PHP JPEG Metadata Toolkit
List of Tested Digital Cameras
Tested with reading and interpreting functions only Makernote Decoded Makernote Present JPEG Comment EXIF Thumbnail Unless otherwise noted, except for unknown EXIF Makernotes, all images tested were fully decoded, with no errors

Contains JFXX

Meta Segment

Contains EXIF

Contains JFIF

Picture Info

Tested
Camera Agfa ePhoto 780 Agfa ePhoto CL18 Agfa ePhoto CL20 Agfa ePhoto CL30 Clik! Agfa ePhoto CL30 Agfa ePhoto CL45 Agfa ePhoto CL50 Agfa ePhoto 1680 Agfa ePhoto 1280 Canon PowerShot S60 Canon PowerShot S410 (Digital IXUS 430) Canon PowerShot S500 (Digital IXUS 500) Canon PowerShot A75 Canon PowerShot SD110 (Digital IXUS IIs) Canon PowerShot A310 Canon PowerShot S1 IS Canon PowerShot Pro1 Canon EOS-1D Mark II with EF 100-400 mm L Canon PowerShot SD10 (Digital IXUS i) Canon PowerShot A80 Canon EOS-300D (EOS Digital Rebel) Canon PowerShot G5 Canon EOS-10D Canon PowerShot A70 Canon PowerShot A60 Canon PowerShot S50

Makernote Coding

Comment
x x x x x x x x x x x x x x x x x x x x x

x x x x Agfa

x x x x x x x x x x x x x x x x x x x x x x x x x x x x x x x x x x x x x x x x x x x x x x x x x x x x x x x x x x x x x x x x x x Canon Canon Canon Canon Canon Canon Canon Canon Canon Canon Canon Canon Canon Canon Canon Canon

Makernote Decoded

Makernote Present

JPEG Comment

EXIF Thumbnail
Camera Canon PowerShot A300 Canon EOS-1Ds with EF 28-70 mm L Canon PowerShot G3 Canon PowerShot S45 Canon PowerShot S230 (Digital IXUS v3) Canon PowerShot A200 Canon PowerShot S330 (Digital IXUS 330) Canon PowerShot A100 Canon PowerShot A40 Canon PowerShot A30 Canon PowerShot S30 Canon PowerShot S40 Canon PowerShot A10 Canon PowerShot A20 Canon PowerShot S100 (Digital IXUS) Canon PowerShot SD100 Digital ELPH Canon PowerShot S400 Canon PowerShot S200 Canon EOS-D60 Canon EOS-1D with EF 28-135 mm F3.5-5.6 Canon PowerShot G2 Canon PowerShot S110 Canon PowerShot S300 Canon PowerShot Pro90 IS Canon PowerShot G1 Canon EOS-D30 Canon PowerShot S20 Canon PowerShot S10 Canon PowerShot A50 Canon PowerShot A5 Zoom Canon PowerShot A5
x x x x x x x x x x x x x x x x x x x x x x x x x x x x x x x
x x x x x x x x x x x x x x x x x x x x x x x x x x x x x
Makernote Coding Canon Canon Canon Canon Canon Canon Canon Canon Canon Canon Canon Canon Canon Canon Canon Canon Canon Canon Canon Canon Canon Canon Canon Canon Canon Canon Canon Canon Canon
Can't decode old Canon proprietory APP0 segment Can't decode old Canon proprietory APP0 segment
Camera Canon PowerShot Pro70 Canon PowerShot 600 Canon PowerShot 350 Canon EOS D6000 Canon EOS D2000 aka Kodak DCS520 Canon PowerShot 600N Canon PowerShot 30 Canon PowerShot 30T Canon EOS DCS1 Canon EOS DCS3 Casio EXILIM EX-M20 Casio EXILIM EX-P600 Casio EXILIM EX-S1 Casio EXILIM EX-S2 Casio EXILIM EX-S3 Casio EXILIM EX-S20 Casio EXILIM EX-Z3 Casio EXILIM EX-Z4 Casio EXILIM EX-Z30 Casio EXILIM EX-Z40 Casio GV-10 Casio GV-20 Casio QV-3EX Casio QV-3 Plus Casio QV-10 Casio QV-10a Casio QV-11 Casio QV-30 Casio QV-70 Casio QV-100 Casio QV-120 Casio QV-200

Makernote Coding Fujifilm Fujifilm Fujifilm Fujifilm Fujifilm Fujifilm Fujifilm Fujifilm Fujifilm Fujifilm Fujifilm
x x x x x x x x x x x x x x

x x x x x

Fujifilm Fujifilm Fujifilm Fujifilm Fujifilm
x Fujifilm x x x x x Fujifilm Fujifilm Fujifilm Fujifilm Fujifilm
x Fujifilm x Fujifilm x Fujifilm
Camera Fujifilm MX-1200 Fujifilm MX-1400 Fujifilm MX-1500 Fujifilm MX-1700 Zoom Fujifilm MX-2700 Fujifilm MX-2900 Zoom HP Photosmart 120 HP Photosmart 210 HP Photosmart 215 HP Photosmart 315 HP Photosmart 318 HP Photosmart 320 HP Photosmart 435 HP Photosmart 612 HP Photosmart 620 HP Photosmart 635 HP Photosmart 715 HP Photosmart 720 HP Photosmart 735 HP Photosmart C20 HP Photosmart C30 HP Photosmart C200 HP Photosmart C500
x x x x x x x x x x x x x x x x x x x x x x x x x x x x x x x x

x x x x x x x x x x

Makernote starts with "HPKK"
FAULTY EXIF - No Next-IFD Pointer on EXIF IFD x x x x x x x x x x x x x Zero Length EXIF IFD, Makernote starts with "HP*" Uncompressed Exif thumbnail not decoded, and 3x FPXR APP2 Flashpix segments not decoded, Makernote starts with "00" Uncompressed Exif thumbnail not decoded, and 3x FPXR APP2 Flashpix segments not decoded, Makernote starts with "00" 2x weird APP3 segments full of HHHH 2x weird APP3 segments full of HHHH Olympus format makernote, but one tag (Digital Zoom) is not to EXIF standard (Rational should be 2 longs but is 2 shorts)

HP Photosmart C618

Camera HP Photosmart C812 HP Photosmart C850

HP Photosmart C912

HP Photosmart C935 HP Photosmart C945 HP Photosmart R707 HP Photosmart R607 JVC GC-QX3HD JVC GC-QX5HD Kodak CX4200 Kodak CX4210 Kodak Easyshare CX4230 Zoom Kodak CX4300 Kodak CX4310 Kodak Easyshare CX6200 Kodak CX6230 Kodak CX6330 Zoom Kodak CX7220 Kodak Easyshare CX7300 Kodak CX7330 Kodak CX7430 Zoom Kodak CX7530 Kodak DC20 Kodak DC25 Kodak DC50 Kodak DC120

x x x x x x

Comment Unknown 2x HPSC APP4 segment not decoded Unknown 2x HPSC APP4 segment not decoded, Makernote is only 1 byte Uncompressed Exif thumbnail not decoded, and 3x FPXR APP2 Flashpix segments not decoded, Makernote starts with "00" Unknown 2x HPSC APP4 segment not decoded, Makernote is only 1 byte Unknown 2x HPSC APP4 segment not decoded, Makernote is only 1 byte Makernote tag corrupted, indicates length 5, also 3x H3X0 unknown segments

x x x x

Camera Kodak DC200 Kodak DC200 plus Kodak DC210 plus Kodak DC210 Zoom Kodak DC215 Zoom Kodak DC220 Kodak DC240 Kodak DC240 Zoom Kodak DC260 Kodak DC265 Kodak DC280 Zoom Kodak DC290 Zoom Kodak DC3200 Kodak DC3400 Zoom Kodak DC3800 Kodak DC4800 Zoom Kodak DC5000 Zoom Kodak DCS Pro 14n Kodak DCS Pro 14nx Kodak DCS Pro SLR/c Kodak DCS Pro SLR/n Kodak DCS Pro Back 645 Kodak DCS315 Kodak DCS330 Kodak DCS420 Kodak DCS460 Kodak DCS520 Kodak DCS520C Kodak DCS560 Kodak DCS620 Kodak DCS620x Kodak DCS660

Makernote Coding x Kyocera
x Kyocera x Kyocera x Kyocera
Kyocera Kyocera Kyocera Kyocera
x x x x x x x x x x x x x x x
Empty APP1 segment x x x x x x x x x x x x x x x x x x x x x x x x x x x x x x x x x x x x x x x x x x x x x x x x x x x x x x x x x x Nikon Type 1 Fujifilm Nikon Type 1 Nikon Type 2 Nikon Type 2 Nikon Type 1 Nikon Type 1 Nikon Type 2 Nikon Type 2 Nikon Type 3 Nikon Type 3 Nikon Type 2 Nikon Type 3 Nikon Type 3
Camera Nikon Coolpix 3500 Nikon Coolpix 3700 Nikon Coolpix 4300 Nikon Coolpix 4500 Nikon Coolpix 5000 Nikon Coolpix 5400 Nikon Coolpix 5700 Nikon Coolpix 8700 Nikon Coolpix SQ Nikon D1 with Nikkor 28mm-105mm F3.5-4.5D Nikon D1H Nikon D1X with 28-105mm F3.5-4.5 Nikon D2H with VR 70-200 mm F2.8 G Nikon D70 with kit 18-70mm Nikon D100 with 24-85mm Olympus C-1 (D-100) Olympus C-21 Olympus C-50 Zoom (X-2) Olympus C-60 Zoom (X-3) Olympus C-700 UZ Olympus C-720 UZ Olympus C-730 UZ Olympus C-740 UZ Olympus C-750 UZ Olympus C-765 UZ Olympus C-770 UZ Olympus C-2000 Zoom Olympus C-2020 Zoom Olympus C-2040 Zoom Olympus C-2100 UZ Olympus C-2500 L Olympus C-3000 Zoom Olympus C-3020 Zoom (C-3100 Zoom) Olympus C-3030 Zoom
x x x x x x x x x x x x x x x x x x x x x x x x x x x x x x x x x x
Makernote Coding Nikon Type 3 Nikon Type 3 Nikon Type 3 Nikon Type 3 Nikon Type 2 Nikon Type 3 Nikon Type 3 Nikon Type 3 Nikon Type 3 Nikon Type 2 Nikon Type 2 Nikon Type 2 Nikon Type 3 Nikon Type 3 Nikon Type 3 Olympus Olympus Olympus Olympus Olympus Olympus Olympus Olympus Olympus Olympus Olympus Olympus Olympus Olympus Olympus Olympus Olympus Olympus Olympus
Camera Olympus C-3040 Zoom Olympus C-4000 Zoom (C-4100 Zoom) Olympus C-4040 Zoom Olympus C-5000 Zoom Olympus C-5050 Zoom Olympus C-5060 Wide Zoom Olympus C-8080 Wide Zoom Olympus D-40 Zoom (C-40 Zoom) Olympus D-150Z (C-1Z) Olympus D-200L Olympus D-230 (C-2) Olympus D-300L Olympus D-340L Olympus D-340R (C-830L) Olympus D-360L (C-860L) Olympus D-370 (C-100) Olympus D-380 (C-120) Olympus D-390 (C-150) Olympus D-395 (C-160) Olympus D-400 Zoom (C-900 Zoom) Olympus D-450 Zoom (C-920 Zoom) Olympus D-460 Zoom (C-960 Zoom) Olympus D-490 Zoom (C-990 Zoom) Olympus D-500L Olympus D-510 Zoom (C-200 Zoom) Olympus D-520 Zoom (C-220 Zoom, C-2 Zoom) Olympus D-540 Zoom (C-310 Zoom, X-100) Olympus D-550 Zoom (C-300 Zoom) Olympus D-560 Zoom (C-350 Zoom, X-200) Olympus D-565 Zoom (C-450 Zoom, X-300) Olympus D-580 Zoom (C-460 Zoom, X-400) Olympus D-600L Olympus D-620L Olympus E-1

EXPERIMENT NO. 1 FLOW VISUALIZATION Submitted by: Isaac W. Newton
AEROSPACE AND OCEAN ENGINEERING DEPARTMENT VIRGINIA POLYTECHNIC INSTITUTE AND STATE UNIVERSITY BLACKSBURG, VIRGINIA 27 JANUARY 2002 Experiment Performed 20 January 2002 Lab Instructor: Jeff K. Immelt
INTRODUCTION Flow visualization is an experimental means of examining flow patterns around a body and over its surface. The purpose of this experiment is as follows; To gain experience of the smoke flow and oil flow visualization techniques To use them to study airfoil separation (stall) Using the vertical smoke tunnel separation points over a NACA 2412 airfoil were measured at varying angles of attack and two Reynolds numbers at varying test section width. The three foot subsonic wind tunnel was utilized to measure separation points on a Clark Y airfoil wing section. Surface oil flow patterns were used to distinguish and reveal the 3D aspects of separation at two angles of attack at identical Reynolds numbers. APPARATUS AND TECHNIQUES Smoke Tunnel Description The smoke tunnel is a relatively small vertical tunnel through which atmospheric air is drawn. A top mounted variable speed fan draws atmospheric air through a turbulence screen at the lower entrance, which measures 35.5 cm x 17.8 cm. The tunnel then converges to the test section where the body of analysis is placed. The tunnel then converges to a circular diameter of 12.7 cm at the fan. Upstream from the body of analysis in an airfoil section strut with small hole punched at even intervals in the trailing edge. Kerosene vapor is produced and fed into the strut by a Preston-Sweeting mist generator. The strut has a black bulb at the end which, when pumped helps clear out any residual kerosene in the piping system. The kerosene vapor is drawn from the strut by the freestream air and forms easily distinguishable streamlines. A sketch of the vertical smoke tunnel can be seen in FIGURE 1. A clear Plexiglas window over the front test section allows a clear view and access to the test body. A modified test section window is used to examine effects of blockage (constraining of flow due to narrow test section). The window has side panels which reduce the effective width of the test section to 12.7 cm. A Fuji FinePix 2300 digital camera, mounted on the tripod was used to take photographs of the flow.
FIGURE 1 Smoke Tunnel NACA 2412 Airfoil Model The body used for analysis in this experiment was an NACA 2412 airfoil model. This is a camber airfoil with a maximum thickness of 12% of the chord or 1.224 cm. The model has a span of 9.9 cm. A threaded stud protrudes from one end to allow mounting. The wing section rotates on the stud to the desired angle of attack. The wing section is butted up against the back wall of the test section and spans the width of the test section butting up against the Plexiglas access cover in the front. The airfoil mounts 8.9 cm from the test section entrance and 9.0 cm from the right hand wall. Three Foot Subsonic Wind Tunnel (Open Jet Tunnel) Description Using the three foot subsonic wind tunnel the 3D effects of separation on a Clark Y airfoil section were analyzed. The test section of subsonic wind tunnel measures 90 cm x 90 cm in cross section (see FIGURE 2). Freestream velocity is measured using a pitot-static probe connected to a digital manometer (accuracy -+
0.01). Ambient temperature inside and outside the tunnel is measured using a digital thermometer (accuracy -+ 0.1). Ambient pressure is measured using a barometer attached outside of the tunnel.

FIGURE 2 Open Jet Tunnel Clark Y Airfoil Section The Clark Y airfoil section model is made of wood. The model chord length is 20.3 cm. Elliptical endplates with a major diameter of 38.1 cm and a minor diameter of 20.3 cm is used. The airfoil section is mounted on a shaft which allows rotation of the wing to the desired angle of attack. The shaft is located about one third of the way from the leading edge. FIGURE 3 shows an isometric view of the airfoil section.
FIGURE 3 Clark Y Airfoil Surface Oil Flow Visualization Techniques Surface oil flow is a useful technique for examining the 3D effect of separation. Oil is spread over the surface of the airfoil section. After the wind tunnel has been run at the desired velocity areas of high oil concentration will form. These high oil concentration areas are flow separation. The composition of oil includes kerosene, titanium dioxide (TiO2) and oleic acid Results and Discussion Smoke Tunnel Measurements Smoke tunnel measurements were taken over varying angles of attack and two Reynolds numbers; Re = 9306.13 and Re = 18612.25. The effects of
blockage were also considered at varying angles of attack at a signal Reynolds number; Re = 9306.13 and test section width 12.7 cm. Where Reynolds Number, Re = Uc/v = 1.4578 x 10-6T1.5/(T + 110.4) Sutherland Relation from lab book. Examining effects of Reynolds number The NACA 2412 airfoil section was initially set at 12 degrees angle of attack. With the mist generator on smoke streamline formed. The average location of separation was then marked along the chord length of the airfoil section on the Plexiglas window with error bars forward and aft of this mark indicating distance from the average at which separation occurred. The distance from the leading edge to these three marks was then recorded. This process was repeated for 8, 4, 0 angle of attack. FIGURE 4 is a photograph of the flow at 4 angle of attack. Tabulated data appears in TABLE 1.
FIGURE 4 1.5 m/s, 4 angle of attack
TABLE 1 1.5 m/s velocity Angle of Average location of Forward most location Attack separation of separation 12 0.12 0.0.28 0.0.96 0.no no Ambient pressure = 943.3 mbars Ambient Temp = 22.8C
Aft most location of separation 0.19 0.37 1.00 no
The angle of attack was then set to 12 and the electric fan voltage increased to 67 volts which corresponds to a speed of 3.0 m/s. The location of separation was measured and recorded as stated above. FIGURE 5 is a photograph of the flow at 8 angle of attack, data is in TABLE 2.

FIGURE 5 3.0 m/s, 8 angle of attack
TABLE 2 3.0 m/s velocity Angle of Average location of Forward most location Attack separation of separation 12 0.08 0.0.09 0.0.37 0.0.72 0.65 Ambient pressure = 943.3 mbars Ambient Temp = 22.8C
Aft most location of separation 0.11 0.16 0.48 0.76
As can be seen from FIGURE 6, as angle of attack is increased the separation point moves further up. The Reynolds number effect is clearly evident at zero degrees angle of attack since separation did not occur at the lower Reynolds number (Re = 9306.13), while at the higher Reynolds number (Re = 18612.25) separation occurred at approximately 70 % chord. This shift in separation point forward is indicative of an increase in the adverse pressure gradient.
Stal l Loclea atiodin n g (meedg asue) red %c fro hor m d
1.0.8 0.6 0.4 0.Angle of Attack (deg)

3.0m/s 1.5m/s

FIGURE 6 Separation location as a function of angle of attack Examining the effects of blockage The regular test section window was removed and replaced with the modified test section window which reduces the effective width of the test section to 12.7 cm. The airfoil section was set to 12 angle of attack and the electric fan was set to 44 volts (1.5 m/s). The location of separation was measured and recorded in the same manner as in Examining the Effects of Reynolds Number. FIGURE 7 is a photograph of the flow at 8 angle of attack. Tabulated data appears in TABLE 3.
FIGURE 7 1.5 m/s, 8 angle of attack, with blockage TABLE 3 1.5 m/s velocity with blockage Average location Forward most
Angle of Attack 12 0.12 0.0.30 0.0.62 0.no no Ambient pressure = 943.3 mbars; Ambient Temp = 22.8C
Aft most 0.19 0.40 0.72 no
FIGURE 7 shows the significant effect of reduced test section width or blockage. The constrained flow in the test section results in premature separation at lower angles of attack. The constraining of the flow increases freestream velocity and alters the flow pattern and characteristics.
Open Jet Measurements Examining separation using the oil flow technique Utilizing oil flow visualization the 3D effects of separation were analyzed. Oil was of the following composition; using a graduated cylinder TiO2 was measured. The TiO2 was then sifted through a strainer to remove any lumps. Next, 45 ml of kerosene were measured and 3 ml of oleic acid added to the kerosene. Finally, all ingredients were combine in a mixing container. The Clark Y airfoil section was prepared for the oil mixture by a light cleaning with kerosene. The airfoil section was then set to 17 angle of attack using an inclinometer placed on lower side (pressure side) of the airfoil. The chord line on the Clark Y airfoil is two degrees higher than the lower surface. Oil was then applied to one side of the airfoil section in an extremely small quantity. If excess oil is applied to the airfoil section puddling and dripping will occur. The wind tunnel was then turned on and the wind velocity increased, slowly to the desired speed, which gave a reading of two inches on the nulling manometer. The tunnel was run for approximately five minutes, allowing the flow patterns to form and the kerosene to evaporate. The flow temperature was also recorded at this time. Measurement were then taken along the chord at various spanwise location. Tabulated data appears in TABLE 5. TABLE 5 Spanwise Position Separation Point (cm) (cm) 2.413 1.2954 5.461 1.62052 9.398 1.83388 12.446 2.03708 16.256 1.62814 21.082 1.38176 Ambient pressure = 943.3 mbars Flow temp = 22.7C Error Points (cm) 0.2286 0.254 0.1778 0.1524 0.1778 0.127

The angle of attack was then increased to 23 and the Reynolds number held constant and the above procedure repeated. Tabulated data appears in TABLE 6. TABLE 6
Spanwise Position Separation Point (cm) (cm) 0 1.00584 2.54 0.84328 7.62 0.79502 12.7 0.62992 17.78 0.6096 22.86 0.5842 Ambient pressure = 943.3 mbars Flow temp = 22.7C
Error Points (cm) 0.2286 0.1778 0.1524 0.2032 0.2794 0.2286
As can be seen in FIGURE 9, which is a plot of separation point vs spanwise location, the 3-dimensional aspects of flow can effect the entire flow field. At 17 angle of attack the flow separates further forward in the mid-span area and move aft as the section ends are approached. At 23 angle of attack the separation line does not seem to be as effected by the 3D of the flow. Only at the last few centimeters does the separation line begin to shift forward. Comparing between the two angles of attack the effect of angle of attack on separation can be seen.
Se 2.5 par ati on 2 Lo cat 1.5 ion (fr cm om 1 lea din 0.5 g ed ge) 25
FIGURE 9 Spanwise separation location at two angles of attack The accuracy of this experiment is highly dependent on the mixture of oil and surface preparation. Great efforts were taken to eliminate the introduction of
error by carefully & accurately mixing the oil and carefully cleaning the application area and the results are very accurate. CONCLUSION Utilizing a 2 tunnels experience in smoke and oil flow visualization techniques was gained. Using these techniques airfoil separation was studied. To demonstrate these techniques an NACA 2412 and Clark Y airfoil section were used. From the above studies the following was learned; 1. Separation line moves forward with an increase in angle of attack 2. Increase in Reynolds number and blockage moves the separation location 3. Separation patterns on an airfoil are unique 4. Oil and smoke flow visualization techniques are very valuable