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Find the shock angle and the total temperature at point P.
Consider an inviscid, adiabatic flow of air at free stream Mach number \(M_{\infty}=2\), across a compression corner \(\left ( \theta …
GATE

Kisan Kumar Asked on 15th October 2019 in Aerodynamics.
- 1K views
- 1 answers
- 0 votes
Poll Prandtl’s lifting line theory.
In the context of prandtl’s lifting line theory for a finite wing,which of the following combinations of statement is true?
GATE

Kisan Kumar Asked on 15th October 2019 in Aerodynamics.
- 857 views
- 2 answers
- 0 votes
Consider the inviscid,adiabatic flow of air at free stream conditions \(M_{1}=2,P_{1}=1\;atm\) and \(T_{1}=288\;K\) around a sharp expansion corner \(\left ( \theta =20^{\circ} \right )\). Assume air to be calorically perfect with \(\gamma =1.4\). What is the Mach number \(M_{2}\), downstream of the expansion corner ?
Consider the inviscid,adiabatic flow of air at free stream conditions \(M_{1}=2,P_{1}=1\;atm\) and \(T_{1}=288\;K\) around a sharp expansion corner \(\left ( …
GATE

Kisan Kumar Asked on 14th October 2019 in Aerodynamics.
- 1K views
- 1 answers
- 0 votes
A low speed wind tunnel has a contraction ratio of 14:1 and the cross-sectional area of the test section is 1m^2. The static pressure difference between the settling chamber and the test section is 40 cm of water column. Assume g=9.81m/s2,ρ_air=1.2kg/m3 and ρ_water=1000kg/m3. What is the speed of air in the test section?
A low speed wind tunnel has a contraction ratio of \(14:1\) and the cross-sectional area of the test section is …
GATE

Kisan Kumar Asked on 10th October 2019 in Aerodynamics.
- 1K views
- 1 answers
- 0 votes
What is the ratio of the Mach number downstream of the shock to its normal component?
An oblique shock wave with a wave angle \(\beta\) is generated from a wedge angle of \(\theta\).What is the ratio …
GATE

Kisan Kumar Asked on 8th October 2019 in Aerodynamics.
- 1K views
- 0 answers
- 0 votes
An airfoil generates a lift of 80 N when operating in a free stream flow of 60 m/s. If the ambient pressure and temperature are 100 kPa and 290 K respectively ( specific gas constant is 287 J/kg-K), find the circulation on the airfoil.
An airfoil generates a lift of 80 N when operating in a free stream flow of 60 m/s. If the …
GATE

incompressible flow

Kisan Kumar Asked on 30th September 2019 in Aerodynamics.
- 1K views
- 1 answers
- 0 votes
Write a matlab code for a point vortex.
Write a Matlab code for a point vortex.
Matlab

vortex flow

Worldtech Asked on 9th September 2019 in Aerodynamics.
- 2K views
- 1 answers
- 0 votes
Write a Matlab code for a doublet at the origin.
Write a Matlab code for a doublet at the origin.
incompressible flow

Matlab

techAir Asked on 5th September 2019 in Aerodynamics.
- 2K views
- 1 answers
- 0 votes
Write a matlab code for a Uniform flow flowing in X direction.
Write a matlab code for a uniform flow flowing in X – direction having a constant velocity depicting equipotential lines …
incompressible flow

Worldtech Asked on 10th August 2019 in Aerodynamics.
- 1K views
- 1 answers
- 0 votes
Write a matlab code for a source at the origin.
Write a MATLAB code for a source flow at the origin.
incompressible flow

techAir Asked on 10th August 2019 in Aerodynamics.
- 1K views
- 0 answers
- 0 votes

Poll Prandtl’s lifting line theory.

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