An oblique shock wave with a wave angle Î² is generated from a wedge angle of

Question

An oblique shock wave with a wave angle Î² is generated from a wedge angle of Î¸. The ratio of the Mach number downstream of the shock to its normal component is

Options:

A . sin(Î²"“Î¸)

B . cos(Î²"“Î¸)

C . sin(Î¸"“Î²)

D . cos(Î¸"“Î²)

Answer: Option B

-NA-

Was this answer helpful ?

Next Question

Submit Solution

More Questions on This Topic :

Question 1. In a closed-circuit supersonic wind tunnel, the convergent-divergent (C-D) nozzle and test section are followed by a C-....to swallow the starting shock. Here, we should have the

Question 2. An aircraft is trimmed straight and level at true air speed (TAS) of 100 m/s at standard sea level (SSL). Further, pull....kg/m3) and 120 m/s TAS without re-trimming, the aircraft needs

Question 3. Data for an airplane are given as follows: weight W = 30kN, thrust available at sea-level T0 = 4000 N, wing planform ar....kg/ m3. Stall speed of the airplane in m/s is

Question 4. An aircraft is flying at Mach number M = 1.5, where the ambient temperature is 250 K. The stagnation temperature of gas....exit Mach numbers given below is the propulsive efficiency highest?

Question 5. A wing-body alone configuration airplane with a wing loading of W/S = 1000 N/m2 is flying in cruise condition at a spee....the chord length. The airplane trim lift coefficient CL trim is

Question 6. An aircraft is flying at Mach number M = 1.5, where the ambient temperature is 250 K. The stagnation temperature of gas....nozzle exit Mach numbers given below is the thrust highest?

Question 7. Data for an airplane are given as follows: weight W = 30kN, thrust available at sea-level T0 = 4000 N, wing planform ar....airplane in level flight condition at sea-level in m/s are respectively

Question 8. All professors are researchers Some scientists are professors Which of the given conclusions is logically valid and i....is logically valid and is inferred from the above arguments:

Question 9. Which one of the following statements is NOT TRUE for a supersonic flow? ....

Question 10. Consider a thin flat plate airfoil at a small angle x to an oncoming supersonic stream of air. Assuming the flow to be ....Assuming the flow to be inviscid, Cd / C2l is

Chapter 1 - GLOBAL STEEL SCENARIO & INDIAN STEEL INDUSTRY Part 1 : (13-04-2024) INDUSTRY AND COMPANY AWARENESS (ICA)

Direction Sense Test Part 1 Reasoning (Hindi)

Chapter 1 - RMHP / OHP / OB & BP Part 1 : (14-02-2024) GPOE

Cube & Cuboid Part 1 Reasoning (Hindi)

Data Interpretation (DI) Basic Concept Reasoning (Hindi)

Counting Figures Part 1 Counting Of Straight Lines Reasoning (Hindi)

Sail E0 free webinar Webinars

Real Numbers Part 7 Class 10 Maths

Real Numbers Part 1 Class 10 Maths

Polynomials Part 1 Class 10 Maths

DSP Combined 1 Free Revision Test SAIL JO E-0

GPOE / GPA Combined 1 Free Revision Test SAIL JO E-0

BSP Plant Specific Review Test SAIL JO E-0

BSL Combined 1 Free Revision Test SAIL JO E-0

GFM Combined 1 Free Revision Test SAIL JO E-0

Submit Solution

More Questions on This Topic :

Latest Videos

Latest Test Papers