C - Εθνικό Μετσόβιο Πολυτεχνείο

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C D untripped 0.4_tripped 0.205_tripped 0.18 0.16 0.14 0.12 0.10 0.08 0.06 0.04 0.02 0.00 -10 -5 0 5 aoa (deg) 10 15 20 Graph 2 All- inclusive graph of drag coefficient curve versus angle of attack of the experimental results of airfoil, airfoil tripped at 1% of chord using tripping tape of 0.4 mm width and airfoil tripped at 1% of chord using tripping tape of 0.205 mm width For the estimate of moment coefficient we use the previous data using the following equation r r CM = ∫ ( CP × r ) ⋅ ez ds s C D The experimental data are being corrected due to closed wind tunnel section, due to blockage effect and as for the zero lift angle of attack. Last but not least, we run a program code of the laboratory named FOIL2W to compare the computational results with these from the experimental test. MEASUREMENT OF POWER AND THRUST ON WIND TURBINE ROTOR The test is implemented using a rotor of short figure design to move the wind car. The test takes part in the No C test section of wind tunnel. The rotor is installed against the airflow approximately at the centre of the section while, at the same time, is based on a load pad measuring three forces, three moments. For the girderage of rotor there have been constructed an iron gantry capable of rotating at yaw angle. For the break of rotor there is used a DC motor with revolution control. The test is run for a range of rotational speed from 300 to 500 RPM. For the measurement of power, there have been installed an electrical box capable of reducing the voltage of motor and converting the current running through motor into voltage. The box through BNC cables sends the signals to an A/D card and thereafter to the PC. The power is estimated via the known relation P = VI, while the power coefficient via the equation P CP = 1 3 ρU A For the measurement of infinite velocity we use a Pitot tube at a sufficient distance ahead of the model and the subtraction of static from total pressure is measured in a manometer connected via a BNC cable with 2
2q an A/D card and afterwards is sent to the PC. The velocity is estimated via the known relationU = , ρ where q is the measured through the manometer dynamic pressure of undisturbed airflow. Using the same ⋅ Rtip velocity we estimate the non-dimensional tip-blade velocity according to the relation = U ω λ . The graph of power of experimental and computational data as well as the graph of power coefficient is shown below for a various rotational speed. power (W) 2000 1500 1000 500 0 -500 0 5 10 15 20 25 30 velocity (m/s) power Graph 3 All-inclusive graph of power curves versus air velocity pitch +0 300 RPM pitch+0 400 RPM pitch +0 500 RPM experimental 300 RPM experimental 400 RPM experimental 500 RPM
Page 1 and 2: Εθνικό Μετσόβιο Πο
Page 4 and 5: ΠΕΡΙΛΗΨΗ Η παρούσα
Page 6 and 7: C D untripped 0.4_tripped 0.205_tri
Page 8 and 9: Cp 0.6 0.5 0.4 0.3 0.2 0.1 0 0 2 4
Page 10 and 11: ABSTRACT The current project consti
Page 14 and 15: Cp 0.6 0.5 0.4 0.3 0.2 0.1 0 Cp 0 2
Page 16: ΠΕΡΙΕΧΟΜΕΝΑ Κεφάλα
Page 19 and 20: συνθηκών. Τέλειας π
Page 21 and 22: τους και της ταχύτη
Page 23 and 24: 2.2.3 Θέση δοκιμών Νο
Page 25 and 26: 2.3.1.2 Σχέδιο εδράνων
Page 27 and 28: περιορισμό λόγω κα
Page 29 and 30: 2.3.2.4 Φωτογραφία του
Page 31 and 32: 2.3.3 ΠΕΡΙ ΜΕΤΡΗΤΙΚΩΝ
Page 33 and 34: της στατικής πίεση
Page 35 and 36: D = −∫ ρ ⋅ ( V ⋅ n) ⋅V
Page 37 and 38: CL 1.60 1.40 1.20 1.00 0.80 0.60 0.
Page 39 and 40: Στην παρούσα εργασ
Page 41 and 42: 2.4.1 Οπίσθια φωτογρα
Page 43 and 44: 2.4.3 Σκαρίφημα του ό
Page 45 and 46: 2.4.1.1 Σκαρίφημα της
Page 47 and 48: 2.4.1.4 Φωτογραφία της
Page 49 and 50: 2.4.2 ΠΕΔΗΣΗ ΔΡΟΜΕΑ: Κ
Page 51 and 52: 2.4.2.2 Χαρακτηριστικ
Page 53 and 54: 2.4.3.1 Σκαρίφημα ζυγο
Page 55 and 56: 2.4.3.3 Ο πίνακας ελέγ
Page 57 and 58: αντίστασης προς τα
Page 59 and 60: Η ζυγοστάθμιση του
Page 61 and 62: Πάχος 0.4 mm ii. Τοποθέ
Page 63 and 64:
ως άθροισμα των δύο
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αυτό διάγραμμα, θεω
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CP CP 0.8 0.3 -0.2 -0.7 -1.2 -1.7 -
Page 69 and 70:
CP CP 0.8 0.3 -0.2 -0.7 -1.2 -1.7 -
Page 71 and 72:
CP CP 0.8 0.3 -0.2 -0.7 -1.2 -1.7 -
Page 73 and 74:
CP CP 0.8 -0.2 -1.2 -2.2 -3.2 -4.2
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Τα διαγράμματα της
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CP,w 1.2 1.1 1 0.9 0.8 0.7 0.6 -0.0
Page 79 and 80:
CP,w 1.2 1.1 1 0.9 0.8 0.7 0.6 -0.0
Page 81 and 82:
CP,w 1.2 1.1 1 0.9 0.8 0.7 0.6 -0.0
Page 83 and 84:
CP,w 1.2 1.1 1 0.9 0.8 0.7 0.6 -0.0
Page 85 and 86:
CP CP 0.8 0.3 -0.2 -0.7 -1.2 -1.7 -
Page 87 and 88:
CP CP 0.8 0.3 -0.2 -0.7 -1.2 -1.7 -
Page 89 and 90:
CP CP 0.8 0.3 -0.2 -0.7 -1.2 -1.7 -
Page 91 and 92:
CP CP 0.8 -0.2 -1.2 -2.2 -3.2 -4.2
Page 93 and 94:
Κατόπιν, παρουσιάζ
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CP,w 1.2 1.1 1 0.9 0.8 0.7 0.6 -0.0
Page 97 and 98:
CP,w 1.2 1.1 1 0.9 0.8 0.7 0.6 -0.0
Page 99 and 100:
CP,w 1.2 1.1 1 0.9 0.8 0.7 0.6 0.5
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CP,w 1.2 1.1 1 0.9 0.8 0.7 0.6 0.5
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CP CP 0.8 0.3 -0.2 -0.7 -1.2 -1.7 -
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CP CP 0.8 0.3 -0.2 -0.7 -1.2 -1.7 -
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CP CP 0.8 0.3 -0.2 0.000 0.200 0.40
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CP CP 0.5 -0.5 -1.5 -2.5 -3.5 -4.5
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Και έπειτα, τις κατ
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CP,w 1.2 1.1 1.0 0.9 0.8 0.7 0.6 -0
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CP,w 1.2 1.1 1.0 0.9 0.8 0.7 0.6 -0
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CP,w 1.2 1.1 1.0 0.9 0.8 0.7 0.6 0.
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CP,w 1.15 1.05 0.95 0.85 0.75 0.65
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διάστημα αβεβαιότη
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CD 3.7.2 Καμπύλη του συ
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CD 0.20 0.18 0.16 0.14 0.12 0.10 0.
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CD 0.18 0.16 0.14 0.12 0.10 0.08 0.
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Συντελεστής άνωσης
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φαινομένου που αντ
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Q2 παροχή από τον εξ
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lift coeff 1.6 1.4 1.2 1.0 0.8 0.6
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Τελικά, συγκρίνοντ
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F F F y x z M M M y x z = T + D = F
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P (W) 3500.00 3000.00 2500.00 2000.
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60 50 40 30 20 10 0 -10 -20 -30 0 1
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εξισορρόπηση της σ
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4.2.2.2 Θεωρητικές καμ
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Στην καμπύλη του CΤ
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χρειάζεται στο μέλ
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power (W) power (W) 1000 800 600 40
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thrust (N) 250 200 150 100 50 0 thr
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αριστερό σωλήνα γι
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P y Az = T = Fφ sinψ − B Ay + B
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160
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C - Εθνικό Μετσόβιο Πολυτεχνείο

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