B-29 TIP AIRFOIL (b29tip-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: B-29 TIP AIRFOIL (b29tip-il) Reynolds number: 200,000 Max Cl/Cd: 68.77 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-b29tip-il-200000.txt Download as CSV file: xf-b29tip-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: B-29 TIP AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.4255 0.09774 0.09460 -0.0022 1.0000 0.0459
-9.250 -0.4226 0.09391 0.09078 -0.0033 1.0000 0.0470
-9.000 -0.5165 0.09550 0.09216 -0.0056 1.0000 0.0445
-8.750 -0.5104 0.09224 0.08892 -0.0060 1.0000 0.0455
-8.500 -0.5078 0.08876 0.08546 -0.0074 1.0000 0.0464
-8.250 -0.5074 0.08512 0.08187 -0.0094 1.0000 0.0476
-8.000 -0.5109 0.08127 0.07807 -0.0122 1.0000 0.0485
-7.750 -0.5154 0.07742 0.07424 -0.0146 1.0000 0.0495
-7.500 -0.5154 0.07311 0.06991 -0.0177 1.0000 0.0510
-7.250 -0.5149 0.06834 0.06495 -0.0231 1.0000 0.0538
-7.000 -0.5128 0.06539 0.06163 -0.0246 1.0000 0.0546
-6.750 -0.5099 0.05812 0.05441 -0.0252 1.0000 0.0558
-6.500 -0.4966 0.05494 0.05132 -0.0248 1.0000 0.0571
-6.250 -0.4834 0.05222 0.04857 -0.0244 1.0000 0.0589
-6.000 -0.4700 0.04931 0.04558 -0.0243 1.0000 0.0617
-5.750 -0.4571 0.04920 0.04471 -0.0228 1.0000 0.0679
-5.500 -0.4430 0.04199 0.03769 -0.0247 0.9879 0.0703
-5.250 -0.4077 0.03925 0.03495 -0.0281 0.9686 0.0757
-5.000 -0.3535 0.01985 0.01541 -0.0310 0.9011 0.0853
-4.750 -0.3381 0.01794 0.01334 -0.0293 0.8845 0.0891
-4.500 -0.3238 0.01565 0.01062 -0.0274 0.8687 0.0987
-4.250 -0.3055 0.01396 0.00884 -0.0262 0.8555 0.1028
-4.000 -0.2774 0.02168 0.01438 -0.0238 0.8751 0.0429
-3.750 -0.2536 0.02048 0.01289 -0.0225 0.8604 0.0426
-3.500 -0.2297 0.01837 0.01050 -0.0214 0.8471 0.0433
-3.250 -0.2053 0.01701 0.00902 -0.0205 0.8344 0.0457
-3.000 -0.1802 0.01606 0.00796 -0.0196 0.8225 0.0469
-2.750 -0.1554 0.01524 0.00703 -0.0186 0.8114 0.0487
-2.500 -0.1307 0.01454 0.00626 -0.0176 0.7996 0.0516
-2.250 -0.1065 0.01389 0.00554 -0.0166 0.7885 0.0556
-2.000 -0.0828 0.01334 0.00496 -0.0155 0.7782 0.0675
-1.750 -0.0622 0.01227 0.00419 -0.0140 0.7689 0.1343
-1.500 -0.0208 0.00944 0.00427 -0.0163 0.7596 0.8966
-1.250 0.1227 0.01011 0.00451 -0.0385 0.7507 0.9983
-1.000 0.1507 0.01009 0.00430 -0.0386 0.7406 1.0000
-0.750 0.1741 0.01009 0.00418 -0.0379 0.7304 1.0000
-0.500 0.1974 0.01010 0.00406 -0.0371 0.7211 1.0000
-0.250 0.2209 0.01013 0.00396 -0.0363 0.7121 1.0000
0.000 0.2449 0.01016 0.00392 -0.0356 0.7029 1.0000
0.250 0.2686 0.01021 0.00384 -0.0348 0.6951 1.0000
0.500 0.2928 0.01024 0.00383 -0.0342 0.6858 1.0000
0.750 0.3170 0.01030 0.00381 -0.0335 0.6781 1.0000
1.000 0.3414 0.01035 0.00381 -0.0328 0.6699 1.0000
1.250 0.3658 0.01043 0.00384 -0.0322 0.6622 1.0000
1.500 0.3903 0.01050 0.00386 -0.0315 0.6545 1.0000
1.750 0.4149 0.01059 0.00394 -0.0310 0.6468 1.0000
2.000 0.4394 0.01068 0.00400 -0.0303 0.6396 1.0000
2.250 0.4640 0.01079 0.00411 -0.0297 0.6319 1.0000
2.500 0.4886 0.01089 0.00419 -0.0291 0.6250 1.0000
2.750 0.5133 0.01102 0.00435 -0.0285 0.6173 1.0000
3.000 0.5380 0.01114 0.00447 -0.0279 0.6104 1.0000
3.250 0.5626 0.01129 0.00467 -0.0273 0.6028 1.0000
3.500 0.5873 0.01143 0.00481 -0.0267 0.5959 1.0000
3.750 0.6120 0.01159 0.00504 -0.0261 0.5880 1.0000
4.000 0.6364 0.01169 0.00513 -0.0253 0.5798 1.0000
4.250 0.6600 0.01167 0.00511 -0.0242 0.5654 1.0000
4.500 0.6830 0.01160 0.00508 -0.0231 0.5473 1.0000
4.750 0.7067 0.01162 0.00513 -0.0221 0.5326 1.0000
5.000 0.7306 0.01170 0.00527 -0.0212 0.5200 1.0000
5.250 0.7545 0.01178 0.00542 -0.0204 0.5068 1.0000
5.500 0.7777 0.01179 0.00552 -0.0193 0.4857 1.0000
5.750 0.7996 0.01178 0.00548 -0.0180 0.4513 1.0000
6.000 0.8211 0.01194 0.00561 -0.0168 0.4052 1.0000
6.250 0.8392 0.01254 0.00589 -0.0152 0.3179 1.0000
6.500 0.8452 0.01474 0.00704 -0.0129 0.1389 1.0000
6.750 0.8524 0.01693 0.00866 -0.0103 0.0614 1.0000
7.000 0.8653 0.01833 0.01007 -0.0080 0.0453 1.0000
7.250 0.8770 0.01973 0.01144 -0.0058 0.0388 1.0000
7.500 0.8929 0.02068 0.01251 -0.0040 0.0354 1.0000
7.750 0.9070 0.02183 0.01370 -0.0019 0.0329 1.0000
8.000 0.9196 0.02327 0.01513 0.0002 0.0311 1.0000
8.250 0.9335 0.02563 0.01748 0.0023 0.0298 1.0000
8.500 0.9526 0.02689 0.01889 0.0037 0.0290 1.0000
8.750 0.9715 0.02824 0.02039 0.0051 0.0279 1.0000
9.000 0.9898 0.02980 0.02214 0.0065 0.0264 1.0000
9.250 1.0082 0.03197 0.02453 0.0078 0.0260 1.0000
9.500 1.0246 0.03459 0.02744 0.0094 0.0260 1.0000
9.750 1.0370 0.03769 0.03090 0.0112 0.0263 1.0000
10.000 1.0444 0.04128 0.03488 0.0134 0.0270 1.0000
10.250 1.0470 0.04521 0.03915 0.0156 0.0280 1.0000
10.500 1.0452 0.04965 0.04386 0.0177 0.0290 1.0000
11.750 0.8670 0.06225 0.05809 0.0291 0.0372 1.0000
12.000 0.8422 0.06813 0.06411 0.0277 0.0376 1.0000
12.250 0.8160 0.07431 0.07042 0.0253 0.0376 1.0000
12.500 0.7874 0.08119 0.07744 0.0219 0.0373 1.0000
12.750 0.7561 0.08928 0.08566 0.0173 0.0369 1.0000
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Polar data table (+)
Polar graphs
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