BOEING 707 .19 SPAN AIRFOIL (b707b-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: BOEING 707 .19 SPAN AIRFOIL (b707b-il) Reynolds number: 500,000 Max Cl/Cd: 54.88 at α=9° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-b707b-il-500000-n5.txt Download as CSV file: xf-b707b-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.250 -0.9506 0.07920 0.07577 -0.0193 0.7364 0.0054
-15.000 -0.9905 0.06867 0.06495 -0.0256 0.7286 0.0054
-14.750 -1.0187 0.06145 0.05747 -0.0290 0.7176 0.0054
-14.500 -1.0355 0.05652 0.05232 -0.0306 0.7071 0.0054
-14.250 -1.0467 0.05264 0.04825 -0.0313 0.6986 0.0054
-14.000 -1.0558 0.04927 0.04470 -0.0315 0.6915 0.0055
-13.750 -1.0652 0.04602 0.04124 -0.0310 0.6859 0.0055
-13.500 -1.0648 0.04408 0.03919 -0.0303 0.6803 0.0056
-13.000 -1.0692 0.03977 0.03455 -0.0278 0.6724 0.0057
-12.750 -1.0663 0.03827 0.03294 -0.0262 0.6690 0.0058
-12.500 -1.0541 0.03811 0.03282 -0.0251 0.6654 0.0062
-12.250 -1.0320 0.03958 0.03449 -0.0245 0.6616 0.0066
-11.750 -1.0155 0.03872 0.03365 -0.0211 0.6556 0.0069
-11.500 -1.0428 0.03018 0.02392 -0.0159 0.6550 0.0101
-11.250 -1.0319 0.02893 0.02245 -0.0140 0.6526 0.0107
-11.000 -1.0168 0.02839 0.02168 -0.0122 0.6499 0.0114
-10.750 -1.0035 0.02798 0.02114 -0.0102 0.6475 0.0116
-10.500 -0.9918 0.02736 0.02043 -0.0080 0.6458 0.0119
-10.250 -0.9793 0.02670 0.01972 -0.0059 0.6440 0.0121
-10.000 -0.9651 0.02631 0.01931 -0.0040 0.6421 0.0125
-9.750 -0.9483 0.02578 0.01872 -0.0026 0.6402 0.0129
-9.500 -0.9304 0.02527 0.01815 -0.0013 0.6388 0.0133
-9.250 -0.9118 0.02478 0.01757 0.0000 0.6371 0.0138
-9.000 -0.8926 0.02440 0.01707 0.0012 0.6356 0.0143
-8.750 -0.8731 0.02414 0.01670 0.0025 0.6343 0.0148
-8.500 -0.8539 0.02413 0.01653 0.0039 0.6330 0.0151
-8.250 -0.8322 0.02250 0.01485 0.0044 0.6315 0.0156
-8.000 -0.8107 0.02165 0.01398 0.0051 0.6298 0.0161
-7.750 -0.7888 0.02100 0.01328 0.0059 0.6285 0.0163
-7.500 -0.7664 0.02037 0.01260 0.0067 0.6274 0.0166
-7.250 -0.7440 0.01981 0.01199 0.0075 0.6264 0.0169
-7.000 -0.7212 0.01930 0.01143 0.0082 0.6255 0.0173
-6.750 -0.6980 0.01883 0.01091 0.0089 0.6246 0.0178
-6.500 -0.6744 0.01843 0.01046 0.0096 0.6238 0.0183
-6.250 -0.6503 0.01816 0.01013 0.0103 0.6228 0.0187
-6.000 -0.6259 0.01795 0.00985 0.0109 0.6217 0.0190
-5.500 -0.5787 0.01681 0.00868 0.0123 0.6190 0.0190
-5.250 -0.5557 0.01622 0.00807 0.0131 0.6175 0.0189
-5.000 -0.5329 0.01567 0.00751 0.0140 0.6158 0.0189
-4.750 -0.5099 0.01519 0.00701 0.0148 0.6140 0.0188
-4.500 -0.4870 0.01474 0.00653 0.0157 0.6116 0.0188
-4.250 -0.4639 0.01432 0.00607 0.0166 0.6076 0.0187
-4.000 -0.4402 0.01390 0.00566 0.0174 0.6039 0.0187
-3.750 -0.4162 0.01353 0.00528 0.0181 0.6001 0.0186
-3.500 -0.3920 0.01318 0.00491 0.0188 0.5972 0.0186
-3.250 -0.3676 0.01287 0.00457 0.0195 0.5929 0.0185
-3.000 -0.3427 0.01255 0.00425 0.0201 0.5856 0.0185
-2.750 -0.3175 0.01227 0.00394 0.0207 0.5778 0.0185
-2.500 -0.2920 0.01201 0.00367 0.0211 0.5701 0.0184
-2.250 -0.2662 0.01179 0.00342 0.0216 0.5598 0.0184
-2.000 -0.2425 0.01180 0.00308 0.0223 0.4294 0.0184
-1.750 -0.2185 0.01199 0.00306 0.0229 0.3674 0.0184
-1.500 -0.1937 0.01208 0.00297 0.0234 0.3055 0.0184
-1.000 -0.1420 0.01203 0.00275 0.0241 0.2706 0.0184
-0.750 -0.1158 0.01199 0.00267 0.0244 0.2631 0.0184
-0.500 -0.0894 0.01195 0.00259 0.0247 0.2553 0.0185
-0.250 -0.0631 0.01195 0.00254 0.0250 0.2460 0.0186
0.000 -0.0364 0.01191 0.00248 0.0252 0.2369 0.0187
0.250 -0.0099 0.01190 0.00244 0.0255 0.2249 0.0189
0.500 0.0150 0.01211 0.00240 0.0259 0.1615 0.0193
0.750 0.0407 0.01223 0.00243 0.0262 0.1373 0.0200
1.000 0.0655 0.01245 0.00249 0.0267 0.0916 0.0220
1.250 0.0908 0.01243 0.00254 0.0271 0.0846 0.0670
1.500 0.1138 0.01210 0.00252 0.0279 0.0824 0.1880
2.000 0.1483 0.01067 0.00246 0.0314 0.0788 0.5827
2.250 0.1679 0.01045 0.00261 0.0330 0.0763 0.6748
2.500 0.1870 0.01029 0.00281 0.0349 0.0734 0.7559
2.750 0.2116 0.01034 0.00296 0.0357 0.0720 0.7819
3.000 0.2372 0.01039 0.00308 0.0361 0.0709 0.8004
3.250 0.2626 0.01045 0.00322 0.0367 0.0689 0.8229
3.500 0.2885 0.01055 0.00337 0.0371 0.0674 0.8403
3.750 0.3146 0.01067 0.00354 0.0374 0.0659 0.8558
4.000 0.3410 0.01082 0.00373 0.0377 0.0643 0.8711
4.250 0.3678 0.01101 0.00395 0.0379 0.0629 0.8855
4.500 0.3950 0.01123 0.00419 0.0379 0.0615 0.8987
4.750 0.4241 0.01138 0.00438 0.0375 0.0608 0.9104
5.000 0.4541 0.01155 0.00458 0.0370 0.0599 0.9208
5.250 0.4852 0.01172 0.00477 0.0362 0.0579 0.9307
5.500 0.5168 0.01191 0.00495 0.0353 0.0553 0.9401
5.750 0.5497 0.01213 0.00515 0.0340 0.0529 0.9472
6.000 0.5817 0.01237 0.00539 0.0329 0.0512 0.9534
6.250 0.6134 0.01261 0.00564 0.0319 0.0490 0.9589
6.500 0.6448 0.01285 0.00587 0.0308 0.0455 0.9637
6.750 0.6774 0.01313 0.00611 0.0295 0.0419 0.9675
7.000 0.7042 0.01371 0.00655 0.0292 0.0210 0.9731
7.250 0.7362 0.01414 0.00699 0.0279 0.0199 0.9763
7.500 0.7661 0.01457 0.00744 0.0270 0.0190 0.9811
7.750 0.7969 0.01498 0.00789 0.0260 0.0184 0.9847
8.000 0.8289 0.01540 0.00836 0.0246 0.0180 0.9879
8.250 0.8592 0.01584 0.00885 0.0236 0.0177 0.9914
8.500 0.8898 0.01631 0.00938 0.0225 0.0174 0.9946
8.750 0.9207 0.01680 0.00994 0.0213 0.0171 0.9973
9.000 0.9511 0.01733 0.01053 0.0201 0.0168 0.9995
9.250 0.9704 0.01781 0.01109 0.0212 0.0165 1.0000
9.500 0.9855 0.01831 0.01165 0.0232 0.0162 1.0000
9.750 0.9998 0.01887 0.01228 0.0252 0.0158 1.0000
10.000 1.0141 0.01942 0.01291 0.0272 0.0156 1.0000
10.250 1.0271 0.02007 0.01363 0.0293 0.0152 1.0000
10.500 1.0387 0.02080 0.01444 0.0315 0.0149 1.0000
10.750 1.0482 0.02163 0.01533 0.0339 0.0146 1.0000
11.000 1.0545 0.02257 0.01634 0.0367 0.0143 1.0000
11.250 1.0621 0.02317 0.01701 0.0395 0.0141 1.0000
11.500 1.0676 0.02393 0.01784 0.0423 0.0139 1.0000
11.750 1.0734 0.02484 0.01883 0.0445 0.0137 1.0000
12.000 1.0802 0.02587 0.01995 0.0463 0.0134 1.0000
12.250 1.0858 0.02711 0.02127 0.0478 0.0132 1.0000
12.500 1.0913 0.02849 0.02275 0.0489 0.0129 1.0000
12.750 1.0961 0.03005 0.02439 0.0499 0.0126 1.0000
13.000 1.0997 0.03179 0.02622 0.0506 0.0123 1.0000
13.250 1.1012 0.03380 0.02832 0.0512 0.0119 1.0000
13.500 1.1003 0.03611 0.03071 0.0516 0.0117 1.0000
13.750 1.0968 0.03876 0.03346 0.0518 0.0116 1.0000
14.000 1.0875 0.04208 0.03687 0.0517 0.0113 1.0000
14.250 1.0824 0.04513 0.04003 0.0513 0.0112 1.0000
14.500 1.0793 0.04814 0.04315 0.0508 0.0111 1.0000
14.750 1.0790 0.05101 0.04615 0.0500 0.0109 1.0000
15.000 1.0740 0.05466 0.04994 0.0487 0.0108 1.0000
15.250 1.0622 0.05967 0.05509 0.0464 0.0108 1.0000
15.500 1.0519 0.06564 0.06121 0.0428 0.0106 1.0000
15.750 1.0383 0.07234 0.06806 0.0389 0.0106 1.0000
16.000 1.0233 0.07909 0.07494 0.0352 0.0105 1.0000
16.250 1.0059 0.08594 0.08189 0.0316 0.0105 1.0000
16.500 0.9891 0.09264 0.08869 0.0282 0.0105 1.0000
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