B-29 TIP AIRFOIL (b29tip-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: B-29 TIP AIRFOIL (b29tip-il) Reynolds number: 50,000 Max Cl/Cd: 34.14 at α=7° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-b29tip-il-50000.txt Download as CSV file: xf-b29tip-il-50000.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 = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.5074 0.11370 0.10707 0.0070 1.0000 0.2098
-9.000 -0.4981 0.10949 0.10287 0.0069 1.0000 0.2177
-8.750 -0.5156 0.10832 0.10184 0.0039 1.0000 0.2262
-8.500 -0.4964 0.10344 0.09695 0.0051 1.0000 0.2388
-8.250 -0.4872 0.09955 0.09310 0.0053 1.0000 0.2505
-8.000 -0.4832 0.09616 0.08977 0.0050 1.0000 0.2628
-7.750 -0.4794 0.09294 0.08661 0.0050 1.0000 0.2778
-7.500 -0.4797 0.09010 0.08386 0.0052 1.0000 0.2965
-7.250 -0.4883 0.08774 0.08162 0.0049 1.0000 0.3135
-7.000 -0.4701 0.08391 0.07780 0.0072 1.0000 0.3408
-6.750 -0.4595 0.08061 0.07455 0.0091 1.0000 0.3686
-6.500 -0.4527 0.07767 0.07166 0.0111 1.0000 0.3991
-6.250 -0.4605 0.07568 0.06981 0.0137 1.0000 0.4320
-6.000 -0.4195 0.07125 0.06531 0.0170 1.0000 0.4823
-5.750 -0.3920 0.06796 0.06200 0.0207 1.0000 0.5421
-4.500 -0.4280 0.04444 0.03678 -0.0155 1.0000 0.1677
-4.250 -0.4195 0.04143 0.03345 -0.0133 1.0000 0.1517
-4.000 -0.4103 0.03911 0.03049 -0.0107 1.0000 0.1388
-3.750 -0.3993 0.03670 0.02798 -0.0088 1.0000 0.1348
-3.500 -0.3863 0.03459 0.02546 -0.0069 1.0000 0.1302
-3.250 -0.3718 0.03288 0.02338 -0.0051 1.0000 0.1297
-3.000 -0.3557 0.03139 0.02159 -0.0036 1.0000 0.1312
-2.750 -0.3378 0.02998 0.01985 -0.0023 1.0000 0.1331
-2.500 -0.3175 0.02866 0.01816 -0.0012 1.0000 0.1344
-2.250 -0.2962 0.02757 0.01673 -0.0002 1.0000 0.1371
-2.000 -0.2735 0.02638 0.01545 0.0003 1.0000 0.1450
-1.750 -0.1183 0.01952 0.01198 -0.0186 1.0000 1.0000
-1.500 -0.1105 0.01991 0.01179 -0.0161 1.0000 1.0000
-1.250 -0.0664 0.02044 0.01172 -0.0206 0.9890 1.0000
-1.000 -0.0162 0.02101 0.01182 -0.0262 0.9755 1.0000
-0.750 0.0307 0.02156 0.01202 -0.0311 0.9626 1.0000
-0.500 0.0767 0.02210 0.01230 -0.0357 0.9499 1.0000
-0.250 0.1218 0.02264 0.01260 -0.0400 0.9377 1.0000
0.000 0.1701 0.02315 0.01294 -0.0448 0.9262 1.0000
0.250 0.2107 0.02368 0.01334 -0.0481 0.9142 1.0000
0.500 0.2453 0.02425 0.01381 -0.0503 0.9021 1.0000
0.750 0.2773 0.02487 0.01435 -0.0519 0.8903 1.0000
1.000 0.3093 0.02549 0.01491 -0.0534 0.8789 1.0000
1.250 0.3459 0.02606 0.01547 -0.0556 0.8684 1.0000
1.500 0.3704 0.02679 0.01617 -0.0557 0.8571 1.0000
1.750 0.3874 0.02765 0.01701 -0.0547 0.8457 1.0000
2.000 0.4087 0.02849 0.01785 -0.0543 0.8350 1.0000
2.250 0.4395 0.02921 0.01863 -0.0552 0.8252 1.0000
2.500 0.4546 0.03020 0.01963 -0.0539 0.8145 1.0000
2.750 0.4666 0.03129 0.02073 -0.0522 0.8039 1.0000
3.000 0.4887 0.03225 0.02175 -0.0519 0.7944 1.0000
3.250 0.5116 0.03320 0.02279 -0.0516 0.7844 1.0000
3.500 0.5162 0.03456 0.02418 -0.0491 0.7742 1.0000
3.750 0.5341 0.03570 0.02539 -0.0483 0.7643 1.0000
4.000 0.5604 0.03669 0.02650 -0.0484 0.7548 1.0000
4.250 0.5620 0.03823 0.02808 -0.0458 0.7441 1.0000
4.500 0.5744 0.03960 0.02954 -0.0444 0.7339 1.0000
4.750 0.6005 0.04067 0.03080 -0.0444 0.7233 1.0000
5.000 0.6198 0.04186 0.03214 -0.0435 0.7114 1.0000
5.250 0.6275 0.04334 0.03372 -0.0415 0.6986 1.0000
5.500 0.6455 0.04450 0.03505 -0.0403 0.6843 1.0000
5.750 0.6834 0.04467 0.03550 -0.0398 0.6656 1.0000
6.000 0.6966 0.04545 0.03650 -0.0373 0.6442 1.0000
6.250 0.7432 0.04371 0.03516 -0.0347 0.6156 1.0000
6.500 0.8121 0.03736 0.02937 -0.0281 0.5758 1.0000
6.750 0.8577 0.03175 0.02410 -0.0207 0.5339 1.0000
7.000 0.8811 0.02581 0.01818 -0.0107 0.4356 1.0000
7.250 0.8674 0.02691 0.01752 -0.0026 0.2422 1.0000
7.500 0.8639 0.03007 0.01974 0.0012 0.1811 1.0000
7.750 0.8742 0.03282 0.02208 0.0039 0.1443 1.0000
8.000 0.8984 0.03535 0.02451 0.0055 0.1216 1.0000
8.250 0.9298 0.03824 0.02741 0.0063 0.1094 1.0000
8.500 0.9561 0.04134 0.03046 0.0069 0.1002 1.0000
8.750 0.9743 0.04421 0.03386 0.0085 0.0966 1.0000
9.000 0.9905 0.04767 0.03777 0.0101 0.0949 1.0000
9.250 1.0018 0.05135 0.04191 0.0117 0.0945 1.0000
9.500 1.0075 0.05519 0.04624 0.0135 0.0946 1.0000
9.750 1.0078 0.05909 0.05055 0.0153 0.0948 1.0000
10.000 1.0029 0.06316 0.05499 0.0170 0.0954 1.0000
10.250 0.9914 0.06718 0.05932 0.0186 0.0958 1.0000
10.500 0.9764 0.07136 0.06374 0.0198 0.0970 1.0000
10.750 0.9580 0.07543 0.06796 0.0209 0.0982 1.0000
11.000 0.9397 0.07991 0.07254 0.0210 0.0992 1.0000
11.250 0.9293 0.08506 0.07775 0.0203 0.1004 1.0000
11.500 0.7306 0.09169 0.08486 0.0133 0.1099 1.0000
11.750 0.7130 0.09940 0.09255 0.0102 0.1128 1.0000
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Polar data table (+)
Polar graphs
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