BOEING 707 .19 SPAN AIRFOIL (b707b-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: BOEING 707 .19 SPAN AIRFOIL (b707b-il) Reynolds number: 100,000 Max Cl/Cd: 31.16 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-b707b-il-100000-n5.txt Download as CSV file: xf-b707b-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: BOEING 707 .19 SPAN AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.000 -0.7178 0.09050 0.08565 -0.0135 1.0000 0.0408
-11.750 -0.7423 0.08269 0.07776 -0.0184 1.0000 0.0399
-11.500 -0.7713 0.07591 0.07086 -0.0221 1.0000 0.0398
-11.250 -0.7968 0.07051 0.06532 -0.0237 1.0000 0.0392
-11.000 -0.8194 0.06621 0.06085 -0.0236 1.0000 0.0390
-10.750 -0.8375 0.06276 0.05724 -0.0222 1.0000 0.0391
-10.500 -0.8524 0.05973 0.05403 -0.0197 1.0000 0.0392
-10.250 -0.8633 0.05688 0.05098 -0.0170 1.0000 0.0393
-10.000 -0.8679 0.05394 0.04781 -0.0148 1.0000 0.0394
-9.500 -0.8578 0.04764 0.04072 -0.0124 0.8577 0.0387
-9.250 -0.8504 0.04496 0.03757 -0.0104 0.8323 0.0383
-9.000 -0.8406 0.04240 0.03457 -0.0085 0.8175 0.0379
-8.750 -0.8277 0.03999 0.03173 -0.0068 0.8073 0.0375
-8.500 -0.8114 0.03772 0.02907 -0.0054 0.7992 0.0372
-8.250 -0.7921 0.03571 0.02670 -0.0044 0.7930 0.0369
-8.000 -0.7702 0.03386 0.02455 -0.0037 0.7878 0.0366
-7.750 -0.7463 0.03217 0.02261 -0.0033 0.7833 0.0364
-7.500 -0.7214 0.03066 0.02090 -0.0030 0.7794 0.0363
-7.250 -0.6958 0.02931 0.01936 -0.0027 0.7762 0.0362
-7.000 -0.6699 0.02809 0.01799 -0.0025 0.7734 0.0361
-6.750 -0.6444 0.02698 0.01679 -0.0023 0.7703 0.0361
-6.500 -0.6197 0.02598 0.01571 -0.0019 0.7671 0.0361
-6.250 -0.5963 0.02506 0.01473 -0.0013 0.7641 0.0362
-6.000 -0.5741 0.02425 0.01386 -0.0005 0.7611 0.0362
-5.750 -0.5529 0.02351 0.01306 0.0006 0.7585 0.0365
-5.500 -0.5322 0.02284 0.01232 0.0016 0.7558 0.0367
-5.250 -0.5115 0.02222 0.01164 0.0027 0.7528 0.0369
-5.000 -0.4907 0.02166 0.01101 0.0038 0.7500 0.0374
-4.750 -0.4694 0.02116 0.01043 0.0049 0.7474 0.0378
-4.500 -0.4476 0.02071 0.00988 0.0059 0.7450 0.0385
-4.250 -0.4253 0.02030 0.00939 0.0068 0.7430 0.0393
-4.000 -0.4024 0.01994 0.00894 0.0077 0.7412 0.0405
-3.750 -0.3787 0.01961 0.00854 0.0084 0.7394 0.0421
-3.500 -0.3547 0.01927 0.00822 0.0090 0.7373 0.0457
-3.250 -0.3303 0.01896 0.00792 0.0095 0.7348 0.0537
-3.000 -0.3057 0.01869 0.00762 0.0101 0.7322 0.0736
-2.750 -0.2854 0.01793 0.00722 0.0112 0.7298 0.1435
-2.500 -0.2729 0.01649 0.00680 0.0133 0.7276 0.3776
-2.250 -0.2519 0.01603 0.00663 0.0145 0.7254 0.4456
-2.000 -0.2316 0.01561 0.00666 0.0161 0.7227 0.5264
-1.750 -0.2078 0.01546 0.00669 0.0171 0.7193 0.5882
-1.500 -0.1847 0.01533 0.00679 0.0184 0.7153 0.6493
-1.250 -0.1606 0.01528 0.00690 0.0198 0.7113 0.6972
-1.000 -0.1345 0.01527 0.00691 0.0207 0.7063 0.7236
-0.750 -0.1083 0.01525 0.00694 0.0214 0.6983 0.7466
-0.500 -0.0823 0.01527 0.00698 0.0227 0.6905 0.7770
-0.250 -0.0546 0.01533 0.00712 0.0235 0.6808 0.8063
0.000 -0.0239 0.01548 0.00730 0.0240 0.6726 0.8329
0.250 0.0051 0.01554 0.00738 0.0244 0.6643 0.8500
0.500 0.0371 0.01554 0.00735 0.0240 0.6540 0.8592
0.750 0.0673 0.01549 0.00723 0.0240 0.6412 0.8691
1.000 0.0962 0.01540 0.00711 0.0242 0.6257 0.8792
1.250 0.1275 0.01533 0.00705 0.0238 0.6077 0.8880
1.500 0.1605 0.01529 0.00709 0.0229 0.5861 0.8960
1.750 0.1927 0.01535 0.00740 0.0217 0.4812 0.9051
2.000 0.2148 0.01550 0.00653 0.0235 0.3903 0.9147
2.250 0.2480 0.01595 0.00684 0.0222 0.3548 0.9218
2.500 0.2799 0.01630 0.00710 0.0211 0.3269 0.9302
2.750 0.3104 0.01666 0.00735 0.0202 0.2992 0.9391
3.000 0.3461 0.01706 0.00759 0.0182 0.2747 0.9451
3.250 0.3790 0.01737 0.00784 0.0168 0.2544 0.9532
3.500 0.4121 0.01763 0.00808 0.0154 0.2281 0.9619
3.750 0.4485 0.01794 0.00823 0.0133 0.1752 0.9684
4.000 0.4817 0.01844 0.00846 0.0116 0.1443 0.9760
4.250 0.5148 0.01884 0.00878 0.0101 0.1273 0.9834
4.500 0.5498 0.01922 0.00909 0.0082 0.1180 0.9893
4.750 0.5838 0.01959 0.00945 0.0064 0.1124 0.9953
5.000 0.6151 0.02003 0.00981 0.0051 0.1075 1.0000
5.250 0.6316 0.02039 0.01018 0.0067 0.1036 1.0000
5.500 0.6474 0.02083 0.01060 0.0084 0.0990 1.0000
5.750 0.6625 0.02138 0.01107 0.0102 0.0953 1.0000
6.000 0.6788 0.02182 0.01155 0.0118 0.0927 1.0000
6.250 0.6949 0.02230 0.01207 0.0136 0.0905 1.0000
6.500 0.7107 0.02281 0.01262 0.0153 0.0893 1.0000
6.750 0.7265 0.02336 0.01323 0.0171 0.0884 1.0000
7.000 0.7422 0.02395 0.01384 0.0188 0.0874 1.0000
7.250 0.7577 0.02458 0.01450 0.0206 0.0861 1.0000
7.500 0.7726 0.02537 0.01524 0.0223 0.0843 1.0000
7.750 0.7891 0.02604 0.01595 0.0239 0.0831 1.0000
8.000 0.8062 0.02665 0.01668 0.0254 0.0823 1.0000
8.250 0.8235 0.02729 0.01742 0.0269 0.0815 1.0000
8.500 0.8407 0.02797 0.01821 0.0283 0.0807 1.0000
8.750 0.8577 0.02868 0.01903 0.0297 0.0797 1.0000
9.000 0.8744 0.02942 0.01988 0.0311 0.0785 1.0000
9.250 0.8904 0.03017 0.02073 0.0326 0.0771 1.0000
9.500 0.9061 0.03097 0.02160 0.0340 0.0757 1.0000
9.750 0.9214 0.03184 0.02250 0.0353 0.0739 1.0000
10.000 0.9375 0.03292 0.02356 0.0365 0.0722 1.0000
10.250 0.9500 0.03363 0.02454 0.0382 0.0710 1.0000
10.500 0.9629 0.03449 0.02561 0.0399 0.0700 1.0000
10.750 0.9746 0.03541 0.02675 0.0415 0.0688 1.0000
11.000 0.9852 0.03640 0.02795 0.0433 0.0675 1.0000
11.250 0.9937 0.03744 0.02919 0.0452 0.0663 1.0000
11.500 0.9998 0.03849 0.03041 0.0473 0.0650 1.0000
11.750 1.0049 0.03955 0.03159 0.0492 0.0634 1.0000
12.000 1.0099 0.04060 0.03263 0.0508 0.0615 1.0000
12.250 1.0068 0.04225 0.03470 0.0523 0.0591 1.0000
12.500 1.0061 0.04407 0.03681 0.0533 0.0565 1.0000
12.750 1.0058 0.04591 0.03887 0.0539 0.0540 1.0000
13.000 1.0062 0.04769 0.04079 0.0543 0.0520 1.0000
13.250 0.9978 0.05109 0.04458 0.0543 0.0489 1.0000
13.500 0.9874 0.05472 0.04849 0.0538 0.0465 1.0000
13.750 0.9749 0.05872 0.05271 0.0528 0.0446 1.0000
14.000 0.9570 0.06373 0.05791 0.0508 0.0432 1.0000
14.250 0.9296 0.07080 0.06517 0.0471 0.0435 1.0000
14.500 0.8441 0.09105 0.08564 0.0341 0.0492 1.0000
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