BOEING 707 .54 SPAN AIRFOIL (b707d-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: BOEING 707 .54 SPAN AIRFOIL (b707d-il) Reynolds number: 100,000 Max Cl/Cd: 47.78 at α=4° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-b707d-il-100000-n5.txt Download as CSV file: xf-b707d-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: BOEING 707 .54 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
------ -------- --------- --------- -------- -------- --------
-8.750 -0.4632 0.09040 0.08555 -0.0332 1.0000 0.0460
-8.500 -0.4729 0.08675 0.08195 -0.0371 1.0000 0.0463
-8.250 -0.4814 0.08379 0.07895 -0.0392 1.0000 0.0467
-8.000 -0.4856 0.08096 0.07603 -0.0401 1.0000 0.0469
-7.750 -0.4892 0.07833 0.07327 -0.0402 1.0000 0.0471
-7.500 -0.4895 0.07562 0.07042 -0.0395 1.0000 0.0472
-7.250 -0.4852 0.06863 0.06366 -0.0390 1.0000 0.0484
-7.000 -0.4808 0.06510 0.06019 -0.0378 1.0000 0.0495
-6.750 -0.4779 0.06216 0.05723 -0.0363 1.0000 0.0509
-6.500 -0.4760 0.05952 0.05454 -0.0346 1.0000 0.0524
-6.250 -0.4749 0.05707 0.05200 -0.0326 1.0000 0.0545
-5.750 -0.4604 0.05151 0.04600 -0.0312 0.9957 0.0639
-5.500 -0.4297 0.05063 0.04441 -0.0339 0.9869 0.0759
-5.250 -0.3578 0.02813 0.02258 -0.0418 0.9678 0.0834
-4.750 -0.3400 0.03742 0.03039 -0.0377 0.9686 0.0447
-4.500 -0.3120 0.03412 0.02676 -0.0386 0.9618 0.0401
-4.250 -0.2753 0.03158 0.02344 -0.0390 0.9569 0.0346
-4.000 -0.2436 0.03068 0.02219 -0.0395 0.9499 0.0334
-3.750 -0.2109 0.02783 0.01906 -0.0409 0.9458 0.0328
-3.500 -0.1821 0.02619 0.01708 -0.0411 0.9385 0.0340
-3.250 -0.1500 0.02392 0.01462 -0.0425 0.9341 0.0365
-3.000 -0.1203 0.02260 0.01307 -0.0426 0.9271 0.0363
-2.750 -0.0868 0.02130 0.01161 -0.0435 0.9222 0.0361
-2.500 -0.0566 0.02020 0.01041 -0.0438 0.9159 0.0362
-2.250 -0.0259 0.01918 0.00933 -0.0443 0.9100 0.0367
-2.000 0.0039 0.01829 0.00843 -0.0446 0.9043 0.0375
-1.750 0.0298 0.01760 0.00774 -0.0442 0.8969 0.0387
-1.500 0.0595 0.01700 0.00706 -0.0446 0.8918 0.0410
-1.250 0.0841 0.01668 0.00663 -0.0440 0.8834 0.0465
-1.000 0.1136 0.01616 0.00600 -0.0443 0.8782 0.0518
-0.750 0.1387 0.01591 0.00565 -0.0437 0.8701 0.0590
-0.500 0.1650 0.01447 0.00523 -0.0441 0.8648 0.3660
-0.250 0.2134 0.01301 0.00564 -0.0458 0.8639 0.9254
0.000 0.3111 0.01296 0.00544 -0.0598 0.8655 0.9973
0.250 0.3370 0.01298 0.00537 -0.0599 0.8568 1.0000
0.750 0.3818 0.01307 0.00534 -0.0582 0.8401 1.0000
1.000 0.4044 0.01314 0.00536 -0.0574 0.8318 1.0000
1.250 0.4280 0.01313 0.00528 -0.0563 0.8209 1.0000
1.500 0.4487 0.01309 0.00520 -0.0546 0.8044 1.0000
1.750 0.4695 0.01304 0.00510 -0.0528 0.7865 1.0000
2.000 0.4915 0.01304 0.00507 -0.0513 0.7712 1.0000
2.250 0.5139 0.01308 0.00509 -0.0500 0.7574 1.0000
2.500 0.5362 0.01311 0.00515 -0.0487 0.7420 1.0000
2.750 0.5584 0.01312 0.00515 -0.0473 0.7240 1.0000
3.000 0.5795 0.01311 0.00511 -0.0455 0.6987 1.0000
3.250 0.5990 0.01308 0.00494 -0.0432 0.6565 1.0000
3.500 0.6182 0.01316 0.00484 -0.0410 0.6022 1.0000
3.750 0.6380 0.01337 0.00491 -0.0392 0.5424 1.0000
4.000 0.6570 0.01375 0.00499 -0.0373 0.4709 1.0000
4.250 0.6746 0.01432 0.00524 -0.0354 0.4031 1.0000
4.500 0.6921 0.01499 0.00564 -0.0337 0.3457 1.0000
5.000 0.7293 0.01628 0.00666 -0.0308 0.2598 1.0000
5.250 0.7493 0.01685 0.00718 -0.0296 0.2297 1.0000
5.500 0.7684 0.01751 0.00774 -0.0283 0.1899 1.0000
5.750 0.7869 0.01827 0.00835 -0.0270 0.1417 1.0000
6.000 0.8006 0.01963 0.00919 -0.0251 0.0678 1.0000
6.250 0.8174 0.02076 0.01031 -0.0234 0.0550 1.0000
6.500 0.8342 0.02190 0.01163 -0.0217 0.0483 1.0000
6.750 0.8509 0.02301 0.01283 -0.0201 0.0401 1.0000
7.000 0.8706 0.02375 0.01367 -0.0190 0.0316 1.0000
7.250 0.8878 0.02475 0.01479 -0.0175 0.0270 1.0000
7.500 0.9014 0.02611 0.01621 -0.0156 0.0245 1.0000
7.750 0.9138 0.02770 0.01795 -0.0134 0.0231 1.0000
8.000 0.9282 0.02939 0.01983 -0.0115 0.0220 1.0000
8.250 0.9450 0.03124 0.02183 -0.0100 0.0208 1.0000
8.500 0.9618 0.03303 0.02374 -0.0088 0.0191 1.0000
8.750 0.9781 0.03602 0.02681 -0.0079 0.0174 1.0000
9.000 0.9943 0.03818 0.02931 -0.0065 0.0167 1.0000
9.250 1.0082 0.04079 0.03230 -0.0049 0.0163 1.0000
9.500 1.0179 0.04360 0.03549 -0.0030 0.0161 1.0000
9.750 1.0226 0.04659 0.03888 -0.0007 0.0159 1.0000
10.000 1.0227 0.04958 0.04223 0.0018 0.0158 1.0000
10.250 1.0169 0.05249 0.04546 0.0048 0.0158 1.0000
10.500 1.0070 0.05551 0.04882 0.0076 0.0158 1.0000
10.750 0.9946 0.05876 0.05234 0.0098 0.0158 1.0000
11.000 0.9806 0.06229 0.05611 0.0111 0.0159 1.0000
11.250 0.9644 0.06632 0.06037 0.0115 0.0159 1.0000
11.500 0.9467 0.07089 0.06515 0.0108 0.0160 1.0000
11.750 0.9286 0.07601 0.07045 0.0090 0.0160 1.0000
12.000 0.9113 0.08162 0.07622 0.0062 0.0162 1.0000
12.250 0.8909 0.08864 0.08334 0.0019 0.0162 1.0000
12.500 0.8741 0.09598 0.09078 -0.0029 0.0165 1.0000
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Polar data table (+)
Polar graphs
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