Flow Past Aerofoil

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ME2135E Lab Report Flow Past an Aerofoil
by

LIN SHAODUN
Lab Group Date

A0066078X
2B 10th 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 Tapping No. 1 2 3 4 5 6 7 8 9 10 11 Note: Table 2: Pressure Readings Manometer inclination: Pressure Readings Pitot Pressure Static Pressure Atmospheric Pressure Atmospheric Temperature Stall angle: At the end of the experiment 474 mm 497 mm 500 mm 29°C

(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 5.704 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 beginning of the experiment
474 mm 497 mm 500 mm 29°C

2

Manometer Readings at various

Tapping 1 2 3 4 5 6 7 8 9 10 11
478 489 494 501 505 506 506 505 502 501 500 496 478 484 492 498 500 502 502 500 499 499 495 475 478 486 494 497 499 500 498 498 498 493 476 475 480 488 493 495 498 496 496 498 486 540 532 528 522 518 516 514 507 503 502 509 562 550 546 526 522 518 514 508 504 502 495 523 520 520 518 517 516 516 515 515 515 498 516 514 515 516 515 514 514 512 513 514

Table 3: Pressure Coefficients

(

)

Free Stream Velocity
√ √ √ ( )

Reynolds 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 -0.130 -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 2.174 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 @ 4°
Cpl

3.0 2.5

CPL , CPU against X/C @ 8°
Cpl Cpu

2.0
1.5

Cpu

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 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

Area = 0.437

Area = 0.813

4

3.0 2.5 2.0 1.5

CPL , CPU 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

Area = 0.858 GRAPH ⁄

Area = 0.729

3.0 2.5 2.0 1.5

CPF , CPR against Y/C @ 4°
Cpf Cpr

3.0 2.5 2.0 1.5

CPF , CPR against Y/C @ 8°
Cpf Cpr

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 -0.04 -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 = 0.032

Area = 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

0.032 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 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 sample calculation is based on Tapping 2 & Table 1: Coordinate of Pressure Tapping

Table 3: Pressure Coefficients 1. Air Density...
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