BOEING 707 .19 SPAN AIRFOIL (b707b-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: BOEING 707 .19 SPAN AIRFOIL (b707b-il) Reynolds number: 200,000 Max Cl/Cd: 40.33 at α=9.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-b707b-il-200000-n5.txt Download as CSV file: xf-b707b-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.750 -0.8633 0.07899 0.07500 -0.0173 1.0000 0.0189
-13.500 -0.8869 0.07198 0.06782 -0.0214 1.0000 0.0188
-13.250 -0.9057 0.06639 0.06207 -0.0239 1.0000 0.0187
-13.000 -0.9241 0.06142 0.05691 -0.0255 1.0000 0.0187
-12.750 -0.9408 0.05713 0.05241 -0.0262 1.0000 0.0187
-12.500 -0.9590 0.05336 0.04834 -0.0258 1.0000 0.0189
-12.000 -0.9729 0.04737 0.04180 -0.0248 0.8511 0.0191
-11.750 -0.9734 0.04553 0.03959 -0.0230 0.7832 0.0194
-11.500 -0.9716 0.04405 0.03794 -0.0210 0.7620 0.0198
-11.250 -0.9714 0.04227 0.03592 -0.0186 0.7494 0.0199
-11.000 -0.9673 0.04100 0.03448 -0.0163 0.7403 0.0202
-10.750 -0.9611 0.03984 0.03318 -0.0140 0.7331 0.0206
-10.500 -0.9539 0.03847 0.03161 -0.0118 0.7274 0.0209
-10.250 -0.9437 0.03710 0.03002 -0.0099 0.7229 0.0213
-10.000 -0.9323 0.03584 0.02855 -0.0081 0.7187 0.0219
-9.750 -0.9199 0.03465 0.02710 -0.0063 0.7151 0.0226
-9.500 -0.9061 0.03359 0.02574 -0.0045 0.7119 0.0232
-9.250 -0.8908 0.03229 0.02417 -0.0030 0.7090 0.0236
-9.000 -0.8717 0.03076 0.02252 -0.0022 0.7060 0.0240
-8.750 -0.8521 0.02968 0.02137 -0.0014 0.7032 0.0246
-8.500 -0.8325 0.02890 0.02051 -0.0005 0.6999 0.0254
-8.250 -0.8110 0.02785 0.01931 0.0002 0.6973 0.0257
-8.000 -0.7893 0.02700 0.01832 0.0010 0.6949 0.0262
-7.750 -0.7666 0.02602 0.01720 0.0017 0.6929 0.0264
-7.500 -0.7432 0.02501 0.01605 0.0023 0.6914 0.0263
-7.250 -0.7195 0.02407 0.01500 0.0028 0.6895 0.0262
-7.000 -0.6961 0.02320 0.01405 0.0034 0.6873 0.0260
-6.750 -0.6731 0.02240 0.01317 0.0042 0.6849 0.0259
-6.500 -0.6505 0.02167 0.01236 0.0050 0.6824 0.0258
-6.250 -0.6283 0.02098 0.01160 0.0059 0.6803 0.0257
-6.000 -0.6063 0.02036 0.01091 0.0068 0.6786 0.0256
-5.750 -0.5845 0.01976 0.01026 0.0078 0.6773 0.0256
-5.500 -0.5626 0.01923 0.00965 0.0088 0.6761 0.0255
-5.250 -0.5407 0.01872 0.00910 0.0098 0.6750 0.0254
-5.000 -0.5185 0.01822 0.00857 0.0107 0.6737 0.0254
-4.750 -0.4958 0.01778 0.00809 0.0116 0.6726 0.0254
-4.500 -0.4729 0.01737 0.00764 0.0124 0.6714 0.0254
-4.250 -0.4495 0.01699 0.00722 0.0132 0.6703 0.0254
-4.000 -0.4258 0.01665 0.00684 0.0139 0.6687 0.0254
-3.750 -0.4017 0.01634 0.00649 0.0146 0.6664 0.0254
-3.500 -0.3774 0.01606 0.00615 0.0153 0.6643 0.0255
-3.250 -0.3528 0.01580 0.00585 0.0159 0.6624 0.0256
-3.000 -0.3281 0.01557 0.00556 0.0165 0.6603 0.0258
-2.750 -0.3030 0.01535 0.00530 0.0171 0.6573 0.0259
-2.500 -0.2777 0.01512 0.00506 0.0176 0.6525 0.0262
-2.250 -0.2524 0.01493 0.00482 0.0182 0.6472 0.0265
-2.000 -0.2271 0.01475 0.00458 0.0189 0.6417 0.0270
-1.750 -0.2012 0.01456 0.00440 0.0193 0.6363 0.0276
-1.500 -0.1755 0.01438 0.00421 0.0198 0.6305 0.0291
-1.250 -0.1509 0.01409 0.00402 0.0205 0.6240 0.0622
-1.000 -0.1247 0.01392 0.00385 0.0209 0.6145 0.0713
-0.750 -0.0987 0.01376 0.00368 0.0214 0.6056 0.0794
-0.500 -0.0775 0.01304 0.00341 0.0224 0.5963 0.1977
-0.250 -0.0626 0.01192 0.00315 0.0245 0.5889 0.4239
0.000 -0.0415 0.01141 0.00305 0.0258 0.5774 0.4945
0.250 -0.0202 0.01100 0.00305 0.0272 0.5568 0.5938
0.500 -0.0027 0.01114 0.00278 0.0293 0.3900 0.6451
0.750 0.0174 0.01113 0.00303 0.0311 0.3566 0.7169
1.250 0.0655 0.01136 0.00338 0.0330 0.2973 0.7941
1.500 0.0914 0.01156 0.00362 0.0338 0.2787 0.8339
1.750 0.1186 0.01176 0.00377 0.0340 0.2644 0.8513
2.000 0.1467 0.01193 0.00391 0.0340 0.2523 0.8642
2.250 0.1766 0.01211 0.00406 0.0336 0.2415 0.8741
2.500 0.2071 0.01225 0.00421 0.0330 0.2261 0.8839
2.750 0.2362 0.01257 0.00432 0.0326 0.1725 0.8947
3.000 0.2652 0.01296 0.00454 0.0322 0.1430 0.9055
3.250 0.2931 0.01345 0.00482 0.0319 0.1036 0.9158
3.500 0.3254 0.01383 0.00511 0.0308 0.0954 0.9227
3.750 0.3560 0.01415 0.00541 0.0300 0.0916 0.9304
4.000 0.3847 0.01456 0.00577 0.0295 0.0868 0.9390
4.250 0.4183 0.01497 0.00617 0.0281 0.0820 0.9447
4.500 0.4494 0.01532 0.00655 0.0271 0.0785 0.9521
4.750 0.4831 0.01572 0.00697 0.0256 0.0764 0.9578
5.000 0.5146 0.01616 0.00742 0.0245 0.0748 0.9639
5.250 0.5465 0.01667 0.00794 0.0231 0.0733 0.9698
5.500 0.5787 0.01721 0.00848 0.0217 0.0721 0.9754
5.750 0.6121 0.01757 0.00890 0.0202 0.0713 0.9810
6.000 0.6462 0.01792 0.00929 0.0185 0.0700 0.9857
6.250 0.6805 0.01827 0.00969 0.0167 0.0680 0.9904
6.500 0.7138 0.01868 0.01014 0.0150 0.0666 0.9949
6.750 0.7475 0.01909 0.01060 0.0133 0.0650 0.9989
7.000 0.7696 0.01947 0.01100 0.0138 0.0635 1.0000
7.250 0.7854 0.01989 0.01142 0.0156 0.0623 1.0000
7.500 0.8013 0.02032 0.01187 0.0173 0.0613 1.0000
7.750 0.8185 0.02065 0.01228 0.0190 0.0607 1.0000
8.000 0.8356 0.02101 0.01271 0.0206 0.0600 1.0000
8.250 0.8526 0.02138 0.01316 0.0223 0.0592 1.0000
8.500 0.8696 0.02176 0.01362 0.0239 0.0581 1.0000
8.750 0.8870 0.02210 0.01405 0.0254 0.0565 1.0000
9.000 0.9039 0.02249 0.01451 0.0270 0.0552 1.0000
9.250 0.9208 0.02286 0.01495 0.0285 0.0539 1.0000
9.500 0.9373 0.02325 0.01542 0.0301 0.0528 1.0000
9.750 0.9537 0.02365 0.01588 0.0317 0.0516 1.0000
10.000 0.9696 0.02417 0.01652 0.0333 0.0500 1.0000
10.250 0.9856 0.02465 0.01714 0.0349 0.0474 1.0000
10.500 1.0012 0.02511 0.01771 0.0365 0.0440 1.0000
10.750 1.0150 0.02574 0.01848 0.0383 0.0405 1.0000
11.000 1.0281 0.02588 0.01833 0.0400 0.0249 1.0000
11.250 1.0324 0.02697 0.01940 0.0428 0.0235 1.0000
11.500 1.0384 0.02806 0.02055 0.0450 0.0226 1.0000
11.750 1.0434 0.02936 0.02193 0.0470 0.0215 1.0000
12.000 1.0499 0.03062 0.02329 0.0485 0.0210 1.0000
12.250 1.0558 0.03201 0.02482 0.0499 0.0205 1.0000
12.500 1.0604 0.03358 0.02654 0.0510 0.0201 1.0000
12.750 1.0624 0.03545 0.02857 0.0520 0.0196 1.0000
13.000 1.0629 0.03752 0.03080 0.0528 0.0192 1.0000
13.250 1.0610 0.03989 0.03333 0.0533 0.0189 1.0000
13.500 1.0557 0.04270 0.03629 0.0535 0.0185 1.0000
13.750 1.0458 0.04610 0.03985 0.0533 0.0181 1.0000
14.000 1.0333 0.04997 0.04388 0.0526 0.0179 1.0000
14.250 1.0228 0.05391 0.04798 0.0515 0.0178 1.0000
14.500 1.0072 0.05890 0.05313 0.0495 0.0177 1.0000
14.750 0.9887 0.06513 0.05955 0.0462 0.0176 1.0000
15.000 0.9673 0.07331 0.06794 0.0410 0.0177 1.0000
15.250 0.9449 0.08184 0.07667 0.0360 0.0179 1.0000
15.500 0.9170 0.09128 0.08630 0.0307 0.0181 1.0000
15.750 0.8867 0.10128 0.09648 0.0255 0.0186 1.0000
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