BOEING 707 .08 SPAN AIRFOIL (b707a-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: BOEING 707 .08 SPAN AIRFOIL (b707a-il) Reynolds number: 500,000 Max Cl/Cd: 52.43 at α=8.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-b707a-il-500000-n5.txt Download as CSV file: xf-b707a-il-500000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-18.000 -1.0066 0.12589 0.12242 0.0053 1.0000 0.0114
-17.750 -1.0330 0.11550 0.11184 -0.0007 1.0000 0.0113
-17.500 -1.0526 0.10719 0.10335 -0.0054 1.0000 0.0113
-17.250 -1.0691 0.09996 0.09597 -0.0093 1.0000 0.0113
-17.000 -1.0831 0.09357 0.08943 -0.0126 1.0000 0.0112
-16.750 -1.0946 0.08791 0.08364 -0.0154 1.0000 0.0112
-16.500 -1.1058 0.08251 0.07809 -0.0180 1.0000 0.0112
-16.250 -1.1143 0.07773 0.07320 -0.0201 1.0000 0.0112
-16.000 -1.1219 0.07328 0.06864 -0.0220 1.0000 0.0113
-15.750 -1.1286 0.06907 0.06430 -0.0237 1.0000 0.0113
-15.500 -1.1358 0.06497 0.06006 -0.0251 1.0000 0.0112
-15.250 -1.1390 0.06151 0.05651 -0.0262 1.0000 0.0113
-15.000 -1.1415 0.05821 0.05312 -0.0273 1.0000 0.0114
-14.750 -1.1436 0.05500 0.04981 -0.0281 1.0000 0.0114
-14.500 -1.1439 0.05203 0.04673 -0.0289 1.0000 0.0114
-14.250 -1.1439 0.04914 0.04374 -0.0295 1.0000 0.0115
-14.000 -1.1418 0.04656 0.04107 -0.0299 1.0000 0.0115
-13.750 -1.1397 0.04402 0.03842 -0.0302 1.0000 0.0115
-13.500 -1.1362 0.04169 0.03600 -0.0303 1.0000 0.0115
-13.250 -1.1319 0.03951 0.03373 -0.0303 1.0000 0.0115
-13.000 -1.1271 0.03744 0.03157 -0.0301 1.0000 0.0115
-12.750 -1.1220 0.03546 0.02951 -0.0298 1.0000 0.0115
-12.500 -1.1162 0.03364 0.02761 -0.0293 1.0000 0.0116
-12.250 -1.1098 0.03197 0.02587 -0.0286 1.0000 0.0116
-10.250 -0.9913 0.02279 0.01526 -0.0258 0.6030 0.0119
-10.000 -0.9852 0.02237 0.01453 -0.0225 0.5035 0.0119
-9.750 -0.9747 0.02190 0.01374 -0.0201 0.3664 0.0120
-9.250 -0.9447 0.02069 0.01234 -0.0164 0.3333 0.0121
-9.000 -0.9277 0.02010 0.01168 -0.0148 0.3301 0.0122
-8.750 -0.9099 0.01952 0.01104 -0.0133 0.3278 0.0123
-8.500 -0.8909 0.01899 0.01046 -0.0119 0.3257 0.0124
-8.250 -0.8713 0.01848 0.00989 -0.0106 0.3239 0.0126
-8.000 -0.8509 0.01800 0.00936 -0.0094 0.3226 0.0126
-7.500 -0.8081 0.01714 0.00840 -0.0072 0.3206 0.0129
-7.250 -0.7858 0.01675 0.00796 -0.0063 0.3200 0.0131
-7.000 -0.7639 0.01630 0.00747 -0.0052 0.3194 0.0133
-6.750 -0.7412 0.01592 0.00704 -0.0043 0.3189 0.0135
-6.500 -0.7180 0.01556 0.00664 -0.0034 0.3184 0.0137
-6.250 -0.6947 0.01520 0.00624 -0.0026 0.3179 0.0142
-6.000 -0.6707 0.01490 0.00589 -0.0018 0.3176 0.0146
-5.750 -0.6464 0.01461 0.00557 -0.0011 0.3172 0.0149
-5.500 -0.6218 0.01434 0.00526 -0.0004 0.3166 0.0154
-5.250 -0.5972 0.01407 0.00495 0.0003 0.3156 0.0161
-5.000 -0.5727 0.01378 0.00463 0.0011 0.3144 0.0173
-4.750 -0.5491 0.01338 0.00431 0.0019 0.3136 0.0262
-4.500 -0.5232 0.01323 0.00421 0.0023 0.3130 0.0422
-4.250 -0.4969 0.01313 0.00409 0.0028 0.3118 0.0461
-4.000 -0.4708 0.01301 0.00397 0.0033 0.3102 0.0493
-3.750 -0.4444 0.01293 0.00386 0.0037 0.3090 0.0518
-3.500 -0.4184 0.01277 0.00370 0.0042 0.3083 0.0538
-3.250 -0.3922 0.01266 0.00357 0.0047 0.3074 0.0554
-2.750 -0.3394 0.01244 0.00332 0.0056 0.3045 0.0592
-2.500 -0.3129 0.01230 0.00318 0.0060 0.3028 0.0617
-2.250 -0.2862 0.01219 0.00307 0.0064 0.3011 0.0649
-2.000 -0.2597 0.01204 0.00294 0.0068 0.2989 0.0700
-1.750 -0.2332 0.01192 0.00283 0.0073 0.2962 0.0762
-1.500 -0.2098 0.01140 0.00258 0.0081 0.2932 0.1594
-1.250 -0.1870 0.01082 0.00230 0.0089 0.2910 0.2560
-1.000 -0.1629 0.01035 0.00226 0.0096 0.2888 0.3695
-0.750 -0.1353 0.01031 0.00226 0.0099 0.2850 0.3834
-0.500 -0.1078 0.01029 0.00224 0.0102 0.2808 0.3912
-0.250 -0.0802 0.01029 0.00224 0.0105 0.2766 0.3987
0.000 -0.0519 0.01026 0.00222 0.0107 0.2710 0.4038
0.250 -0.0242 0.01020 0.00218 0.0110 0.2644 0.4084
0.500 0.0038 0.01014 0.00219 0.0113 0.2510 0.4136
0.750 0.0315 0.01013 0.00198 0.0115 0.2071 0.4187
1.000 0.0586 0.01025 0.00203 0.0119 0.1933 0.4222
1.250 0.0857 0.01035 0.00209 0.0122 0.1834 0.4247
1.500 0.1126 0.01041 0.00215 0.0126 0.1730 0.4294
1.750 0.1393 0.01052 0.00223 0.0130 0.1577 0.4344
2.000 0.1659 0.01068 0.00230 0.0134 0.1376 0.4387
2.250 0.1928 0.01084 0.00238 0.0138 0.1237 0.4424
2.500 0.2196 0.01095 0.00247 0.0142 0.1149 0.4453
2.750 0.2464 0.01105 0.00256 0.0146 0.1068 0.4482
3.000 0.2732 0.01119 0.00267 0.0150 0.0959 0.4511
3.250 0.2989 0.01148 0.00282 0.0155 0.0656 0.4540
3.500 0.3249 0.01173 0.00302 0.0160 0.0564 0.4570
3.750 0.3515 0.01191 0.00319 0.0164 0.0531 0.4602
4.000 0.3783 0.01207 0.00337 0.0168 0.0509 0.4633
4.250 0.4049 0.01220 0.00354 0.0172 0.0491 0.4676
4.500 0.4312 0.01237 0.00373 0.0177 0.0471 0.4729
4.750 0.4578 0.01251 0.00391 0.0181 0.0447 0.4795
5.250 0.5103 0.01280 0.00428 0.0190 0.0385 0.4959
5.750 0.5604 0.01341 0.00485 0.0202 0.0148 0.5183
6.000 0.5855 0.01366 0.00519 0.0208 0.0137 0.5337
6.250 0.6104 0.01387 0.00552 0.0215 0.0132 0.5568
6.500 0.6347 0.01403 0.00585 0.0222 0.0129 0.5952
6.750 0.6580 0.01415 0.00621 0.0232 0.0126 0.6538
7.000 0.6806 0.01430 0.00660 0.0244 0.0123 0.7128
7.250 0.7026 0.01445 0.00699 0.0256 0.0122 0.7682
7.500 0.7234 0.01458 0.00742 0.0272 0.0119 0.8373
7.750 0.7736 0.01500 0.00816 0.0225 0.0116 0.9483
8.000 0.8158 0.01561 0.00885 0.0193 0.0114 0.9804
8.250 0.8493 0.01620 0.00952 0.0179 0.0112 0.9938
8.500 0.8768 0.01682 0.01020 0.0177 0.0111 1.0000
8.750 0.8977 0.01732 0.01076 0.0190 0.0110 1.0000
9.000 0.9183 0.01786 0.01136 0.0203 0.0110 1.0000
9.250 0.9385 0.01844 0.01201 0.0216 0.0109 1.0000
9.500 0.9583 0.01905 0.01267 0.0229 0.0108 1.0000
9.750 0.9776 0.01970 0.01339 0.0243 0.0108 1.0000
10.000 0.9964 0.02040 0.01415 0.0257 0.0107 1.0000
10.250 1.0144 0.02115 0.01497 0.0271 0.0107 1.0000
10.500 1.0317 0.02195 0.01584 0.0286 0.0106 1.0000
10.750 1.0483 0.02278 0.01675 0.0301 0.0106 1.0000
11.000 1.0639 0.02367 0.01771 0.0317 0.0105 1.0000
11.250 1.0781 0.02463 0.01875 0.0334 0.0105 1.0000
11.500 1.0911 0.02565 0.01985 0.0352 0.0105 1.0000
11.750 1.1032 0.02667 0.02096 0.0370 0.0105 1.0000
12.000 1.1121 0.02785 0.02223 0.0391 0.0104 1.0000
12.250 1.1191 0.02907 0.02353 0.0413 0.0104 1.0000
12.500 1.1194 0.03036 0.02491 0.0444 0.0104 1.0000
12.750 1.1173 0.03187 0.02651 0.0472 0.0104 1.0000
13.000 1.1128 0.03379 0.02855 0.0492 0.0104 1.0000
13.250 1.1041 0.03654 0.03143 0.0498 0.0104 1.0000
13.500 1.0889 0.04193 0.03702 0.0458 0.0104 1.0000
13.750 1.0718 0.05083 0.04615 0.0377 0.0104 1.0000
14.000 1.0443 0.05941 0.05487 0.0317 0.0104 1.0000
14.250 1.0165 0.06705 0.06262 0.0271 0.0105 1.0000
14.500 0.9945 0.07383 0.06949 0.0232 0.0105 1.0000
14.750 0.9749 0.08044 0.07620 0.0196 0.0105 1.0000
15.000 0.9606 0.08625 0.08207 0.0166 0.0105 1.0000
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