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Which one is incorrect? 1. Kumabaram Lift Canal-Older name - Nohar Sohwa Lift Canal. 2. Kawar sen Lift Canal-Older name - Lunaksar Lift Canal. 3. Panna Lal Lift Canal - Older name - Gajner Lift canal. 4. Veer Tejaji Lift Canal-Older name - Bagdsar.
An aircraft with elliptic wing planform has parasite drag coefficient as 0.6. Lift coefficient of wing is 0.25 and aspect ratio is 7.5. If induced drag co-efficient is 0.0235 then, find total drag coefficient for the wing.
An aircraft with elliptic wing planform has parasite drag coefficient as 0.9. Lift coefficient of wing is 1.8 and aspect ratio is 8.5. Find total drag coefficient for the wing.
A subsonic aircraft has unswept wing which has maximum lift coefficient of 1.4. Now, consider wing is provided sweep of 25° at quarter chord point. Now, determine the change in maximum lift coefficient due to the provision of sweep.
If moment coefficient about aerodynamic centre of wing is -0.216 and lift coefficient of wing is 1.2. Find moment coefficient about cg. Given cg location as Xcg = 0.3.
For estimated value of the thrust loading, we got three different values of wing loading. As a designer typically which wing loading should be considered?
Determine wing loading for civil aircraft if lift-off speed is 80m/s and maximum lift coefficient is 2.8.
Statements: 1. Sofa, park bench, arm chair, wing chair, deck chair, stool and wood chair are placed in a straight line facing north. 2. Arm chair is third to the left of wing chair which is second to the left of deck chair. 3. Deck chair is at extreme right end and stool is placed somewhere between arm chair and wing chair. 4. Third to the right of stool is wood chair. 5. Sofa is not at any end place. Conclusions: 1. Stool is at fifth place from the right end. 2. Sofa is at the middle place of the row. 3. Wing chair is at fifth place from the left end.
A twin turboprop engine is flying with 120m/s. Wing of the aircraft has span of 2m and lift co-efficient as 0.15 with aspect ratio as 9.2. Find the lift produced by the wing.
A wing is to be loft with span as 2m and reference area of wing is 4m2. If we want to design the wing with taper ratio of 0.6 then what will be the value of root chord?