BOEING 707 .08 SPAN AIRFOIL (b707a-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: BOEING 707 .08 SPAN AIRFOIL (b707a-il) Reynolds number: 500,000 Max Cl/Cd: 59.12 at α=7.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-b707a-il-500000.txt Download as CSV file: xf-b707a-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: BOEING 707 .08 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.000 -0.8487 0.13023 0.12753 0.0085 1.0000 0.0215
-15.750 -0.9599 0.09874 0.09568 -0.0105 1.0000 0.0205
-15.500 -1.0391 0.08064 0.07711 -0.0213 1.0000 0.0198
-15.250 -1.0854 0.07018 0.06627 -0.0271 1.0000 0.0194
-15.000 -1.1197 0.06223 0.05794 -0.0311 1.0000 0.0192
-14.750 -1.1366 0.05699 0.05243 -0.0331 1.0000 0.0190
-14.500 -1.1466 0.05291 0.04813 -0.0345 1.0000 0.0188
-14.250 -1.1536 0.04940 0.04441 -0.0354 1.0000 0.0187
-14.000 -1.1558 0.04657 0.04143 -0.0358 1.0000 0.0187
-13.750 -1.1571 0.04406 0.03875 -0.0359 1.0000 0.0186
-13.500 -1.1558 0.04190 0.03645 -0.0356 1.0000 0.0186
-13.250 -1.1533 0.03990 0.03432 -0.0350 1.0000 0.0185
-13.000 -1.1493 0.03815 0.03246 -0.0341 1.0000 0.0185
-12.750 -1.1428 0.03629 0.03049 -0.0330 1.0000 0.0184
-12.500 -1.1358 0.03455 0.02864 -0.0318 1.0000 0.0184
-12.250 -1.1267 0.03294 0.02694 -0.0304 1.0000 0.0184
-12.000 -1.1188 0.03151 0.02540 -0.0288 1.0000 0.0184
-11.750 -1.1102 0.03022 0.02402 -0.0271 1.0000 0.0184
-11.500 -1.1017 0.02907 0.02278 -0.0251 1.0000 0.0184
-11.250 -1.0922 0.02803 0.02166 -0.0230 1.0000 0.0185
-11.000 -1.0824 0.02685 0.02042 -0.0207 1.0000 0.0185
-10.750 -1.0730 0.02595 0.01947 -0.0182 1.0000 0.0185
-10.500 -1.0636 0.02502 0.01849 -0.0155 1.0000 0.0184
-10.250 -1.0524 0.02407 0.01750 -0.0131 1.0000 0.0184
-10.000 -1.0403 0.02315 0.01654 -0.0108 1.0000 0.0184
-9.750 -1.0279 0.02229 0.01564 -0.0085 1.0000 0.0184
-9.500 -1.0150 0.02147 0.01479 -0.0062 1.0000 0.0184
-9.250 -1.0018 0.02068 0.01397 -0.0039 1.0000 0.0185
-9.000 -0.9881 0.01992 0.01320 -0.0016 1.0000 0.0185
-8.750 -0.9750 0.01912 0.01237 0.0008 1.0000 0.0185
-8.500 -0.9611 0.01835 0.01159 0.0031 1.0000 0.0186
-8.250 -0.9468 0.01761 0.01082 0.0054 1.0000 0.0187
-8.000 -0.9309 0.01696 0.01015 0.0074 1.0000 0.0188
-7.750 -0.9145 0.01632 0.00949 0.0094 1.0000 0.0190
-7.500 -0.8795 0.01559 0.00874 0.0075 0.9960 0.0193
-7.250 -0.8484 0.01499 0.00812 0.0066 0.9915 0.0196
-7.000 -0.8186 0.01446 0.00756 0.0060 0.9862 0.0201
-6.750 -0.7863 0.01398 0.00705 0.0049 0.9812 0.0205
-6.500 -0.7591 0.01356 0.00660 0.0050 0.9740 0.0210
-6.250 -0.7263 0.01306 0.00609 0.0039 0.9668 0.0224
-6.000 -0.6956 0.01259 0.00563 0.0033 0.9565 0.0245
-5.750 -0.6391 0.01282 0.00521 -0.0026 0.6668 0.0415
-5.500 -0.6186 0.01316 0.00512 -0.0010 0.5309 0.0464
-5.250 -0.5932 0.01318 0.00502 -0.0004 0.4938 0.0501
-5.000 -0.5694 0.01328 0.00485 0.0004 0.3886 0.0531
-4.750 -0.5437 0.01324 0.00472 0.0009 0.3726 0.0560
-4.500 -0.5178 0.01312 0.00456 0.0014 0.3672 0.0591
-4.250 -0.4923 0.01297 0.00439 0.0020 0.3624 0.0622
-4.000 -0.4661 0.01290 0.00427 0.0024 0.3588 0.0648
-3.750 -0.4413 0.01262 0.00398 0.0031 0.3563 0.0679
-3.500 -0.4156 0.01245 0.00378 0.0036 0.3547 0.0702
-3.250 -0.3894 0.01230 0.00360 0.0041 0.3531 0.0721
-3.000 -0.3634 0.01213 0.00340 0.0047 0.3511 0.0743
-2.750 -0.3377 0.01193 0.00320 0.0052 0.3484 0.0781
-2.500 -0.3115 0.01180 0.00305 0.0057 0.3457 0.0818
-2.250 -0.2859 0.01161 0.00288 0.0063 0.3433 0.0921
-2.000 -0.2686 0.01031 0.00231 0.0078 0.3407 0.2746
-1.750 -0.2446 0.01011 0.00245 0.0086 0.3371 0.3902
-1.500 -0.2171 0.01013 0.00249 0.0089 0.3338 0.4067
-1.250 -0.1899 0.01017 0.00255 0.0093 0.3306 0.4185
-1.000 -0.1626 0.01023 0.00259 0.0097 0.3276 0.4275
-0.750 -0.1359 0.01032 0.00267 0.0101 0.3232 0.4341
-0.500 -0.1085 0.01041 0.00273 0.0105 0.3190 0.4392
-0.250 -0.0806 0.01047 0.00275 0.0107 0.3143 0.4432
0.000 -0.0538 0.01047 0.00277 0.0111 0.3091 0.4482
0.250 -0.0268 0.01055 0.00284 0.0115 0.3041 0.4522
0.500 0.0010 0.01053 0.00285 0.0118 0.2988 0.4566
0.750 0.0283 0.01062 0.00288 0.0121 0.2927 0.4607
1.000 0.0564 0.01061 0.00289 0.0124 0.2861 0.4637
1.250 0.0837 0.01053 0.00283 0.0127 0.2789 0.4673
1.500 0.1120 0.01037 0.00276 0.0129 0.2680 0.4720
2.250 0.1941 0.01051 0.00260 0.0138 0.1833 0.4847
2.500 0.2207 0.01055 0.00267 0.0143 0.1737 0.4893
2.750 0.2474 0.01063 0.00276 0.0147 0.1634 0.4933
3.000 0.2741 0.01074 0.00284 0.0151 0.1523 0.4975
3.250 0.3011 0.01083 0.00292 0.0155 0.1421 0.5019
3.500 0.3277 0.01097 0.00301 0.0159 0.1291 0.5066
3.750 0.3540 0.01106 0.00312 0.0163 0.1184 0.5134
4.000 0.3803 0.01120 0.00325 0.0168 0.1071 0.5212
4.250 0.4063 0.01135 0.00340 0.0173 0.0940 0.5312
4.500 0.4316 0.01156 0.00356 0.0179 0.0734 0.5456
4.750 0.4563 0.01174 0.00378 0.0186 0.0650 0.5701
5.000 0.4799 0.01178 0.00404 0.0195 0.0606 0.6223
5.250 0.5012 0.01175 0.00433 0.0209 0.0577 0.7147
5.500 0.5219 0.01160 0.00456 0.0228 0.0558 0.8081
5.750 0.5647 0.01169 0.00500 0.0200 0.0530 0.9331
6.000 0.6196 0.01203 0.00537 0.0143 0.0501 0.9714
6.250 0.6605 0.01235 0.00568 0.0116 0.0476 0.9868
6.500 0.7005 0.01263 0.00597 0.0091 0.0457 0.9969
6.750 0.7343 0.01286 0.00620 0.0079 0.0431 1.0000
7.000 0.7572 0.01307 0.00642 0.0090 0.0407 1.0000
7.250 0.7802 0.01329 0.00664 0.0101 0.0382 1.0000
7.500 0.8029 0.01358 0.00686 0.0112 0.0257 1.0000
7.750 0.8229 0.01419 0.00738 0.0127 0.0197 1.0000
8.000 0.8442 0.01467 0.00789 0.0140 0.0186 1.0000
8.250 0.8658 0.01512 0.00837 0.0153 0.0180 1.0000
8.500 0.8875 0.01556 0.00886 0.0165 0.0177 1.0000
8.750 0.9090 0.01601 0.00936 0.0177 0.0175 1.0000
9.000 0.9304 0.01649 0.00991 0.0190 0.0173 1.0000
9.250 0.9512 0.01703 0.01051 0.0203 0.0170 1.0000
9.500 0.9719 0.01757 0.01111 0.0216 0.0169 1.0000
9.750 0.9922 0.01815 0.01176 0.0229 0.0168 1.0000
10.000 1.0122 0.01876 0.01245 0.0242 0.0167 1.0000
10.250 1.0313 0.01944 0.01320 0.0256 0.0166 1.0000
10.500 1.0499 0.02016 0.01400 0.0270 0.0165 1.0000
10.750 1.0678 0.02093 0.01483 0.0285 0.0164 1.0000
11.000 1.0847 0.02175 0.01573 0.0301 0.0164 1.0000
11.250 1.1005 0.02263 0.01669 0.0317 0.0163 1.0000
11.500 1.1148 0.02360 0.01772 0.0335 0.0162 1.0000
11.750 1.1276 0.02462 0.01883 0.0353 0.0161 1.0000
12.000 1.1385 0.02573 0.02001 0.0374 0.0160 1.0000
12.250 1.1475 0.02689 0.02124 0.0395 0.0159 1.0000
12.500 1.1536 0.02814 0.02257 0.0420 0.0159 1.0000
12.750 1.1551 0.02935 0.02386 0.0451 0.0158 1.0000
13.000 1.1532 0.03076 0.02536 0.0481 0.0158 1.0000
13.250 1.1506 0.03241 0.02710 0.0505 0.0158 1.0000
13.500 1.1461 0.03451 0.02931 0.0519 0.0158 1.0000
13.750 1.1387 0.03746 0.03238 0.0516 0.0158 1.0000
14.000 1.1297 0.04212 0.03720 0.0481 0.0158 1.0000
14.250 1.1191 0.04825 0.04350 0.0429 0.0159 1.0000
14.500 1.1095 0.05447 0.04987 0.0382 0.0159 1.0000
14.750 1.0946 0.06070 0.05620 0.0342 0.0159 1.0000
15.000 1.0785 0.06669 0.06229 0.0306 0.0160 1.0000
15.250 1.0627 0.07240 0.06810 0.0273 0.0161 1.0000
15.500 1.0481 0.07789 0.07367 0.0244 0.0161 1.0000
15.750 1.0342 0.08351 0.07939 0.0213 0.0162 1.0000
16.000 1.0229 0.08870 0.08465 0.0186 0.0162 1.0000
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