B-29 TIP AIRFOIL (b29tip-il)
B-29 TIP AIRFOIL - Boeing B-29 tip airfoil
| Details | Dat file | Parser | |
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(b29tip-il) B-29 TIP AIRFOIL Boeing B-29 tip airfoil Max thickness 9% at 30% chord. Max camber 2.2% at 30% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
B-29 TIP AIRFOIL
19.0 21.0
0.0000000 0.0000000
0.0075149 0.0101442
0.0125046 0.0136584
0.0249843 0.0204940
0.0499554 0.0301654
0.0749328 0.0376370
0.0999142 0.0437086
0.1498843 0.0533519
0.1998618 0.0603954
0.2498462 0.0650390
0.2998375 0.0672827
0.3998371 0.0658704
0.4998552 0.0580585
0.5998839 0.0465468
0.6999180 0.0331352
0.7999519 0.0198236
0.8999808 0.0082119
0.9499917 0.0036560
1.0000000 -.0000000
0.0000000 0.0000000
0.0050092 -.0082226
0.0050680 -.0082620
0.0075716 -.0095547
0.0125762 -.0112403
0.0250839 -.0141042
0.0500918 -.0172321
0.0750953 -.0188601
0.1000975 -.0199881
0.1500994 -.0214442
0.2000997 -.0223003
0.2500985 -.0226564
0.3000964 -.0227126
0.4000917 -.0226249
0.5000867 -.0224372
0.6000798 -.0215496
0.7000698 -.0196620
0.8000548 -.0159745
0.9000326 -.0097872
0.9500182 -.0055435
1.0000000 -.0000000
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Polars for B-29 TIP AIRFOIL (b29tip-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| b29tip-il | 50,000 | 9 | 34.1 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| b29tip-il | 50,000 | 5 | 34.8 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| b29tip-il | 100,000 | 9 | 51.1 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| b29tip-il | 100,000 | 5 | 50.9 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| b29tip-il | 200,000 | 9 | 68.8 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| b29tip-il | 200,000 | 5 | 66.4 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| b29tip-il | 500,000 | 9 | 91.4 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| b29tip-il | 500,000 | 5 | 84.3 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| b29tip-il | 1,000,000 | 9 | 106.1 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| b29tip-il | 1,000,000 | 5 | 90 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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