BOEING 707 .40 SPAN AIRFOIL (b707c-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: BOEING 707 .40 SPAN AIRFOIL (b707c-il) Reynolds number: 200,000 Max Cl/Cd: 43.44 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-b707c-il-200000-n5.txt Download as CSV file: xf-b707c-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.3679 0.09058 0.08697 -0.0272 1.0000 0.0247
-9.500 -0.3689 0.08674 0.08315 -0.0283 1.0000 0.0250
-9.250 -0.3708 0.08278 0.07923 -0.0294 1.0000 0.0253
-9.000 -0.3735 0.07878 0.07525 -0.0306 1.0000 0.0255
-8.750 -0.3774 0.07471 0.07121 -0.0319 1.0000 0.0256
-8.500 -0.3833 0.07049 0.06703 -0.0335 1.0000 0.0258
-8.250 -0.3925 0.06608 0.06265 -0.0356 1.0000 0.0258
-8.000 -0.4088 0.06170 0.05829 -0.0380 1.0000 0.0257
-7.750 -0.4279 0.05852 0.05511 -0.0370 1.0000 0.0257
-7.500 -0.4395 0.05524 0.05181 -0.0359 1.0000 0.0257
-7.250 -0.4484 0.05198 0.04850 -0.0345 1.0000 0.0260
-7.000 -0.4542 0.04889 0.04535 -0.0327 1.0000 0.0261
-6.750 -0.4492 0.04518 0.04151 -0.0330 0.9973 0.0268
-6.500 -0.4284 0.04176 0.03780 -0.0351 0.9906 0.0283
-6.250 -0.4045 0.03907 0.03476 -0.0366 0.9835 0.0290
-6.000 -0.3821 0.03555 0.03098 -0.0379 0.9765 0.0291
-5.750 -0.3593 0.03198 0.02719 -0.0390 0.9693 0.0292
-5.500 -0.3360 0.02893 0.02387 -0.0397 0.9608 0.0293
-5.250 -0.3258 0.02215 0.01701 -0.0406 0.9525 0.0307
-5.000 -0.3035 0.01935 0.01410 -0.0413 0.9429 0.0316
-4.750 -0.2799 0.01700 0.01156 -0.0415 0.9321 0.0320
-4.500 -0.2550 0.01490 0.00925 -0.0417 0.9187 0.0324
-4.250 -0.2278 0.01291 0.00701 -0.0419 0.9037 0.0324
-3.750 -0.1915 0.02456 0.01753 -0.0391 0.9025 0.0210
-3.500 -0.1618 0.02256 0.01534 -0.0396 0.8854 0.0204
-3.250 -0.1292 0.02087 0.01343 -0.0404 0.8634 0.0199
-3.000 -0.0959 0.01939 0.01168 -0.0411 0.8319 0.0195
-2.750 -0.0651 0.01813 0.01015 -0.0412 0.7936 0.0192
-2.500 -0.0375 0.01714 0.00889 -0.0407 0.7559 0.0191
-2.250 -0.0116 0.01629 0.00783 -0.0399 0.7275 0.0191
-2.000 0.0125 0.01563 0.00692 -0.0388 0.6920 0.0193
-1.750 0.0349 0.01514 0.00615 -0.0374 0.6529 0.0197
-1.500 0.0574 0.01467 0.00549 -0.0361 0.6239 0.0203
-1.250 0.0815 0.01430 0.00501 -0.0352 0.6100 0.0215
-1.000 0.1032 0.01397 0.00461 -0.0340 0.5768 0.0236
-0.750 0.1242 0.01386 0.00424 -0.0327 0.5033 0.0255
-0.500 0.1420 0.01402 0.00385 -0.0308 0.3912 0.0267
-0.250 0.1578 0.01473 0.00376 -0.0289 0.2170 0.0281
0.000 0.1811 0.01461 0.00349 -0.0281 0.1974 0.0305
0.250 0.2057 0.01447 0.00322 -0.0275 0.1733 0.0373
0.500 0.2270 0.01489 0.00317 -0.0264 0.0430 0.0474
0.750 0.2522 0.01488 0.00311 -0.0258 0.0393 0.0583
1.000 0.2714 0.01404 0.00314 -0.0246 0.0379 0.3989
1.250 0.2864 0.01315 0.00324 -0.0223 0.0368 0.6504
1.500 0.3068 0.01297 0.00345 -0.0204 0.0358 0.7620
1.750 0.3308 0.01300 0.00363 -0.0194 0.0351 0.8084
2.000 0.3579 0.01307 0.00383 -0.0190 0.0345 0.8556
2.250 0.4119 0.01328 0.00423 -0.0242 0.0341 0.9478
2.500 0.4482 0.01352 0.00444 -0.0261 0.0338 0.9642
2.750 0.4827 0.01374 0.00463 -0.0278 0.0325 0.9761
3.000 0.5179 0.01399 0.00486 -0.0296 0.0308 0.9869
3.250 0.5533 0.01427 0.00513 -0.0316 0.0295 0.9976
3.500 0.5777 0.01452 0.00537 -0.0312 0.0290 1.0000
3.750 0.5983 0.01478 0.00562 -0.0299 0.0287 1.0000
4.000 0.6189 0.01507 0.00591 -0.0287 0.0283 1.0000
4.250 0.6396 0.01537 0.00622 -0.0275 0.0279 1.0000
4.500 0.6603 0.01569 0.00658 -0.0263 0.0277 1.0000
4.750 0.6808 0.01605 0.00696 -0.0250 0.0274 1.0000
5.000 0.7011 0.01645 0.00738 -0.0238 0.0271 1.0000
5.250 0.7213 0.01688 0.00784 -0.0225 0.0269 1.0000
5.500 0.7412 0.01733 0.00832 -0.0213 0.0266 1.0000
5.750 0.7623 0.01771 0.00874 -0.0202 0.0262 1.0000
6.000 0.7835 0.01807 0.00919 -0.0191 0.0253 1.0000
6.250 0.8040 0.01851 0.00970 -0.0180 0.0244 1.0000
6.500 0.8241 0.01901 0.01026 -0.0168 0.0233 1.0000
6.750 0.8437 0.01957 0.01088 -0.0155 0.0225 1.0000
7.000 0.8633 0.02012 0.01151 -0.0143 0.0217 1.0000
7.250 0.8809 0.02097 0.01249 -0.0127 0.0199 1.0000
7.500 0.8989 0.02183 0.01345 -0.0112 0.0184 1.0000
7.750 0.9171 0.02271 0.01439 -0.0098 0.0175 1.0000
8.000 0.9362 0.02344 0.01521 -0.0086 0.0164 1.0000
8.250 0.9560 0.02391 0.01573 -0.0076 0.0156 1.0000
8.500 0.9749 0.02454 0.01641 -0.0065 0.0153 1.0000
8.750 0.9930 0.02527 0.01722 -0.0053 0.0151 1.0000
9.000 1.0104 0.02611 0.01815 -0.0040 0.0149 1.0000
9.250 1.0273 0.02702 0.01916 -0.0027 0.0148 1.0000
9.500 1.0433 0.02809 0.02035 -0.0013 0.0146 1.0000
9.750 1.0587 0.02907 0.02143 0.0001 0.0144 1.0000
10.000 1.0724 0.03056 0.02309 0.0018 0.0144 1.0000
10.250 1.0847 0.03181 0.02448 0.0036 0.0142 1.0000
10.500 1.0950 0.03366 0.02655 0.0055 0.0142 1.0000
10.750 1.1026 0.03571 0.02884 0.0076 0.0141 1.0000
11.000 1.1060 0.03836 0.03177 0.0100 0.0141 1.0000
11.250 1.1047 0.04121 0.03491 0.0126 0.0141 1.0000
11.500 1.0967 0.04465 0.03868 0.0153 0.0141 1.0000
11.750 1.0826 0.04854 0.04290 0.0178 0.0142 1.0000
12.000 1.0653 0.05264 0.04730 0.0195 0.0142 1.0000
12.250 1.0446 0.05735 0.05229 0.0202 0.0143 1.0000
12.500 1.0223 0.06256 0.05775 0.0195 0.0144 1.0000
12.750 0.9959 0.06891 0.06435 0.0174 0.0145 1.0000
13.000 0.9676 0.07627 0.07192 0.0138 0.0146 1.0000
13.250 0.9344 0.08560 0.08145 0.0081 0.0147 1.0000
13.500 0.8909 0.09940 0.09544 -0.0011 0.0149 1.0000
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Polar data table (+)
Polar graphs
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