BOEING 707 .08 SPAN AIRFOIL (b707a-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: BOEING 707 .08 SPAN AIRFOIL (b707a-il) Reynolds number: 200,000 Max Cl/Cd: 43.13 at α=8.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-b707a-il-200000.txt Download as CSV file: xf-b707a-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.250 -0.8066 0.09861 0.09436 -0.0147 1.0000 0.0406
-13.000 -0.7894 0.09766 0.09348 -0.0130 1.0000 0.0402
-12.750 -0.9256 0.07336 0.06851 -0.0302 1.0000 0.0360
-12.500 -0.9288 0.06975 0.06486 -0.0310 1.0000 0.0358
-12.250 -0.9373 0.06603 0.06106 -0.0319 1.0000 0.0356
-12.000 -0.9513 0.06214 0.05704 -0.0325 1.0000 0.0353
-11.750 -0.9664 0.05853 0.05328 -0.0322 1.0000 0.0350
-11.500 -0.9828 0.05511 0.04968 -0.0308 1.0000 0.0347
-11.250 -0.9991 0.05197 0.04633 -0.0281 1.0000 0.0342
-11.000 -1.0184 0.04815 0.04219 -0.0243 1.0000 0.0335
-10.750 -1.0483 0.04007 0.03309 -0.0193 1.0000 0.0318
-10.500 -1.0389 0.03753 0.03033 -0.0175 1.0000 0.0318
-10.250 -1.0266 0.03515 0.02774 -0.0158 1.0000 0.0318
-10.000 -1.0119 0.03291 0.02528 -0.0142 1.0000 0.0318
-9.750 -0.9953 0.03111 0.02336 -0.0128 1.0000 0.0321
-9.500 -0.9782 0.02969 0.02189 -0.0114 1.0000 0.0323
-9.250 -0.9614 0.02857 0.02073 -0.0099 1.0000 0.0327
-9.000 -0.9443 0.02742 0.01953 -0.0083 1.0000 0.0331
-8.750 -0.9273 0.02634 0.01840 -0.0066 1.0000 0.0337
-8.500 -0.9103 0.02526 0.01726 -0.0049 1.0000 0.0345
-8.250 -0.8939 0.02412 0.01605 -0.0030 1.0000 0.0354
-8.000 -0.8780 0.02312 0.01501 -0.0010 1.0000 0.0364
-7.750 -0.8607 0.02249 0.01441 0.0007 1.0000 0.0375
-7.500 -0.8435 0.02176 0.01365 0.0026 1.0000 0.0393
-7.250 -0.8268 0.02098 0.01284 0.0045 1.0000 0.0414
-7.000 -0.8086 0.02039 0.01224 0.0063 1.0000 0.0444
-6.750 -0.7909 0.01973 0.01159 0.0081 1.0000 0.0485
-6.500 -0.7723 0.01915 0.01100 0.0098 1.0000 0.0551
-6.250 -0.7528 0.01868 0.01050 0.0112 1.0000 0.0634
-6.000 -0.7345 0.01806 0.00990 0.0129 1.0000 0.0697
-5.750 -0.7155 0.01749 0.00931 0.0144 1.0000 0.0751
-5.500 -0.6958 0.01699 0.00881 0.0159 1.0000 0.0800
-5.250 -0.6761 0.01646 0.00827 0.0174 1.0000 0.0836
-5.000 -0.6568 0.01588 0.00772 0.0189 1.0000 0.0870
-4.750 -0.6357 0.01548 0.00729 0.0202 1.0000 0.0908
-4.500 -0.6149 0.01501 0.00682 0.0216 1.0000 0.0937
-4.250 -0.5942 0.01453 0.00636 0.0229 1.0000 0.0976
-4.000 -0.5722 0.01418 0.00598 0.0241 1.0000 0.1017
-3.750 -0.5505 0.01377 0.00560 0.0253 1.0000 0.1071
-3.500 -0.5286 0.01336 0.00526 0.0265 1.0000 0.1172
-3.250 -0.5102 0.01241 0.00478 0.0280 1.0000 0.1929
-3.000 -0.4935 0.01148 0.00462 0.0297 1.0000 0.3828
-2.750 -0.4700 0.01153 0.00473 0.0309 1.0000 0.4162
-2.500 -0.4388 0.01163 0.00484 0.0305 0.9974 0.4391
-2.250 -0.3897 0.01174 0.00498 0.0263 0.9858 0.4595
-2.000 -0.3437 0.01171 0.00500 0.0229 0.9718 0.4739
-1.750 -0.3030 0.01169 0.00492 0.0206 0.9549 0.4845
-1.500 -0.2687 0.01144 0.00478 0.0198 0.9251 0.4923
-1.250 -0.1792 0.01197 0.00440 0.0084 0.6334 0.5065
-1.000 -0.1575 0.01231 0.00434 0.0099 0.5388 0.5117
-0.750 -0.1331 0.01250 0.00433 0.0108 0.4893 0.5177
-0.500 -0.1074 0.01262 0.00428 0.0115 0.4509 0.5231
0.250 -0.0295 0.01280 0.00419 0.0133 0.3946 0.5410
0.500 -0.0035 0.01294 0.00422 0.0138 0.3826 0.5478
0.750 0.0222 0.01306 0.00429 0.0144 0.3703 0.5540
1.000 0.0485 0.01325 0.00442 0.0148 0.3569 0.5591
1.250 0.0752 0.01344 0.00455 0.0152 0.3436 0.5629
1.500 0.1020 0.01369 0.00472 0.0155 0.3301 0.5668
1.750 0.1286 0.01389 0.00491 0.0158 0.3168 0.5711
2.000 0.1551 0.01404 0.00508 0.0162 0.3034 0.5764
2.250 0.1815 0.01412 0.00520 0.0167 0.2897 0.5833
2.500 0.2080 0.01404 0.00523 0.0172 0.2753 0.5911
2.750 0.2346 0.01378 0.00519 0.0178 0.2575 0.6010
3.000 0.2616 0.01349 0.00502 0.0183 0.2394 0.6134
3.250 0.2876 0.01329 0.00482 0.0189 0.2249 0.6302
3.500 0.3118 0.01333 0.00489 0.0198 0.2102 0.6539
3.750 0.3344 0.01348 0.00516 0.0209 0.1962 0.6946
4.000 0.3569 0.01342 0.00545 0.0224 0.1842 0.7666
4.250 0.3970 0.01343 0.00587 0.0206 0.1707 0.8816
4.500 0.4601 0.01379 0.00624 0.0136 0.1524 0.9573
4.750 0.5110 0.01407 0.00651 0.0089 0.1339 0.9859
5.000 0.5564 0.01448 0.00682 0.0052 0.1177 1.0000
5.250 0.5772 0.01487 0.00714 0.0066 0.1094 1.0000
5.500 0.5979 0.01529 0.00746 0.0079 0.1033 1.0000
5.750 0.6200 0.01560 0.00781 0.0091 0.0974 1.0000
6.000 0.6413 0.01600 0.00814 0.0104 0.0936 1.0000
6.250 0.6636 0.01635 0.00855 0.0116 0.0901 1.0000
6.500 0.6856 0.01672 0.00893 0.0128 0.0873 1.0000
6.750 0.7075 0.01712 0.00930 0.0139 0.0846 1.0000
7.000 0.7301 0.01744 0.00969 0.0150 0.0813 1.0000
7.250 0.7522 0.01780 0.01005 0.0161 0.0787 1.0000
7.500 0.7741 0.01820 0.01047 0.0172 0.0760 1.0000
7.750 0.7964 0.01857 0.01089 0.0183 0.0730 1.0000
8.000 0.8175 0.01903 0.01132 0.0194 0.0701 1.0000
8.250 0.8395 0.01948 0.01188 0.0206 0.0679 1.0000
8.500 0.8608 0.01996 0.01239 0.0217 0.0651 1.0000
8.750 0.8814 0.02054 0.01302 0.0229 0.0624 1.0000
9.000 0.9023 0.02108 0.01365 0.0240 0.0594 1.0000
9.250 0.9221 0.02174 0.01436 0.0252 0.0559 1.0000
9.500 0.9415 0.02242 0.01510 0.0265 0.0526 1.0000
9.750 0.9610 0.02313 0.01595 0.0277 0.0488 1.0000
10.000 0.9797 0.02389 0.01684 0.0290 0.0450 1.0000
10.250 0.9981 0.02468 0.01774 0.0304 0.0411 1.0000
10.500 1.0159 0.02550 0.01866 0.0317 0.0379 1.0000
10.750 1.0318 0.02649 0.01979 0.0333 0.0354 1.0000
11.000 1.0476 0.02740 0.02076 0.0348 0.0338 1.0000
11.250 1.0604 0.02856 0.02204 0.0366 0.0325 1.0000
11.500 1.0718 0.02975 0.02334 0.0384 0.0315 1.0000
11.750 1.0816 0.03098 0.02467 0.0403 0.0309 1.0000
12.000 1.0896 0.03223 0.02599 0.0423 0.0303 1.0000
12.250 1.0922 0.03359 0.02743 0.0448 0.0300 1.0000
12.500 1.0896 0.03529 0.02925 0.0476 0.0296 1.0000
12.750 1.0849 0.03731 0.03141 0.0497 0.0294 1.0000
13.000 1.0772 0.03989 0.03414 0.0508 0.0292 1.0000
13.250 1.0666 0.04335 0.03777 0.0501 0.0291 1.0000
13.500 1.0530 0.04829 0.04289 0.0469 0.0291 1.0000
13.750 1.0380 0.05432 0.04910 0.0424 0.0291 1.0000
14.000 1.0201 0.06120 0.05615 0.0375 0.0291 1.0000
14.250 0.9991 0.06853 0.06362 0.0326 0.0291 1.0000
14.500 0.9764 0.07576 0.07098 0.0281 0.0293 1.0000
14.750 0.9490 0.08390 0.07925 0.0231 0.0295 1.0000
15.000 0.9218 0.09232 0.08780 0.0181 0.0297 1.0000
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