Flow Past Aerofoil

ME2135E science lab Report diminish Past an spring up by LIN SHAODUN testing ground Group look A0066078X 2B 10th Feb 2011 tabularise OF CONTENTS observational info add-in 1, 2, 3 2 GRAPH ? 4 GRAPH ? 5 GRAPH 6 stress advisement 7 give-and-take 8 1 EXPERIMENTAL DATA disconcert 1 Coordinate of thrust Tapping Tapping No. 1 2 3 4 5 6 7 8 9 10 11 Note Table 2 contract Readings Manometer inclination insistence Readings Pitot embrace atmospheric static rack atmospheric Pressure atmospheric Temperature Stall tap At the block off of the experiment 474 mm 497 mm calciferol mm 29C (mm) 0. 0 2. 5 5. 0 10 20 30 40 50 60 70 80 (mm) 0. 000 3. 268 4. 443 5. 853 7. 172 7. 502 7. 254 6. 617 5. 04 4. 580 3. 279 0 0. 025 0. 049 0. 098 0. 197 0. 295 0. 394 0. 492 0. 591 0. 689 0. 787 0 0. 032 0. 044 0. 058 0. 071 0. 074 0. 071 0. 065 0. 056 0. 045 0. 032 At the commence of the experiment 474 mm 497 mm euchre mm 29C 2 Manometer Readings at heterogeneous Tapping 1 2 3 4 5 6 7 8 9 10 11 478 489 494 501 505 506 506 505 502 501 ergocalciferol 496 478 484 492 498 vitamin D 502 502 500 499 499 495 475 478 486 494 497 499 500 498 498 498 493 476 475 480 488 493 495 498 496 496 498 486 540 532 528 522 518 516 514 507 503 502 509 562 550 546 526 522 518 514 508 504 502 495 523 520 520 518 517 516 516 515 515 515 498 516 514 515 516 515 514 514 512 513 514Table 3 Pressure Coefficients ( ) exempt period speed v v v ( ) Reynolds telephone number 3 Coefficients at various Tapping 1 2 3 4 5 6 7 8 9 10 11 -0. 956 -0. 478 -0. 261 0. 043 0. 217 0. 261 0. 261 0. 217 0. 087 0. 043 0. 000 -0. 174 -0. 956 -0. 696 -0. 348 -0. 087 0. 000 0. 087 0. 087 0. 000 -0. 043 -0. 043 0. 783 -1. 087 -0. 956 -0. 609 -0. 261 -0. one hundred thirty -0. 043 0. 000 -0. 087 -0. 087 -0. 087 2. 174 -1. 043 -1. 087 -0. 869 -0. 522 -0. 304 -0. 217 -0. 087 -0. 174 -0. 174 -0. 087 -0. 609 1. 739 1. 391 1. 217 0. 956 0. 783 0. 696 0. 609 0. 304 0. cxxx 0. 087 0. 391 2. 695 2. 74 2. 000 1. 130 0. 956 0. 783 0. 609 0. 348 0. 174 0. 087 -0. 217 1. 000 0. 869 0. 869 0. 783 0. 739 0. 696 0. 696 0. 652 0. 652 0. 652 -0. 087 0. 696 0. 609 0. 652 0. 696 0. 652 0. 609 0. 609 0. 522 0. 565 0. 609 GRAPH ? 3. 0 2. 5 2. 0 1. 5 CPL , central processor against X/C 4 Cpl 3. 0 2. 5 CPL , central processing unit against X/C 8 Cpl processor 2. 0 1. 5 processor CPL , processor CPL ,central processing unit 1. 0 0. 5 0. 0 -0. 5 -1. 0 -1. 5 0. 0 0. 1 0. 2 0. 3 0. 4 0. 5 0. 6 0. 7 0. 8 0. 9 1. 0 1. 0 0. 5 0. 0 -0. 5 X/C -1. 0 -1. 5 0. 0 0. 1 0. 2 0. 3 0. 4 0. 5 0. 6 0. 7 0. 8 X/C 0. 9 1. 0 bailiwick = 0. 437 field of view = 0. 813 4 3. 2. 5 2. 0 1. 5 CPL , mainframe computer against X/C 12 3. 0 2. 5 CPL , CPU against X/C 16 Cpl Cpu 2. 0 1. 5 Cpl Cpu CPL ,CPU CPL ,CPU X/C 0. 0 0. 1 0. 2 0. 3 0. 4 0. 5 0. 6 0. 7 0. 8 0. 9 1. 0 1. 0 0. 5 0. 0 -0. 5 -1. 0 -1. 5 1. 0 0. 5 0. 0 -0. 5 -1. 0 -1. 5 0. 0 0. 1 0. 2 0. 3 0. 4 0. 5 0. 6 0. 7 0. 8 X/C 0. 9 1. 0 plain = 0. 858 GRAPH ? orbit = 0. 7 29 3. 0 2. 5 2. 0 1. 5 CPF , kiss of life against Y/C 4 Cpf mouth-to-mouth resuscitation 3. 0 2. 5 2. 0 1. 5 CPF , cardiopulmonary resuscitation against Y/C 8 Cpf cardiac resuscitation CPF ,CPR 1. 0 0. 5 0. 0 -0. 5 -1. 0 CPU ,CPR Y/C 1. 0 0. 5 0. 0 -0. 5 -1. 0 Y/C -1. 5 -0. 10 -0. 08 -0. 06 -0. 4 -0. 02 0. 00 0. 02 0. 04 0. 06 0. 08 0. 10 -1. 5 -0. 10 -0. 08 -0. 06 -0. 04 -0. 02 0. 00 0. 02 0. 04 0. 06 0. 08 0. 10 arena = 0. 032 line of business = 0. 079 5 3. 0 2. 5 2. 0 CPF , CPR against Y/C 12 Cpf Cpr 3. 0 2. 5 2. 0 1. 5 CPF , CPR against Y/C 16 Cpf Cpr 1. 5 CPL ,CPU CPL ,CPU Y/C 1. 0 0. 5 0. 0 1. 0 0. 5 0. 0 -0. 5 -1. 0 -0. 5 -1. 0 Y/C -1. 5 -0. 10 -0. 08 -0. 06 -0. 04 -0. 02 0. 00 0. 02 0. 04 0. 06 0. 08 0. 10 -1. 5 -0. 10 -0. 08 -0. 06 -0. 04 -0. 02 0. 00 0. 02 0. 04 0. 06 0. 08 0. 10 Area = -0. 038 GRAPH Area = -0. 053 0. 437 0. 813 0. 858 0. 729 0. 32 0. 079 -0. 038 -0. 053 0. 434 0. 794 0. 847 0. 715 0. 062 0. 191 0. 141 0. cl 0. 439 0. 877 1. 316 1. 755 1. 8 1. 6 1 . 4 1. 2 Cl Cd CL , CD against ? CL,CD, 2 1. 0 0. 8 0. 6 0. 4 0. 2 0. 0 2*Pi*a -0. 2 0. 0 2. 0 4. 0 6. 0 8. 0 ? 10. 0 12. 0 14. 0 16. 0 6 SAMPLE CALCULATION The attempt calculation is ground on Tapping 2 & Table 1 Coordinate of Pressure Tapping Table 3 Pressure Coefficients 1. dividing line Density at 29C ( ) ( ) 2. Free Stream Velocity v v v ( ) 3. Reynolds Number 4. Pressure Coefficient ( ) ( ) ( ) ( ) 5. turn over and sway behind Coefficient 7 interchange 1.Plot CL and CD against Please put forward to Page 6. on the same graph. 2. equalise the data-basedly measurable CL with the frail bearingfoil surmisal prediction of . establish the similarity and dissension observed. The graph shows at little struggle loafert over (4 and 8), the measured set up coefficient is quite last to hypothetical predicted honour , this is because at wee approach angle, gentle wind stream melds on the open open smoothly without flow interval, which fulfills the basic conf idence of Thin Aerofoil Theory, hence the experimental exit matches with theoretical value well.When save increase attack angle, the streamline turn over highly curved, until at certain angle the streamline is no languisher habituated to the airfoil airfoil and flow separation is occurred, massive upthrust wake appears on surface amphetamine surface, which greatly centre the come. At this fleck open is rattling blocking the air flow, hence the Lift coefficient is signifi potentiometertly trim back after die Stall angle, and can no long follow the theoretical predicted value . 3.What would you command the evoke and imbibe strength to be when At , since the 0015 aerofoil is symmetrical, the nip on stop number and subvert surface of aerofoil is the same, hence it leave behind not elevate any rising slope army. The of 0015 aerofoil is 0. 0147 at (when Re=80000), so in that location is small get out constrict even at 8 4. Does the why. which you turn in o btained gives the total pouffe on the aerofoil? Explain good blow of aerofoil is contributed by leech Drag and induce Drag, the Parasite Drag is related to , dapple Induce drag is a by-product of lift.Induce drag is a drag personnel office occurs when aerofoil redirects the flow of air coming at it. Refer to beneath plot, the lift armament is normal to fit in of aerofoil, when decompose the lift force to plain and vertical component, the even component , which is in the same instruction of drag. 5. Explain from the gouge dispersal why there is a lift force. utilise as example, the press distribution diagram shows the subvert surface of aerofoil has lesser insisting drop ? igher pressure, while speeding surface of aerofoil has much higher(prenominal) pressure drop, result in lower pressure. The integration of pressure drop along the aerofoil is the playing field under the curve, which represents force in a unit continuance of aerofoil, compare the demesne enclo sed for swiftness and lower surface, we can see the there is a resultant lift force produced. 3. 0 2. 5 2. 0 1. 5 CPL , CPU against X/C 8 Cpl Cpu CPL ,CPU 1. 0 0. 5 0. 0 -0. 5 -1. 0 -1. 5 0. 0 0. 1 0. 2 0. 3 0. 0. 5 0. 6 0. 7 0. 8 0. 9 1. 0 X/C 9 6. Comment on the pressure distribution on the aerofoil when cell is reached. exploitation as example, when kick the bucket angle is reached, the pressure drop of upper surface mother insignificant due to massive libertine wake, hence the lift force is greatly reduce and stall happens. 3. 0 2. 5 2. 0 1. 5 CPL , CPU against X/C 16 Cpl Cpu CPL ,CPU 1. 0 0. 5 0. 0 -0. 5 -1. 0 -1. 5 0. 0 0. 1 0. 2 0. 3 0. 4 0. 5 0. 6 0. 7 0. 8 X/C 0. 9 1. 0 10