B-29 ROOT AIRFOIL (b29root-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: B-29 ROOT AIRFOIL (b29root-il) Reynolds number: 1,000,000 Max Cl/Cd: 83.17 at α=8° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-b29root-il-1000000-n5.txt Download as CSV file: xf-b29root-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: B-29 ROOT AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-19.750 -1.2010 0.06783 0.06331 -0.0611 1.0000 0.0388
-19.500 -1.2027 0.06470 0.06012 -0.0621 1.0000 0.0393
-19.250 -1.2038 0.06169 0.05705 -0.0630 1.0000 0.0397
-19.000 -1.2030 0.05896 0.05426 -0.0638 1.0000 0.0402
-18.750 -1.2012 0.05633 0.05158 -0.0644 1.0000 0.0406
-18.500 -1.1994 0.05376 0.04895 -0.0650 1.0000 0.0410
-18.250 -1.1963 0.05136 0.04649 -0.0655 1.0000 0.0414
-18.000 -1.1917 0.04917 0.04424 -0.0659 1.0000 0.0418
-17.750 -1.1873 0.04697 0.04198 -0.0662 1.0000 0.0421
-17.500 -1.1853 0.04458 0.03954 -0.0664 1.0000 0.0425
-17.250 -1.1812 0.04245 0.03737 -0.0666 1.0000 0.0429
-17.000 -1.1762 0.04047 0.03534 -0.0666 1.0000 0.0435
-16.750 -1.1701 0.03862 0.03347 -0.0665 1.0000 0.0442
-16.500 -1.1592 0.03681 0.03161 -0.0672 0.9996 0.0448
-16.250 -1.1426 0.03500 0.02977 -0.0682 0.9557 0.0457
-16.000 -1.0782 0.03324 0.02786 -0.0787 0.9154 0.0466
-15.750 -1.0134 0.03138 0.02583 -0.0896 0.8798 0.0479
-15.500 -0.9765 0.02983 0.02412 -0.0949 0.8462 0.0489
-15.250 -0.9549 0.02863 0.02278 -0.0967 0.8195 0.0497
-15.000 -0.9391 0.02751 0.02155 -0.0971 0.8008 0.0504
-14.750 -0.9241 0.02654 0.02047 -0.0971 0.7845 0.0513
-14.250 -0.8972 0.02470 0.01846 -0.0961 0.7594 0.0521
-14.000 -0.8850 0.02382 0.01749 -0.0953 0.7489 0.0528
-13.750 -0.8743 0.02289 0.01651 -0.0943 0.7401 0.0537
-13.500 -0.8624 0.02210 0.01566 -0.0931 0.7309 0.0542
-13.250 -0.8504 0.02134 0.01485 -0.0919 0.7238 0.0551
-13.000 -0.8375 0.02066 0.01412 -0.0907 0.7165 0.0557
-12.750 -0.8241 0.02005 0.01346 -0.0894 0.7095 0.0565
-12.500 -0.8106 0.01947 0.01282 -0.0880 0.7030 0.0572
-12.250 -0.7963 0.01893 0.01224 -0.0867 0.6960 0.0579
-12.000 -0.7833 0.01838 0.01164 -0.0851 0.6899 0.0588
-11.750 -0.7706 0.01785 0.01107 -0.0834 0.6839 0.0599
-11.500 -0.7570 0.01734 0.01054 -0.0818 0.6787 0.0609
-11.250 -0.7423 0.01691 0.01008 -0.0802 0.6729 0.0620
-11.000 -0.7278 0.01650 0.00963 -0.0785 0.6667 0.0632
-10.750 -0.7121 0.01614 0.00922 -0.0769 0.6617 0.0641
-10.500 -0.6972 0.01574 0.00880 -0.0752 0.6566 0.0654
-10.250 -0.6824 0.01537 0.00841 -0.0734 0.6509 0.0668
-10.000 -0.6670 0.01504 0.00805 -0.0716 0.6452 0.0684
-9.750 -0.6509 0.01473 0.00771 -0.0699 0.6404 0.0703
-9.500 -0.6343 0.01442 0.00739 -0.0683 0.6359 0.0722
-9.250 -0.6184 0.01411 0.00707 -0.0665 0.6308 0.0744
-9.000 -0.6021 0.01385 0.00678 -0.0647 0.6252 0.0768
-8.750 -0.5843 0.01361 0.00652 -0.0631 0.6205 0.0788
-8.500 -0.5676 0.01333 0.00624 -0.0613 0.6157 0.0819
-8.250 -0.5501 0.01309 0.00599 -0.0596 0.6108 0.0847
-8.000 -0.5321 0.01288 0.00576 -0.0580 0.6057 0.0876
-7.750 -0.5149 0.01265 0.00552 -0.0562 0.6009 0.0916
-7.500 -0.4961 0.01244 0.00531 -0.0547 0.5968 0.0953
-7.250 -0.4783 0.01221 0.00509 -0.0529 0.5915 0.0996
-7.000 -0.4595 0.01203 0.00490 -0.0513 0.5865 0.1038
-6.750 -0.4408 0.01186 0.00471 -0.0497 0.5820 0.1079
-6.500 -0.4219 0.01165 0.00452 -0.0481 0.5783 0.1130
-6.250 -0.4029 0.01146 0.00434 -0.0465 0.5733 0.1190
-6.000 -0.3839 0.01128 0.00417 -0.0449 0.5683 0.1253
-5.750 -0.3657 0.01110 0.00399 -0.0431 0.5632 0.1332
-5.250 -0.3273 0.01071 0.00367 -0.0399 0.5558 0.1513
-5.000 -0.3085 0.01051 0.00351 -0.0382 0.5514 0.1625
-4.750 -0.2907 0.01031 0.00334 -0.0363 0.5468 0.1774
-4.500 -0.2741 0.01006 0.00317 -0.0341 0.5424 0.1990
-4.250 -0.2590 0.00974 0.00300 -0.0317 0.5386 0.2297
-4.000 -0.2419 0.00952 0.00287 -0.0297 0.5343 0.2548
-3.750 -0.2240 0.00934 0.00277 -0.0277 0.5300 0.2782
-3.500 -0.2051 0.00922 0.00270 -0.0260 0.5258 0.2958
-3.250 -0.1853 0.00911 0.00263 -0.0243 0.5224 0.3117
-3.000 -0.1646 0.00903 0.00259 -0.0229 0.5188 0.3253
-2.750 -0.1451 0.00893 0.00254 -0.0212 0.5145 0.3418
-2.500 -0.1259 0.00884 0.00250 -0.0194 0.5099 0.3591
-2.250 -0.1051 0.00879 0.00246 -0.0180 0.5053 0.3714
-2.000 -0.0817 0.00873 0.00243 -0.0170 0.5023 0.3832
-1.750 -0.0593 0.00865 0.00240 -0.0159 0.4988 0.3956
-1.500 -0.0371 0.00858 0.00237 -0.0148 0.4949 0.4099
-1.250 -0.0150 0.00853 0.00235 -0.0136 0.4910 0.4252
-0.750 0.0293 0.00842 0.00232 -0.0112 0.4836 0.4564
-0.500 0.0508 0.00833 0.00231 -0.0099 0.4797 0.4775
-0.250 0.0736 0.00829 0.00230 -0.0089 0.4759 0.4904
0.000 0.0970 0.00829 0.00230 -0.0080 0.4721 0.5006
0.250 0.1195 0.00828 0.00231 -0.0069 0.4683 0.5110
0.500 0.1435 0.00826 0.00232 -0.0061 0.4654 0.5225
0.750 0.1669 0.00823 0.00233 -0.0051 0.4619 0.5329
1.000 0.1906 0.00823 0.00234 -0.0043 0.4580 0.5438
1.250 0.2128 0.00822 0.00236 -0.0031 0.4543 0.5557
1.500 0.2350 0.00823 0.00239 -0.0020 0.4505 0.5684
1.750 0.2575 0.00821 0.00241 -0.0009 0.4476 0.5830
2.000 0.2801 0.00819 0.00244 0.0002 0.4442 0.5963
2.250 0.3031 0.00819 0.00247 0.0012 0.4407 0.6091
2.500 0.3245 0.00819 0.00251 0.0025 0.4372 0.6232
2.750 0.3450 0.00821 0.00256 0.0040 0.4333 0.6372
3.000 0.3661 0.00822 0.00261 0.0054 0.4300 0.6527
3.250 0.3881 0.00821 0.00265 0.0066 0.4274 0.6673
3.500 0.4092 0.00820 0.00270 0.0080 0.4243 0.6807
3.750 0.4301 0.00823 0.00276 0.0094 0.4210 0.6941
4.000 0.4491 0.00825 0.00282 0.0112 0.4173 0.7096
4.250 0.4665 0.00828 0.00290 0.0133 0.4137 0.7250
4.500 0.4853 0.00828 0.00296 0.0151 0.4115 0.7402
4.750 0.5030 0.00828 0.00301 0.0172 0.4091 0.7551
5.000 0.5189 0.00828 0.00308 0.0196 0.4063 0.7714
5.250 0.5348 0.00830 0.00317 0.0221 0.4032 0.7889
5.500 0.5506 0.00837 0.00329 0.0245 0.3999 0.8050
5.750 0.5656 0.00845 0.00343 0.0270 0.3964 0.8239
6.000 0.5846 0.00851 0.00357 0.0287 0.3939 0.8415
6.250 0.6063 0.00858 0.00371 0.0298 0.3915 0.8593
6.500 0.6295 0.00867 0.00386 0.0306 0.3887 0.8763
6.750 0.6567 0.00879 0.00405 0.0305 0.3854 0.8924
7.000 0.6859 0.00898 0.00427 0.0298 0.3807 0.9046
7.250 0.7157 0.00918 0.00448 0.0290 0.3754 0.9160
7.500 0.7523 0.00936 0.00469 0.0268 0.3700 0.9242
7.750 0.7814 0.00959 0.00492 0.0261 0.3645 0.9326
8.000 0.8217 0.00988 0.00520 0.0229 0.3562 0.9368
8.250 0.8524 0.01026 0.00553 0.0215 0.3444 0.9427
8.500 0.8766 0.01058 0.00584 0.0216 0.3338 0.9493
8.750 0.9089 0.01101 0.00624 0.0198 0.3238 0.9527
9.000 0.9361 0.01139 0.00661 0.0192 0.3156 0.9575
9.250 0.9525 0.01186 0.00706 0.0206 0.3081 0.9646
9.500 0.9814 0.01229 0.00749 0.0194 0.3004 0.9667
9.750 1.0046 0.01292 0.00808 0.0191 0.2897 0.9695
10.000 1.0252 0.01357 0.00870 0.0192 0.2797 0.9729
10.250 1.0365 0.01424 0.00936 0.0210 0.2708 0.9785
10.500 1.0587 0.01511 0.01019 0.0202 0.2587 0.9801
10.750 1.0773 0.01619 0.01120 0.0198 0.2432 0.9821
11.000 1.0920 0.01745 0.01239 0.0196 0.2260 0.9847
11.250 1.1028 0.01891 0.01378 0.0199 0.2082 0.9878
11.500 1.1060 0.02077 0.01555 0.0209 0.1886 0.9912
11.750 1.1140 0.02264 0.01736 0.0209 0.1726 0.9937
12.000 1.1259 0.02443 0.01910 0.0202 0.1596 0.9959
12.250 1.1394 0.02617 0.02081 0.0193 0.1489 0.9977
12.500 1.1507 0.02812 0.02273 0.0184 0.1379 0.9990
12.750 1.1622 0.03003 0.02462 0.0176 0.1292 0.9999
13.000 1.1585 0.03185 0.02642 0.0198 0.1221 1.0000
13.250 1.1538 0.03375 0.02830 0.0220 0.1139 1.0000
13.500 1.1522 0.03555 0.03011 0.0238 0.1100 1.0000
13.750 1.1489 0.03756 0.03212 0.0255 0.1030 1.0000
14.000 1.1469 0.03954 0.03409 0.0270 0.0974 1.0000
14.250 1.1416 0.04191 0.03645 0.0285 0.0909 1.0000
14.500 1.1422 0.04386 0.03841 0.0296 0.0868 1.0000
14.750 1.1394 0.04616 0.04070 0.0308 0.0818 1.0000
15.000 1.1395 0.04827 0.04283 0.0317 0.0782 1.0000
15.250 1.1382 0.05054 0.04510 0.0326 0.0744 1.0000
15.500 1.1401 0.05261 0.04721 0.0333 0.0723 1.0000
15.750 1.1421 0.05467 0.04928 0.0339 0.0696 1.0000
16.000 1.1423 0.05698 0.05162 0.0344 0.0679 1.0000
16.250 1.1450 0.05905 0.05371 0.0349 0.0659 1.0000
16.500 1.1462 0.06134 0.05603 0.0353 0.0639 1.0000
16.750 1.1483 0.06355 0.05827 0.0356 0.0624 1.0000
17.000 1.1485 0.06600 0.06075 0.0359 0.0607 1.0000
17.250 1.1516 0.06817 0.06296 0.0361 0.0595 1.0000
17.500 1.1553 0.07029 0.06510 0.0362 0.0583 1.0000
17.750 1.1560 0.07280 0.06765 0.0363 0.0569 1.0000
18.000 1.1581 0.07515 0.07003 0.0363 0.0556 1.0000
18.250 1.1579 0.07779 0.07270 0.0363 0.0542 1.0000
18.500 1.1609 0.08008 0.07504 0.0362 0.0535 1.0000
18.750 1.1645 0.08232 0.07730 0.0361 0.0523 1.0000
19.000 1.1650 0.08496 0.07999 0.0359 0.0512 1.0000
19.250 1.1663 0.08751 0.08256 0.0356 0.0500 1.0000
|
Polar data table (+)
Polar graphs
<< Back to B-29 ROOT AIRFOIL (b29root-il)