BOEING 707 .19 SPAN AIRFOIL (b707b-il) Xfoil prediction polar at RE=200,000 Ncrit=9
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Airfoil: BOEING 707 .19 SPAN AIRFOIL (b707b-il) Reynolds number: 200,000 Max Cl/Cd: 39.07 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-b707b-il-200000.txt Download as CSV file: xf-b707b-il-200000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.500 -0.6497 0.12301 0.11968 0.0079 1.0000 0.0702
-12.250 -0.6413 0.12012 0.11679 0.0075 1.0000 0.0722
-12.000 -0.6411 0.11562 0.11231 0.0054 1.0000 0.0741
-11.750 -0.6487 0.10960 0.10633 0.0014 1.0000 0.0766
-11.500 -0.6859 0.09725 0.09404 -0.0099 1.0000 0.0784
-11.250 -0.7142 0.08890 0.08567 -0.0161 1.0000 0.0784
-11.000 -0.7489 0.08244 0.07914 -0.0202 1.0000 0.0785
-10.750 -0.7737 0.07768 0.07431 -0.0214 1.0000 0.0784
-10.500 -0.8037 0.07423 0.07075 -0.0203 1.0000 0.0786
-10.250 -0.8402 0.07250 0.06866 -0.0175 0.8920 0.0793
-10.000 -0.8602 0.07164 0.06723 -0.0138 0.8436 0.0797
-9.750 -0.8587 0.06284 0.05837 -0.0146 0.8307 0.0813
-9.500 -0.8358 0.05928 0.05489 -0.0155 0.8208 0.0831
-9.250 -0.8273 0.05675 0.05223 -0.0144 0.8129 0.0849
-9.000 -0.8236 0.05431 0.04960 -0.0125 0.8064 0.0868
-8.750 -0.8229 0.05252 0.04747 -0.0098 0.8006 0.0905
-7.750 -0.7839 0.03538 0.02816 0.0007 0.7841 0.0542
-7.500 -0.7639 0.03252 0.02502 0.0017 0.7805 0.0517
-7.250 -0.7422 0.02945 0.02125 0.0036 0.7776 0.0475
-7.000 -0.7175 0.02880 0.02040 0.0044 0.7744 0.0467
-6.750 -0.6894 0.02658 0.01808 0.0041 0.7718 0.0462
-6.500 -0.6616 0.02495 0.01635 0.0040 0.7698 0.0457
-6.250 -0.6336 0.02355 0.01486 0.0040 0.7681 0.0453
-6.000 -0.6060 0.02234 0.01358 0.0040 0.7666 0.0451
-5.750 -0.5795 0.02130 0.01249 0.0043 0.7650 0.0449
-5.500 -0.5547 0.02038 0.01153 0.0048 0.7635 0.0450
-5.250 -0.5311 0.01955 0.01069 0.0056 0.7616 0.0452
-5.000 -0.5089 0.01882 0.00995 0.0065 0.7593 0.0456
-4.750 -0.4874 0.01817 0.00928 0.0076 0.7570 0.0461
-4.500 -0.4659 0.01761 0.00868 0.0087 0.7553 0.0467
-4.250 -0.4456 0.01699 0.00807 0.0100 0.7539 0.0481
-4.000 -0.4231 0.01657 0.00765 0.0109 0.7527 0.0501
-3.750 -0.4000 0.01623 0.00727 0.0117 0.7511 0.0534
-3.500 -0.3772 0.01586 0.00689 0.0128 0.7491 0.0595
-3.250 -0.3549 0.01547 0.00648 0.0138 0.7474 0.0764
-3.000 -0.3363 0.01462 0.00603 0.0152 0.7457 0.1593
-2.750 -0.3291 0.01301 0.00559 0.0183 0.7438 0.4218
-2.500 -0.3141 0.01235 0.00553 0.0207 0.7411 0.5283
-2.250 -0.2935 0.01213 0.00557 0.0224 0.7380 0.6070
-2.000 -0.2698 0.01204 0.00554 0.0236 0.7340 0.6428
-1.750 -0.2466 0.01198 0.00556 0.0250 0.7290 0.6799
-1.500 -0.2217 0.01189 0.00553 0.0259 0.7227 0.7042
-1.250 -0.1968 0.01185 0.00548 0.0270 0.7172 0.7262
-1.000 -0.1714 0.01182 0.00551 0.0279 0.7122 0.7485
-0.750 -0.1463 0.01179 0.00556 0.0290 0.7058 0.7748
-0.250 -0.0947 0.01172 0.00553 0.0311 0.6890 0.8157
0.000 -0.0701 0.01180 0.00562 0.0327 0.6813 0.8426
0.250 -0.0411 0.01189 0.00576 0.0335 0.6722 0.8622
0.500 -0.0136 0.01187 0.00573 0.0342 0.6625 0.8754
0.750 0.0181 0.01191 0.00570 0.0341 0.6521 0.8863
1.000 0.0510 0.01190 0.00569 0.0337 0.6391 0.8961
1.250 0.0812 0.01187 0.00568 0.0338 0.6260 0.9074
1.500 0.1192 0.01183 0.00561 0.0322 0.6079 0.9130
1.750 0.1492 0.01170 0.00551 0.0321 0.5810 0.9227
2.000 0.1847 0.01193 0.00511 0.0308 0.4064 0.9274
2.250 0.2152 0.01245 0.00541 0.0300 0.3643 0.9359
2.500 0.2546 0.01280 0.00565 0.0274 0.3319 0.9404
2.750 0.2946 0.01311 0.00583 0.0248 0.3047 0.9449
3.000 0.3249 0.01343 0.00601 0.0240 0.2799 0.9536
3.250 0.3660 0.01380 0.00626 0.0210 0.2541 0.9574
3.500 0.4042 0.01404 0.00640 0.0187 0.1953 0.9639
3.750 0.4390 0.01475 0.00669 0.0166 0.1412 0.9706
4.000 0.4780 0.01519 0.00703 0.0139 0.1260 0.9764
4.250 0.5142 0.01559 0.00737 0.0118 0.1194 0.9829
4.500 0.5548 0.01587 0.00764 0.0087 0.1134 0.9880
4.750 0.5926 0.01635 0.00801 0.0060 0.1077 0.9940
5.000 0.6346 0.01661 0.00831 0.0026 0.1036 0.9992
5.250 0.6553 0.01692 0.00863 0.0034 0.1019 1.0000
5.500 0.6717 0.01724 0.00895 0.0050 0.1005 1.0000
5.750 0.6880 0.01761 0.00932 0.0067 0.0991 1.0000
6.000 0.7041 0.01806 0.00975 0.0084 0.0975 1.0000
6.250 0.7192 0.01879 0.01041 0.0103 0.0950 1.0000
6.500 0.7364 0.01909 0.01079 0.0119 0.0933 1.0000
6.750 0.7535 0.01949 0.01123 0.0135 0.0916 1.0000
7.000 0.7706 0.01994 0.01173 0.0152 0.0901 1.0000
7.250 0.7877 0.02043 0.01226 0.0168 0.0887 1.0000
7.500 0.8051 0.02095 0.01280 0.0184 0.0874 1.0000
7.750 0.8224 0.02153 0.01337 0.0200 0.0859 1.0000
8.000 0.8402 0.02223 0.01407 0.0214 0.0847 1.0000
8.250 0.8588 0.02314 0.01501 0.0227 0.0833 1.0000
8.500 0.8768 0.02391 0.01586 0.0241 0.0821 1.0000
8.750 0.8935 0.02421 0.01629 0.0257 0.0805 1.0000
9.000 0.9104 0.02462 0.01681 0.0273 0.0785 1.0000
9.250 0.9270 0.02509 0.01737 0.0289 0.0765 1.0000
9.500 0.9438 0.02563 0.01796 0.0303 0.0747 1.0000
9.750 0.9612 0.02629 0.01863 0.0316 0.0729 1.0000
10.000 0.9798 0.02743 0.01977 0.0326 0.0712 1.0000
10.250 0.9949 0.02803 0.02054 0.0342 0.0699 1.0000
10.500 1.0071 0.02818 0.02088 0.0364 0.0677 1.0000
10.750 1.0191 0.02851 0.02138 0.0384 0.0651 1.0000
11.000 1.0309 0.02884 0.02178 0.0404 0.0626 1.0000
11.250 1.0420 0.02934 0.02224 0.0423 0.0602 1.0000
11.500 1.0480 0.02967 0.02283 0.0451 0.0579 1.0000
11.750 1.0536 0.03004 0.02341 0.0479 0.0547 1.0000
12.000 1.0606 0.03034 0.02379 0.0499 0.0516 1.0000
12.250 1.0718 0.03092 0.02458 0.0513 0.0467 1.0000
12.500 1.0844 0.03139 0.02514 0.0523 0.0414 1.0000
12.750 1.0960 0.03212 0.02589 0.0531 0.0365 1.0000
13.000 1.1043 0.03328 0.02704 0.0539 0.0337 1.0000
13.250 1.1094 0.03485 0.02866 0.0547 0.0319 1.0000
13.500 1.1112 0.03679 0.03062 0.0554 0.0303 1.0000
13.750 1.1102 0.03909 0.03301 0.0559 0.0292 1.0000
14.000 1.1087 0.04150 0.03556 0.0563 0.0286 1.0000
14.250 1.1029 0.04445 0.03865 0.0564 0.0276 1.0000
14.500 1.0958 0.04766 0.04198 0.0561 0.0270 1.0000
14.750 1.0866 0.05125 0.04571 0.0555 0.0267 1.0000
15.000 1.0727 0.05565 0.05024 0.0542 0.0262 1.0000
15.250 1.0611 0.06014 0.05489 0.0524 0.0262 1.0000
15.500 1.0457 0.06575 0.06066 0.0496 0.0261 1.0000
15.750 1.0273 0.07289 0.06797 0.0453 0.0259 1.0000
16.000 1.0091 0.08015 0.07539 0.0410 0.0260 1.0000
16.250 0.9893 0.08773 0.08314 0.0367 0.0261 1.0000
16.500 0.9652 0.09609 0.09165 0.0320 0.0262 1.0000
16.750 0.9386 0.10504 0.10079 0.0272 0.0267 1.0000
17.000 0.8958 0.11772 0.11368 0.0203 0.0274 1.0000
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