Flow Past Aerofoil Free Essays

ME2135E Lab Report Flow Past an Aerofoil by LIN SHAODUN Lab Group Date A0066078X 2B tenth Feb 2011 TABLE OF CONTENTS EXPERIMENTAL DATA †TABLE 1, 2, 3 2 GRAPH †? 4 GRAPH †? 5 GRAPH †6 SAMPLE CALCULATION 7 DISCUSSION 8 1 EXPERIMENTAL DATA Table 1: Coordinate of Pressure Tapping No. 1 2 3 4 5 6 7 8 9 10 11 Note: Table 2: Pressure Readings Manometer tendency: Pressure Readings Pitot Pressure Static Pressure Atmospheric Pressure Atmospheric Temperature Stall edge: At the finish of the trial 474 mm 497 mm 500 mm 29 °C (mm) 0. 0 2. We will compose a custom exposition test on Stream Past Aerofoil or then again any comparative point just for you Request Now 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. 025 0. 049 0. 098 0. 197 0. 295 0. 394 0. 492 0. 591 0. 689 0. 787 0. 032 0. 044 0. 058 0. 071 0. 074 0. 071 0. 065 0. 056 0. 045 0. 032 At the start of the examination 474 mm 497 mm 500 mm 29 °C 2 Manometer Readings at different Tapping 1 2 3 4 5 6 7 8 9 10 11 478 489 494 501 505 506 505 502 501 500 496 478 484 492 498 500 502 500 499 495 475 478 486 494 497 499 500 498 493 476 475 480 488 493 495 498 496 498 486 540 532 528 522 518 516 514 507 503 502 509 562 550 546 526 522 518 514 508 504 502 495 523 520 518 517 516 515 498 516 514 515 516 515 514 512 513 514 Table 3: Pressure Coefficients ( ) Free Stream Velocity v ( ) Reynolds Number 3 Coefficients at different 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. 130 - 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. 130 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 , CPU against X/C @ 4â ° Cpl 3. 0 2. 5 CPL , CPU against X/C @ 8â ° Cpl Cpu 2. 0 1. 5 Cpu CPL ,CPU CPL ,CPU 1. 0. 5 0. 0 - 0. 5 - 1. 0 - 1. 5 0. 0. 1 0. 2 0. 3 0. 4 0. 5 0. 6 0. 7 0. 8 0. 9 1. 0 1. 0. 5 0. 0 - 0. 5 X/C - 1. 0 - 1. 5 0. 0. 1 0. 2 0. 3 0. 4 0. 5 0. 6 0. 7 0. 8 X/C 0. 9 1. 0 Area = 0. 437 Area = 0. 813 4 3. 2. 5 2. 0 1. 5 CPL , CPU against X/C @ 12â ° 3. 0 2. 5 CPL , CPU against X/C @ 16â ° Cpl Cpu 2. 0 1. 5 Cpl Cpu CPL ,CPU CPL ,CPU X/C 0. 0. 1 0. 2 0. 3 0. 4 0. 5 0. 6 0. 7 0. 8 0. 9 1. 0 1. 0. 5 0. 0 - 0. 5 - 1. 0 - 1. 5 1. 0. 5 0. 0 - 0. 5 - 1. 0 - 1. 5 0. 0. 1 0. 2 0. 3 0. 4 0. 5 0. 6 0. 7 0. 8 X/C 0. 9 1. 0 Area = 0. 858 GRAPH ? Region = 0. 729 3. 0 2. 5 2. 0 1. 5 CPF , CPR against Y/C @ 4â ° Cpf Cpr 3. 0 2. 5 2. 0 1. 5 CPF , CPR against Y/C @ 8â ° Cpf Cpr CPF ,CPR 1. 0. 5 0. 0 - 0. 5 - 1. 0 CPU ,CPR Y/C 1. 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 Area = 0. 032 Area = 0. 079 5 3. 0 2. 5 2. 0 CPF , CPR against Y/C @ 12â ° Cpf Cpr 3. 0 2. 5 2. 0 1. 5 CPF , CPR against Y/C @ 16â ° Cpf Cpr 1. 5 CPL ,CPU CPL ,CPU Y/C 1. 0. 5 0. 0 1. 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. 150 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. 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 example figuring depends on Tapping 2 Table 1: Coordinate of Pressure Tapping Table 3: Pressure Coefficients 1. Air Density at 29 °C ( ) ( ) 2. Free Stream Velocity v ( ) 3. Reynolds Number 4. Weight Coefficient ( ) ( ) ( ) ( ) 5. Lift and Drag Coefficient 7 DISCUSSION 1. Plot CL and CD against Please allude to Page 6. on a similar diagram. 2. Contrast the tentatively estimated CL and the Thin Aerofoil Theory forecast of . Talk about the closeness and disparity watched. The chart appears at little assault point (4â ° and 8â °), the deliberate Lift coefficient is very near hypothetical anticipated worth , this is on the grounds that at little assault edge, air stream streams along the aerofoil surface easily without stream detachment, which satisfies the fundamental supposition of Thin Aerofoil Theory, consequently the trial result matches with hypothetical worth well. At the point when further increment assault edge, the smooth out become exceptionally bended, until at certain edge the smooth out is not, at this point joined to the aerofoil surface and stream partition is happened, enormous choppiness wake shows up on aerofoil upper surface, which incredibly diminish the lift. Right now aerofoil is really â€Å"blocking† the wind current, consequently the Lift coefficient is altogether diminished after arrive at Stall point, and can no long follow the hypothetical anticipated worth . 3. What might you expect the lift and drag power to be when At , since the 0015 aerofoil is balanced, the weight on upper and lower surface of aerofoil is the equivalent, consequently it won't produce any lift power. The of 0015 aerofoil is 0. 0147 at (when Re=80000), so there is little drag power even at 8 4. Does the why. which you have gotten gives the all out delay the aerofoil? Clarify Total Drag of aerofoil is contributed by Parasite Drag and Induced Drag, the Parasite Drag is identified with , while Induce drag is a result of lift. Incite drag is a drag power happens when aerofoil diverts the wind stream coming at it. Allude to beneath outline, the lift power is typical to harmony of aerofoil, when break down the lift power to even and vertical part, the level segment , which is a similar way of drag. 5. Clarify from the weight circulation why there is a lift power. Utilizing as model, the weight appropriation outline shows the lower surface of aerofoil has lesser weight drop ? igher pressure, while upper surface of aerofoil has a lot higher weight drop, bring about lower pressure. The coordination of weight drop along the aerofoil is the zone under the bend, which speaks to drive in a unit length of aerofoil, analyze the territory encased for upper and lower surface, we can see the there is a resultant lift power created. 3. 0 2. 5 2. 0 1. 5 CPL , CPU against X/C @ 8â ° Cpl Cpu CPL ,CPU 1. 0. 5 0. 0 - 0. 5 - 1. 0 - 1. 5 0. 0. 1 0. 2 0. 3 0. 0. 5 0. 6 0. 7 0. 8 0. 9 1. 0 X/C 9 6. Remark on the weight conveyanc e on the aerofoil when slow down is reached. Utilizing as model, when slow down point is reached, the weight drop of upper surface become irrelevant because of enormous violent wake, thus the lift power is extraordinarily lessen and slow down occurs. 3. 0 2. 5 2. 0 1. 5 CPL , CPU against X/C @ 16â ° Cpl Cpu CPL ,CPU 1. 0. 5 0. 0 - 0. 5 - 1. 0 - 1. 5 0. 0. 1 0. 2 0. 3 0. 4 0. 5 0. 6 0. 7 0. 8 X/C 0. 9 1. 0 10 The most effective method to refer to Flow Past Aerofoil, Papers