BOEING 707 .40 SPAN AIRFOIL (b707c-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: BOEING 707 .40 SPAN AIRFOIL (b707c-il) Reynolds number: 500,000 Max Cl/Cd: 61.93 at α=7.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-b707c-il-500000.txt Download as CSV file: xf-b707c-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.4778 0.08801 0.08563 -0.0275 1.0000 0.0160
-9.000 -0.4785 0.08438 0.08202 -0.0291 1.0000 0.0162
-8.750 -0.4820 0.08044 0.07811 -0.0314 1.0000 0.0163
-8.500 -0.4941 0.07592 0.07361 -0.0352 1.0000 0.0163
-8.250 -0.5073 0.07274 0.07044 -0.0349 1.0000 0.0164
-8.000 -0.5141 0.06938 0.06703 -0.0348 1.0000 0.0165
-7.750 -0.5190 0.06632 0.06393 -0.0340 1.0000 0.0166
-7.500 -0.5224 0.06347 0.06104 -0.0326 1.0000 0.0169
-7.250 -0.5246 0.06069 0.05818 -0.0308 1.0000 0.0171
-7.000 -0.5251 0.05801 0.05544 -0.0288 1.0000 0.0173
-6.750 -0.5238 0.05529 0.05262 -0.0267 1.0000 0.0179
-6.500 -0.4861 0.05133 0.04816 -0.0298 0.9960 0.0192
-6.250 -0.4617 0.04684 0.04341 -0.0319 0.9920 0.0194
-6.000 -0.4392 0.04248 0.03903 -0.0346 0.9882 0.0197
-5.750 -0.4117 0.03954 0.03602 -0.0371 0.9854 0.0201
-5.500 -0.3867 0.03704 0.03340 -0.0382 0.9801 0.0207
-5.250 -0.3565 0.03450 0.03067 -0.0398 0.9757 0.0217
-5.000 -0.3170 0.03276 0.02857 -0.0408 0.9727 0.0235
-4.750 -0.2889 0.03151 0.02692 -0.0403 0.9647 0.0238
-4.500 -0.2605 0.02684 0.02215 -0.0422 0.9592 0.0244
-4.250 -0.2333 0.02477 0.02001 -0.0430 0.9480 0.0249
-4.000 -0.2023 0.02303 0.01814 -0.0441 0.9355 0.0256
-3.750 -0.1710 0.02144 0.01637 -0.0448 0.9192 0.0269
-3.500 -0.1369 0.02185 0.01632 -0.0444 0.8970 0.0295
-3.250 -0.1120 0.01867 0.01290 -0.0440 0.8695 0.0303
-3.000 -0.0868 0.01718 0.01128 -0.0436 0.8301 0.0314
-2.750 -0.0648 0.01641 0.01018 -0.0422 0.7656 0.0327
-2.250 -0.0198 0.01515 0.00819 -0.0391 0.6734 0.0383
-2.000 0.0040 0.01434 0.00727 -0.0383 0.6448 0.0404
-1.750 0.0313 0.01359 0.00618 -0.0369 0.6211 0.0289
-1.500 0.0550 0.01216 0.00461 -0.0356 0.5979 0.0246
-1.250 0.0786 0.01175 0.00405 -0.0346 0.5675 0.0241
-1.000 0.0995 0.01128 0.00338 -0.0332 0.5075 0.0244
-0.750 0.1169 0.01152 0.00306 -0.0313 0.3696 0.0254
-0.500 0.1351 0.01208 0.00304 -0.0298 0.2137 0.0270
-0.250 0.1599 0.01199 0.00286 -0.0291 0.1985 0.0297
0.000 0.1847 0.01180 0.00263 -0.0285 0.1773 0.0365
0.250 0.2058 0.01200 0.00242 -0.0273 0.0514 0.0464
0.500 0.2313 0.01190 0.00227 -0.0269 0.0465 0.0550
0.750 0.2567 0.01178 0.00228 -0.0264 0.0454 0.1112
1.000 0.2770 0.01108 0.00233 -0.0253 0.0426 0.4103
1.250 0.2935 0.01029 0.00241 -0.0233 0.0402 0.6588
1.500 0.3143 0.01018 0.00263 -0.0218 0.0381 0.7513
1.750 0.3369 0.01017 0.00281 -0.0205 0.0376 0.8010
2.000 0.3600 0.01015 0.00294 -0.0194 0.0363 0.8459
2.250 0.3849 0.01018 0.00313 -0.0185 0.0352 0.8996
2.500 0.4249 0.01038 0.00340 -0.0211 0.0339 0.9460
2.750 0.4718 0.01071 0.00370 -0.0254 0.0325 0.9730
3.000 0.5102 0.01116 0.00412 -0.0280 0.0307 0.9842
3.250 0.5476 0.01125 0.00417 -0.0303 0.0294 0.9896
3.500 0.5836 0.01142 0.00431 -0.0323 0.0281 0.9954
3.750 0.6214 0.01158 0.00441 -0.0348 0.0266 0.9999
4.000 0.6421 0.01179 0.00460 -0.0336 0.0259 1.0000
4.250 0.6628 0.01200 0.00478 -0.0323 0.0252 1.0000
4.500 0.6850 0.01212 0.00490 -0.0312 0.0247 1.0000
4.750 0.7070 0.01231 0.00509 -0.0302 0.0243 1.0000
5.000 0.7291 0.01251 0.00532 -0.0291 0.0237 1.0000
5.250 0.7512 0.01274 0.00556 -0.0281 0.0232 1.0000
5.500 0.7734 0.01297 0.00581 -0.0271 0.0223 1.0000
5.750 0.7959 0.01318 0.00603 -0.0261 0.0214 1.0000
6.000 0.8177 0.01347 0.00635 -0.0251 0.0207 1.0000
6.250 0.8385 0.01386 0.00682 -0.0238 0.0193 1.0000
6.500 0.8586 0.01433 0.00736 -0.0224 0.0173 1.0000
6.750 0.8832 0.01440 0.00739 -0.0219 0.0168 1.0000
7.000 0.9058 0.01465 0.00765 -0.0211 0.0164 1.0000
7.250 0.9277 0.01498 0.00797 -0.0201 0.0162 1.0000
7.500 0.9490 0.01535 0.00836 -0.0190 0.0159 1.0000
7.750 0.9693 0.01582 0.00887 -0.0178 0.0158 1.0000
8.000 0.9893 0.01631 0.00941 -0.0166 0.0157 1.0000
8.250 1.0082 0.01689 0.01004 -0.0152 0.0156 1.0000
8.500 1.0267 0.01749 0.01071 -0.0138 0.0155 1.0000
8.750 1.0449 0.01811 0.01137 -0.0123 0.0153 1.0000
9.000 1.0616 0.01885 0.01220 -0.0106 0.0152 1.0000
9.250 1.0774 0.01966 0.01307 -0.0089 0.0150 1.0000
9.500 1.0921 0.02057 0.01408 -0.0070 0.0150 1.0000
9.750 1.1057 0.02162 0.01523 -0.0050 0.0150 1.0000
10.000 1.1183 0.02286 0.01660 -0.0029 0.0150 1.0000
10.250 1.1303 0.02426 0.01815 -0.0008 0.0151 1.0000
10.500 1.1417 0.02584 0.01989 0.0013 0.0151 1.0000
10.750 1.1122 0.04092 0.03638 0.0067 0.0168 1.0000
11.000 1.1079 0.04374 0.03942 0.0099 0.0171 1.0000
11.250 1.0966 0.04649 0.04236 0.0138 0.0172 1.0000
11.500 1.0861 0.04904 0.04507 0.0170 0.0173 1.0000
11.750 1.0719 0.05204 0.04823 0.0197 0.0174 1.0000
12.000 1.0628 0.05487 0.05116 0.0212 0.0175 1.0000
12.250 0.9484 0.05083 0.04757 0.0237 0.0174 1.0000
12.500 0.9286 0.05600 0.05287 0.0228 0.0175 1.0000
12.750 0.9044 0.06223 0.05924 0.0210 0.0175 1.0000
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Polar data table (+)
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