTION E NGINEERING F OR G IVEN F UEL D I NDEPENDENT OF F OR T URBULENT F LOW R EPLACE D BY A T URBULENT D IFFUSION COEFFICIENT,

29. P ROPULSION AND C OMBUSTION L ABORATORY C OMBUSTION E NGINEERING D t ( T URBULENT S CALE)( T URBULENT I NTENSITY) SIZE OF LARGEST EDDY I NDEPENDENT OF J ET V ELOCITY L