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author | prashantsinalkar | 2017-10-10 12:27:19 +0530 |
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committer | prashantsinalkar | 2017-10-10 12:27:19 +0530 |
commit | 7f60ea012dd2524dae921a2a35adbf7ef21f2bb6 (patch) | |
tree | dbb9e3ddb5fc829e7c5c7e6be99b2c4ba356132c /3765/CH3 | |
parent | b1f5c3f8d6671b4331cef1dcebdf63b7a43a3a2b (diff) | |
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initial commit / add all books
Diffstat (limited to '3765/CH3')
-rw-r--r-- | 3765/CH3/EX3.10/Ex3_10.sce | 23 | ||||
-rw-r--r-- | 3765/CH3/EX3.13/Ex3_13.sce | 18 | ||||
-rw-r--r-- | 3765/CH3/EX3.2/Ex3_2.sce | 31 | ||||
-rw-r--r-- | 3765/CH3/EX3.3/Ex3_3.sce | 30 | ||||
-rw-r--r-- | 3765/CH3/EX3.4/Ex3_4.sce | 37 | ||||
-rw-r--r-- | 3765/CH3/EX3.6/Ex3_6.sce | 17 | ||||
-rw-r--r-- | 3765/CH3/EX3.7/Ex3_7.sce | 20 |
7 files changed, 176 insertions, 0 deletions
diff --git a/3765/CH3/EX3.10/Ex3_10.sce b/3765/CH3/EX3.10/Ex3_10.sce new file mode 100644 index 000000000..4becf3099 --- /dev/null +++ b/3765/CH3/EX3.10/Ex3_10.sce @@ -0,0 +1,23 @@ +clc +// Example 3.10.py +// In example 3.9, how much heat per unit mass must be added to choke the flow// + + +// Variable declaration from example 3.9 +To1 = 840 // upstream total temperature (in K) +M1 = 3.0 // upstream mach number +To1_by_Tostar = 0.6540 // To1/Tostar from Table A3 +cp = 1004.5 // specific heat at constant pressure for air (in J/Kg K) + +// Calculations +Tostar = To1 / To1_by_Tostar // Tostar = To1 * Tostar/To1 (in K) + +M2 = 1.0 // for choked flow +To2 = Tostar // since M2 = 1.0 + +q = cp * (To2 - To1) // required heat = cp(To2 - To1) (in J/kg) + + +// Result +printf("\n Heat require to choke the flow is %.2e J/kg", q) + diff --git a/3765/CH3/EX3.13/Ex3_13.sce b/3765/CH3/EX3.13/Ex3_13.sce new file mode 100644 index 000000000..f4d3590d0 --- /dev/null +++ b/3765/CH3/EX3.13/Ex3_13.sce @@ -0,0 +1,18 @@ +clc +// Example 3.13.py +// In example 3.12, what is the length of the duct required to choke the flow// + + +// Variable declaration from example 3.12 +M1 = 3.0 // mach number +C1 = 0.5222 // C1 = 4*f*L1star/D +f = 0.005 // friction coefficient +D = 0.4 // diameter of pipe (in ft) + +// Calculations +L1star = 0.5222 * D/4.0/f + + +// Result +printf("\n Length required to choke the flow is %.2f ft", L1star) + diff --git a/3765/CH3/EX3.2/Ex3_2.sce b/3765/CH3/EX3.2/Ex3_2.sce new file mode 100644 index 000000000..b845282e5 --- /dev/null +++ b/3765/CH3/EX3.2/Ex3_2.sce @@ -0,0 +1,31 @@ +clc +// Example 3.2.py +// Return to Example 1.6, Calculate the Mach Number and velocity at the exit of the rocket +// nozzle. + +// Variable declaration from example 1.6 +pc = 15.0 // pressure combustion chamber (atm) +Tc = 2500.0 // temperature combustion chamber (K) +mol_wt = 12.0 // molecular weight (gm) +cp = 4157.0 // specific heat at constant pressure (J/Kg/K) + +Tn = 1350.0 // temperature at nozzle exit (K) + +// Calculations +R = 8314.0/mol_wt // gas constant = R_prime/mo_wt, R_prime = 8314 J/K +cv = cp - R // specific heat at constant volume (J/Kg k) +gamma1 = cp/cv // ratio of specific heat + +pn_by_pc = (Tn/Tc** gamma1/(gamma1-1)) // ratio of pressure for isentropic process** pn/pc + +Mn = (2/(gamma1-1)*((1/pn_by_pc**(gamma1-1)/gamma1) - 1)** 0.5) // Mach number at exit** from isentropic flow relation + +an = (gamma1*R*Tn** 0.5) // Speed of sound at exit (m/s) +Vn = Mn*an // Velocity at exit (m/s) + + +// Result +printf("\n Mach number at the exit of the rocket nozzle is %.3f",(Mn)) + +printf("\n Velocity at the exit of the rocket nozzle is %.1f m/s",(Vn)) + diff --git a/3765/CH3/EX3.3/Ex3_3.sce b/3765/CH3/EX3.3/Ex3_3.sce new file mode 100644 index 000000000..91e85eaf0 --- /dev/null +++ b/3765/CH3/EX3.3/Ex3_3.sce @@ -0,0 +1,30 @@ +clc +// Example 3.3.py +// Return to Example 1.1, calculate the percentage density change between the given point +// on the wing and the free-stream, assuming compressible flow. + +// Variable declaration from example 1.1 +rho_1 = 0.002377 // density at sea level (slug/ft^3) +T_1 = 519.0 // temperature at sea level (R) +v_1 = 100.0 // velocity far ahead of the wing (mi/h) +v_2 = 150.0 // velocity at some point on the wing (mi/h) +gamma1 = 1.4 // ratio of specific heat capacity for air +R = 1716.0 // gas constant (ft lbf/slug/R) + +// Calculations +cp = gamma1*R/(gamma1-1) // specific heat capacity at constant pressure (ft lb/ slug / R) +u_1 = v_1 * 88.0/60.0 // converting v_1 in ft/s +u_2 = v_2 * 88.0/60.0 // converting v_2 in ft/s + +T_2 = T_1 + (u_1*u_1 - u_2*u_2)/cp/2.0 // temperature at a point from energy equation (R) + +rho_2_by_rho_1 = ((T_2/T_1)** 1/(gamma1-1))// density ratio from isentropic flow relation + +rho_2 = rho_2_by_rho_1 * rho_1 // density at the point (slug/ ft^3) + +delrho = rho_1 - rho_2 // change in density (slug/ ft^3) +fracrho = delrho/rho_1 // fractional change in density + +// Result +printf("\n Percentage change in density is %.1f",(fracrho*100)) + diff --git a/3765/CH3/EX3.4/Ex3_4.sce b/3765/CH3/EX3.4/Ex3_4.sce new file mode 100644 index 000000000..3f4dc9308 --- /dev/null +++ b/3765/CH3/EX3.4/Ex3_4.sce @@ -0,0 +1,37 @@ +clc +// Example 3.4.py +// A normal shock wave is standing in the test section of a supersonic wind tunnel. +// Upstream of the wave, M1 = 3, p1 = 0.5 atm, and T1 = 200 K. Find M2, p2, T2 and +// u2 downstream of the wave + + +// Variable declaration from example 1.1 +M1 = 3.0 // upstream mach number +p1 = 0.5 // upstream pressure (atm) +T1 = 200.0 // upstream temperature (K) +R = 287.0 // gas constant (J/Kg/K) +gamma1 = 1.4 // ratio of specific heats for air + +// Calculations + +// from shock relation (Table A2) for M1 = 3.0 +// subscript 2 means downstream of the shock +p2_by_p1 = 10.33 // p2/p1 +T2_by_T1 = 2.679 // T2/T1 +M2 = 0.4752 // M2 + +p2 = p2_by_p1 * p1 // downstream pressure (atm) +T2 = T2_by_T1 * T1 // downstream temperature (K) +a2 = (gamma1*R*T2** 0.5) // speed of sound downstream of the shock (m/s) +u2 = M2*a2 // downstream velocity (m/s) + + +// Result +printf("\n M2 = %.4f",(M2)) + +printf("\n p2 = %.3f atm",(p2)) + +printf("\n T2 = %.1f K",(T2)) + +printf("\n u2 = %.1f m/s",(u2)) + diff --git a/3765/CH3/EX3.6/Ex3_6.sce b/3765/CH3/EX3.6/Ex3_6.sce new file mode 100644 index 000000000..0ad8c2aa0 --- /dev/null +++ b/3765/CH3/EX3.6/Ex3_6.sce @@ -0,0 +1,17 @@ +clc +// Example 3.6.py +// Consider a point in a supersonic flow where the static pressure is 0.4 atm. When +// a pitot tube is inserted in the at this point, the pressure measured by the +// pitot tube is 3 atm. Calculate the mach number at this point. + +// Variable declaration +p1 = 0.4 // static pressure (in atm) +po2 = 3.0 // pressure measured by the pitot tube (in atm) + +//Calculations +// from table A2 for po2/p1 = 7.5 +M1 = 2.35 + +// Results +printf("\n Mach number is %.2f",(M1)) + diff --git a/3765/CH3/EX3.7/Ex3_7.sce b/3765/CH3/EX3.7/Ex3_7.sce new file mode 100644 index 000000000..72afdaa62 --- /dev/null +++ b/3765/CH3/EX3.7/Ex3_7.sce @@ -0,0 +1,20 @@ +clc +// Example 3.7.py +// For the normal shock that occurs in front of the pitot tube in Example 3.6, +// calculate the entropy change across the shock. + + +// Variable declaration +M1 = 2.34 // mach number from example 3.6 +R = 1716.0 // gas constant (ft lbf/slug/R) + +// Calculations +// subscript 2 means downstream of the shock + +po2_by_po1 = 0.5615 // from shock table A2 for mach M1 +// +dels = -R*log(po2_by_po1) // s2 - s1 (in lb/slug R) + +// Result +printf("\n Change is entropy is %.1f lb/slug R", dels) + |