BOEING 707 .40 SPAN AIRFOIL (b707c-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: BOEING 707 .40 SPAN AIRFOIL (b707c-il) Reynolds number: 100,000 Max Cl/Cd: 34.27 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-b707c-il-100000-n5.txt Download as CSV file: xf-b707c-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: BOEING 707 .40 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
------ -------- --------- --------- -------- -------- --------
-9.250 -0.4950 0.09558 0.09026 -0.0372 1.0000 0.0412
-9.000 -0.5043 0.09267 0.08734 -0.0376 1.0000 0.0413
-8.750 -0.5114 0.08974 0.08438 -0.0377 1.0000 0.0413
-8.500 -0.5165 0.08683 0.08142 -0.0376 1.0000 0.0413
-8.250 -0.5205 0.08397 0.07847 -0.0370 1.0000 0.0414
-8.000 -0.5221 0.08116 0.07556 -0.0362 1.0000 0.0414
-7.750 -0.5121 0.07420 0.06885 -0.0361 1.0000 0.0423
-7.500 -0.5082 0.07069 0.06536 -0.0351 1.0000 0.0428
-7.250 -0.5037 0.06745 0.06218 -0.0339 1.0000 0.0442
-7.000 -0.5011 0.06461 0.05929 -0.0328 1.0000 0.0451
-6.750 -0.4980 0.06187 0.05649 -0.0316 1.0000 0.0470
-6.500 -0.4939 0.05922 0.05373 -0.0302 1.0000 0.0486
-6.250 -0.4902 0.05877 0.05272 -0.0278 1.0000 0.0529
-6.000 -0.4851 0.05511 0.04894 -0.0262 1.0000 0.0538
-5.750 -0.4762 0.05151 0.04541 -0.0250 1.0000 0.0548
-5.500 -0.4667 0.04883 0.04270 -0.0234 1.0000 0.0561
-5.250 -0.4564 0.04651 0.04028 -0.0217 1.0000 0.0583
-4.750 -0.4160 0.04157 0.03487 -0.0219 0.9939 0.0673
-4.500 -0.3828 0.03908 0.03212 -0.0245 0.9857 0.0784
-4.000 -0.3027 0.03372 0.02582 -0.0263 0.9702 0.0398
-3.750 -0.2712 0.03095 0.02285 -0.0277 0.9618 0.0365
-3.500 -0.2374 0.02874 0.02032 -0.0284 0.9532 0.0334
-3.250 -0.2014 0.02711 0.01818 -0.0288 0.9441 0.0306
-2.750 -0.1306 0.02486 0.01545 -0.0309 0.9233 0.0293
-2.500 -0.0988 0.02322 0.01369 -0.0314 0.9090 0.0292
-2.250 -0.0655 0.02142 0.01183 -0.0322 0.8944 0.0301
-2.000 -0.0322 0.01999 0.01045 -0.0333 0.8784 0.0327
-1.750 0.0002 0.01898 0.00941 -0.0339 0.8596 0.0348
-1.500 0.0327 0.01801 0.00843 -0.0343 0.8409 0.0355
-1.250 0.0621 0.01719 0.00758 -0.0342 0.8205 0.0366
-1.000 0.0910 0.01654 0.00685 -0.0341 0.8010 0.0379
-0.750 0.1185 0.01606 0.00622 -0.0337 0.7810 0.0397
-0.500 0.1462 0.01563 0.00555 -0.0332 0.7514 0.0423
-0.250 0.1720 0.01526 0.00486 -0.0323 0.7102 0.0499
0.000 0.1963 0.01498 0.00438 -0.0311 0.6656 0.0745
0.250 0.2115 0.01323 0.00415 -0.0291 0.6385 0.5521
0.500 0.2318 0.01271 0.00450 -0.0258 0.6208 0.8378
0.750 0.2682 0.01284 0.00453 -0.0267 0.5929 0.8925
1.000 0.3199 0.01305 0.00463 -0.0309 0.5541 0.9492
1.250 0.3790 0.01357 0.00451 -0.0372 0.4317 0.9853
1.500 0.4062 0.01493 0.00465 -0.0382 0.2258 0.9952
1.750 0.4325 0.01534 0.00486 -0.0385 0.2017 1.0000
2.000 0.4515 0.01548 0.00497 -0.0370 0.1777 1.0000
2.250 0.4652 0.01629 0.00525 -0.0349 0.0601 1.0000
2.500 0.4841 0.01656 0.00544 -0.0334 0.0556 1.0000
2.750 0.5038 0.01681 0.00565 -0.0320 0.0538 1.0000
3.000 0.5238 0.01707 0.00590 -0.0307 0.0525 1.0000
3.250 0.5440 0.01736 0.00619 -0.0293 0.0515 1.0000
3.500 0.5643 0.01767 0.00652 -0.0280 0.0507 1.0000
3.750 0.5847 0.01799 0.00686 -0.0267 0.0501 1.0000
4.000 0.6051 0.01835 0.00724 -0.0255 0.0492 1.0000
4.250 0.6250 0.01879 0.00768 -0.0242 0.0476 1.0000
4.500 0.6449 0.01925 0.00818 -0.0229 0.0465 1.0000
4.750 0.6652 0.01970 0.00870 -0.0216 0.0458 1.0000
5.000 0.6856 0.02015 0.00921 -0.0204 0.0448 1.0000
5.250 0.7057 0.02063 0.00977 -0.0192 0.0438 1.0000
5.500 0.7254 0.02117 0.01039 -0.0179 0.0424 1.0000
5.750 0.7446 0.02176 0.01106 -0.0166 0.0414 1.0000
6.000 0.7632 0.02241 0.01183 -0.0152 0.0406 1.0000
6.250 0.7813 0.02314 0.01265 -0.0137 0.0399 1.0000
6.500 0.7987 0.02396 0.01352 -0.0122 0.0382 1.0000
6.750 0.8148 0.02497 0.01454 -0.0107 0.0360 1.0000
7.000 0.8305 0.02628 0.01586 -0.0091 0.0343 1.0000
7.250 0.8502 0.02719 0.01695 -0.0079 0.0325 1.0000
7.500 0.8697 0.02837 0.01825 -0.0067 0.0308 1.0000
7.750 0.8895 0.02974 0.01971 -0.0057 0.0293 1.0000
8.000 0.9097 0.03125 0.02128 -0.0049 0.0281 1.0000
8.250 0.9299 0.03293 0.02304 -0.0041 0.0273 1.0000
8.500 0.9505 0.03500 0.02519 -0.0035 0.0265 1.0000
8.750 0.9692 0.03708 0.02759 -0.0024 0.0260 1.0000
9.000 0.9850 0.03934 0.03019 -0.0010 0.0255 1.0000
9.250 0.9978 0.04173 0.03292 0.0007 0.0251 1.0000
9.500 1.0071 0.04418 0.03573 0.0026 0.0246 1.0000
9.750 1.0132 0.04651 0.03841 0.0047 0.0238 1.0000
10.000 1.0164 0.04907 0.04126 0.0070 0.0235 1.0000
10.250 1.0175 0.05132 0.04376 0.0092 0.0229 1.0000
10.500 1.0129 0.05382 0.04650 0.0119 0.0227 1.0000
10.750 1.0044 0.05647 0.04938 0.0147 0.0226 1.0000
11.000 0.9917 0.05956 0.05272 0.0169 0.0226 1.0000
11.250 0.9761 0.06307 0.05646 0.0183 0.0226 1.0000
11.500 0.9577 0.06717 0.06079 0.0186 0.0226 1.0000
11.750 0.9358 0.07218 0.06603 0.0175 0.0228 1.0000
12.000 0.9119 0.07815 0.07220 0.0149 0.0229 1.0000
12.250 0.8845 0.08565 0.07988 0.0106 0.0232 1.0000
12.500 0.8537 0.09519 0.08958 0.0043 0.0235 1.0000
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Polar data table (+)
Polar graphs
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