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An airfoil is in airflow with 0.52 free stream Mach number. Local Mach number at a given point is 0.82. …
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- 1 answers
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A finite wing with an elliptical lift distribution has an aspect ratio of 6. The airfoil of the wing has …
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- 1 answers
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An airplane is cruising at 50\,m/s at standard sea level in straight and level flight. The airplane has a wing …
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A finite wing has aspect ratio of 6 and taper ratio of 0.8. The airfoil constituting this wing has a …
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- 1 answers
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A NACA 4421 airfoil having a chord length of 2\,m is flying at an velocity of 70\,m/s at an altitude …
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An airfoil has a lift coefficient and moment coefficient of -0.35 and -0.050 about quarter-chord at -6^{\circ} angle of attack. …
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A NACA 0012 airfoil having a chord of 2.3\,m is in an airstream velocity of 70\,m/s at standard sea level …
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A positively cambered airfoil has a zero-lift angle of -3.5^{\circ}. The lift slope for this airfoil is 0.12 per degree. …
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Find the coefficient of pressure at a point on the wing where the velocity is 58\,m/s. The airplane is flying …
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- 1 answers
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Calculate the pressure coefficient at a point on the airfoil where the pressure is 8.9 \times 10^4\,N/m^2. Airfoil is …
- 1K views
- 1 answers
- 0 votes