BOEING 707 .19 SPAN AIRFOIL (b707b-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: BOEING 707 .19 SPAN AIRFOIL (b707b-il) Reynolds number: 500,000 Max Cl/Cd: 60.89 at α=9.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-b707b-il-500000.txt Download as CSV file: xf-b707b-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.250 -0.8040 0.08036 0.07792 -0.0217 0.8902 0.0258
-13.000 -0.8335 0.07308 0.07012 -0.0261 0.7777 0.0255
-12.750 -0.8600 0.06738 0.06420 -0.0283 0.7555 0.0250
-12.500 -0.8915 0.06162 0.05822 -0.0294 0.7428 0.0246
-12.250 -0.9187 0.05699 0.05334 -0.0288 0.7341 0.0248
-12.000 -0.9518 0.05186 0.04793 -0.0267 0.7275 0.0241
-11.750 -0.9637 0.04967 0.04554 -0.0240 0.7217 0.0250
-11.500 -0.9806 0.04671 0.04233 -0.0203 0.7165 0.0249
-11.250 -0.9933 0.04427 0.03966 -0.0161 0.7122 0.0251
-11.000 -1.0011 0.04194 0.03709 -0.0121 0.7079 0.0252
-10.750 -1.0012 0.03981 0.03469 -0.0090 0.7046 0.0254
-10.500 -0.9959 0.04061 0.03516 -0.0055 0.7007 0.0264
-10.250 -0.9917 0.03778 0.03207 -0.0031 0.6979 0.0265
-10.000 -0.9827 0.03532 0.02936 -0.0011 0.6954 0.0266
-9.750 -0.9711 0.03280 0.02661 0.0007 0.6933 0.0267
-9.500 -0.9553 0.03098 0.02459 0.0020 0.6912 0.0268
-9.250 -0.9325 0.03124 0.02514 0.0019 0.6888 0.0290
-9.000 -0.9163 0.02882 0.02240 0.0035 0.6869 0.0286
-8.750 -0.8970 0.02736 0.02074 0.0046 0.6847 0.0287
-8.500 -0.8762 0.02558 0.01870 0.0056 0.6831 0.0283
-8.250 -0.8540 0.02479 0.01786 0.0063 0.6815 0.0288
-8.000 -0.8303 0.02323 0.01609 0.0069 0.6798 0.0283
-7.750 -0.8074 0.02260 0.01544 0.0075 0.6780 0.0290
-7.500 -0.7835 0.02174 0.01449 0.0081 0.6765 0.0294
-7.250 -0.7593 0.02090 0.01356 0.0086 0.6752 0.0297
-7.000 -0.7352 0.02021 0.01280 0.0092 0.6740 0.0302
-6.750 -0.7105 0.01932 0.01184 0.0097 0.6729 0.0302
-6.500 -0.6861 0.01839 0.01084 0.0103 0.6718 0.0297
-6.250 -0.6628 0.01754 0.00990 0.0112 0.6708 0.0292
-6.000 -0.6402 0.01684 0.00913 0.0121 0.6694 0.0287
-5.750 -0.6179 0.01624 0.00847 0.0132 0.6679 0.0283
-5.500 -0.5955 0.01569 0.00788 0.0142 0.6666 0.0280
-5.250 -0.5729 0.01519 0.00734 0.0152 0.6652 0.0277
-5.000 -0.5500 0.01476 0.00687 0.0161 0.6636 0.0275
-4.750 -0.5267 0.01435 0.00644 0.0170 0.6621 0.0274
-4.500 -0.5033 0.01397 0.00603 0.0179 0.6609 0.0273
-4.250 -0.4794 0.01363 0.00566 0.0186 0.6597 0.0272
-4.000 -0.4552 0.01330 0.00531 0.0194 0.6582 0.0271
-3.750 -0.4310 0.01300 0.00496 0.0201 0.6551 0.0272
-3.500 -0.4063 0.01274 0.00465 0.0208 0.6518 0.0273
-3.250 -0.3811 0.01244 0.00435 0.0214 0.6484 0.0275
-3.000 -0.3556 0.01219 0.00408 0.0220 0.6457 0.0279
-2.750 -0.3298 0.01197 0.00382 0.0225 0.6418 0.0284
-2.500 -0.3042 0.01181 0.00360 0.0230 0.6366 0.0293
-2.250 -0.2780 0.01156 0.00337 0.0235 0.6309 0.0307
-2.000 -0.2519 0.01135 0.00317 0.0239 0.6262 0.0356
-1.750 -0.2265 0.01111 0.00303 0.0245 0.6217 0.0658
-1.500 -0.2000 0.01090 0.00287 0.0249 0.6164 0.0782
-1.250 -0.1752 0.01053 0.00268 0.0254 0.6112 0.1249
-1.000 -0.1602 0.00931 0.00229 0.0275 0.6068 0.3679
-0.750 -0.1351 0.00901 0.00217 0.0280 0.6013 0.4122
-0.500 -0.1154 0.00834 0.00197 0.0295 0.5938 0.5120
-0.250 -0.0940 0.00793 0.00191 0.0309 0.5835 0.6078
0.000 -0.0693 0.00771 0.00184 0.0317 0.5688 0.6496
0.250 -0.0478 0.00785 0.00166 0.0330 0.4172 0.6781
0.500 -0.0251 0.00820 0.00187 0.0339 0.3566 0.7020
0.750 -0.0010 0.00836 0.00196 0.0346 0.3096 0.7260
1.250 0.0471 0.00851 0.00215 0.0363 0.2718 0.7844
1.500 0.0713 0.00854 0.00228 0.0372 0.2605 0.8169
1.750 0.0965 0.00862 0.00240 0.0379 0.2500 0.8409
2.000 0.1231 0.00871 0.00250 0.0383 0.2361 0.8559
2.250 0.1501 0.00879 0.00257 0.0386 0.2129 0.8703
2.500 0.1742 0.00920 0.00272 0.0392 0.1463 0.8862
2.750 0.1990 0.00962 0.00296 0.0397 0.1015 0.9019
3.000 0.2274 0.00986 0.00318 0.0396 0.0937 0.9143
3.250 0.2560 0.01008 0.00341 0.0395 0.0911 0.9252
3.500 0.2849 0.01036 0.00369 0.0393 0.0882 0.9350
3.750 0.3168 0.01071 0.00402 0.0383 0.0845 0.9420
4.000 0.3473 0.01105 0.00436 0.0377 0.0821 0.9501
4.250 0.3806 0.01133 0.00466 0.0364 0.0806 0.9556
4.500 0.4167 0.01167 0.00501 0.0345 0.0789 0.9595
4.750 0.4504 0.01203 0.00537 0.0331 0.0771 0.9646
5.000 0.4831 0.01243 0.00576 0.0318 0.0749 0.9691
5.250 0.5189 0.01297 0.00627 0.0297 0.0725 0.9714
5.500 0.5522 0.01365 0.00697 0.0281 0.0706 0.9747
5.750 0.5863 0.01379 0.00713 0.0266 0.0696 0.9788
6.000 0.6202 0.01397 0.00733 0.0251 0.0682 0.9824
6.250 0.6585 0.01417 0.00755 0.0227 0.0662 0.9846
6.500 0.6962 0.01438 0.00777 0.0203 0.0642 0.9876
6.750 0.7318 0.01461 0.00798 0.0184 0.0623 0.9910
7.000 0.7644 0.01516 0.00852 0.0168 0.0600 0.9940
7.250 0.8027 0.01511 0.00852 0.0144 0.0588 0.9962
7.500 0.8409 0.01516 0.00860 0.0120 0.0573 0.9987
7.750 0.8722 0.01520 0.00865 0.0110 0.0552 1.0000
8.000 0.8919 0.01528 0.00876 0.0123 0.0536 1.0000
8.250 0.9115 0.01538 0.00884 0.0137 0.0518 1.0000
8.500 0.9304 0.01556 0.00902 0.0151 0.0501 1.0000
8.750 0.9490 0.01576 0.00928 0.0167 0.0484 1.0000
9.000 0.9681 0.01594 0.00946 0.0181 0.0444 1.0000
9.250 0.9864 0.01620 0.00959 0.0196 0.0290 1.0000
9.500 0.9980 0.01698 0.01030 0.0220 0.0239 1.0000
9.750 1.0116 0.01760 0.01095 0.0242 0.0225 1.0000
10.000 1.0263 0.01813 0.01154 0.0262 0.0217 1.0000
10.250 1.0407 0.01870 0.01217 0.0282 0.0209 1.0000
10.500 1.0545 0.01930 0.01287 0.0303 0.0204 1.0000
10.750 1.0672 0.01997 0.01363 0.0324 0.0199 1.0000
11.000 1.0789 0.02069 0.01443 0.0347 0.0195 1.0000
11.250 1.0875 0.02158 0.01542 0.0372 0.0189 1.0000
11.500 1.0899 0.02257 0.01649 0.0406 0.0184 1.0000
11.750 1.0896 0.02360 0.01760 0.0441 0.0181 1.0000
12.000 1.0874 0.02499 0.01907 0.0470 0.0177 1.0000
12.250 1.0862 0.02664 0.02081 0.0491 0.0173 1.0000
12.500 1.0910 0.02805 0.02232 0.0504 0.0171 1.0000
12.750 1.0955 0.02962 0.02399 0.0515 0.0168 1.0000
13.000 1.0980 0.03144 0.02591 0.0524 0.0165 1.0000
13.250 1.0997 0.03343 0.02800 0.0530 0.0164 1.0000
13.500 1.0992 0.03569 0.03034 0.0535 0.0160 1.0000
13.750 1.0971 0.03816 0.03291 0.0539 0.0157 1.0000
14.000 1.0948 0.04075 0.03558 0.0541 0.0155 1.0000
14.250 1.0883 0.04384 0.03876 0.0540 0.0152 1.0000
14.500 1.0825 0.04698 0.04198 0.0538 0.0150 1.0000
14.750 1.0741 0.05050 0.04556 0.0533 0.0147 1.0000
15.000 1.0656 0.05414 0.04926 0.0528 0.0145 1.0000
15.250 1.0584 0.05759 0.05272 0.0528 0.0142 1.0000
15.500 1.0507 0.06180 0.05708 0.0509 0.0140 1.0000
15.750 1.0426 0.06675 0.06220 0.0480 0.0139 1.0000
16.000 1.0358 0.07187 0.06746 0.0450 0.0137 1.0000
16.250 1.0287 0.07717 0.07289 0.0419 0.0136 1.0000
16.500 1.0180 0.08316 0.07903 0.0383 0.0134 1.0000
16.750 1.0108 0.08815 0.08411 0.0357 0.0134 1.0000
17.000 0.9994 0.09412 0.09020 0.0325 0.0132 1.0000
17.250 0.9902 0.09952 0.09569 0.0297 0.0132 1.0000
17.500 0.9786 0.10559 0.10187 0.0263 0.0131 1.0000
17.750 0.9685 0.11127 0.10765 0.0234 0.0131 1.0000
18.000 0.9581 0.11718 0.11366 0.0202 0.0130 1.0000
18.250 0.9467 0.12349 0.12008 0.0168 0.0129 1.0000
18.500 0.9352 0.13002 0.12671 0.0133 0.0129 1.0000
18.750 0.9236 0.13678 0.13356 0.0095 0.0126 1.0000
19.000 0.9099 0.14417 0.14106 0.0054 0.0129 1.0000
19.250 0.8963 0.15185 0.14886 0.0011 0.0129 1.0000
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