BOEING 737 ROOT AIRFOIL (b737a-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: BOEING 737 ROOT AIRFOIL (b737a-il) Reynolds number: 500,000 Max Cl/Cd: 68.25 at α=8.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-b737a-il-500000-n5.txt Download as CSV file: xf-b737a-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: BOEING 737 ROOT 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
------ -------- --------- --------- -------- -------- --------
-17.500 -1.1900 0.08508 0.08016 -0.0070 1.0000 0.0284
-17.250 -1.2183 0.07709 0.07204 -0.0110 1.0000 0.0285
-17.000 -1.2483 0.06875 0.06353 -0.0153 1.0000 0.0285
-16.750 -1.2745 0.06093 0.05554 -0.0195 1.0000 0.0286
-16.500 -1.2941 0.05430 0.04874 -0.0230 1.0000 0.0287
-16.250 -1.3074 0.04894 0.04324 -0.0258 1.0000 0.0289
-16.000 -1.3152 0.04462 0.03879 -0.0277 1.0000 0.0291
-15.750 -1.3188 0.04107 0.03513 -0.0290 1.0000 0.0294
-15.500 -1.3189 0.03812 0.03207 -0.0298 1.0000 0.0297
-15.250 -1.3162 0.03559 0.02944 -0.0303 1.0000 0.0300
-15.000 -1.3136 0.03318 0.02695 -0.0305 1.0000 0.0304
-14.750 -1.3087 0.03109 0.02479 -0.0305 1.0000 0.0308
-14.500 -1.3013 0.02934 0.02297 -0.0303 1.0000 0.0312
-14.250 -1.2921 0.02785 0.02142 -0.0298 1.0000 0.0317
-14.000 -1.2814 0.02656 0.02007 -0.0291 1.0000 0.0323
-13.750 -1.2698 0.02546 0.01890 -0.0282 1.0000 0.0329
-13.500 -1.2568 0.02454 0.01792 -0.0270 1.0000 0.0335
-13.250 -1.2447 0.02362 0.01695 -0.0255 1.0000 0.0341
-13.000 -1.2308 0.02280 0.01610 -0.0240 1.0000 0.0348
-12.750 -1.2135 0.02207 0.01533 -0.0228 1.0000 0.0355
-12.500 -1.1947 0.02142 0.01464 -0.0217 1.0000 0.0363
-12.250 -1.1747 0.02083 0.01401 -0.0207 1.0000 0.0371
-12.000 -1.1548 0.02021 0.01336 -0.0197 1.0000 0.0380
-11.750 -1.1344 0.01959 0.01273 -0.0187 1.0000 0.0389
-11.500 -1.1129 0.01906 0.01217 -0.0178 1.0000 0.0400
-11.250 -1.0905 0.01859 0.01166 -0.0169 1.0000 0.0411
-11.000 -1.0685 0.01807 0.01112 -0.0160 1.0000 0.0422
-10.750 -1.0462 0.01756 0.01059 -0.0150 1.0000 0.0436
-10.500 -1.0233 0.01712 0.01012 -0.0142 1.0000 0.0452
-10.250 -1.0009 0.01661 0.00960 -0.0132 1.0000 0.0470
-10.000 -0.9784 0.01612 0.00910 -0.0122 1.0000 0.0494
-9.750 -0.9570 0.01552 0.00850 -0.0111 1.0000 0.0533
-9.500 -0.9344 0.01505 0.00829 -0.0102 1.0000 0.0845
-9.250 -0.9085 0.01494 0.00815 -0.0095 1.0000 0.0895
-9.000 -0.8833 0.01479 0.00801 -0.0087 1.0000 0.0923
-8.750 -0.8581 0.01465 0.00786 -0.0079 1.0000 0.0946
-8.500 -0.8293 0.01453 0.00771 -0.0078 0.9978 0.0963
-8.250 -0.7939 0.01423 0.00743 -0.0093 0.9860 0.0979
-8.000 -0.7566 0.01396 0.00718 -0.0110 0.9609 0.0995
-7.750 -0.7119 0.01373 0.00690 -0.0142 0.9132 0.1011
-7.500 -0.6804 0.01361 0.00664 -0.0144 0.8677 0.1022
-7.000 -0.6280 0.01351 0.00627 -0.0130 0.8133 0.1037
-6.750 -0.6022 0.01334 0.00601 -0.0123 0.7913 0.1045
-6.500 -0.5763 0.01312 0.00574 -0.0117 0.7721 0.1055
-6.250 -0.5496 0.01292 0.00551 -0.0112 0.7561 0.1062
-6.000 -0.5226 0.01275 0.00529 -0.0107 0.7428 0.1069
-5.750 -0.4955 0.01259 0.00509 -0.0103 0.7292 0.1075
-5.500 -0.4681 0.01243 0.00490 -0.0099 0.7157 0.1081
-5.250 -0.4408 0.01230 0.00471 -0.0094 0.6989 0.1088
-5.000 -0.4136 0.01218 0.00453 -0.0090 0.6801 0.1096
-4.750 -0.3862 0.01207 0.00436 -0.0086 0.6603 0.1104
-4.500 -0.3587 0.01198 0.00419 -0.0081 0.6378 0.1110
-4.250 -0.3313 0.01190 0.00403 -0.0077 0.6131 0.1115
-4.000 -0.3040 0.01182 0.00388 -0.0073 0.5877 0.1116
-3.750 -0.2768 0.01175 0.00372 -0.0069 0.5564 0.1120
-3.500 -0.2500 0.01175 0.00357 -0.0064 0.5129 0.1123
-3.250 -0.2242 0.01189 0.00345 -0.0058 0.4366 0.1127
-3.000 -0.1984 0.01211 0.00338 -0.0053 0.3568 0.1132
-2.750 -0.1716 0.01222 0.00332 -0.0049 0.3104 0.1137
-2.500 -0.1443 0.01226 0.00327 -0.0046 0.2845 0.1143
-2.250 -0.1166 0.01227 0.00322 -0.0043 0.2663 0.1149
-2.000 -0.0888 0.01228 0.00317 -0.0040 0.2518 0.1157
-1.750 -0.0610 0.01230 0.00313 -0.0037 0.2390 0.1166
-1.500 -0.0329 0.01229 0.00310 -0.0035 0.2300 0.1176
-1.250 -0.0050 0.01231 0.00308 -0.0032 0.2217 0.1189
-1.000 0.0231 0.01229 0.00306 -0.0029 0.2158 0.1209
-0.750 0.0509 0.01226 0.00303 -0.0027 0.2097 0.1249
-0.500 0.0776 0.01209 0.00299 -0.0023 0.2037 0.1574
-0.250 0.1054 0.01202 0.00303 -0.0021 0.1994 0.1896
0.000 0.1335 0.01203 0.00307 -0.0019 0.1952 0.1986
0.250 0.1616 0.01208 0.00311 -0.0016 0.1904 0.2049
0.500 0.1895 0.01212 0.00317 -0.0014 0.1854 0.2119
0.750 0.2178 0.01215 0.00321 -0.0012 0.1810 0.2182
1.000 0.2458 0.01219 0.00327 -0.0010 0.1767 0.2244
1.250 0.2737 0.01224 0.00333 -0.0008 0.1730 0.2332
1.500 0.3018 0.01230 0.00341 -0.0005 0.1700 0.2400
1.750 0.3298 0.01232 0.00348 -0.0004 0.1674 0.2494
2.000 0.3578 0.01236 0.00357 -0.0001 0.1645 0.2601
2.500 0.4129 0.01241 0.00374 0.0003 0.1585 0.3033
2.750 0.4401 0.01230 0.00382 0.0005 0.1556 0.3580
3.000 0.4659 0.01193 0.00388 0.0008 0.1520 0.4843
3.250 0.4919 0.01177 0.00402 0.0013 0.1482 0.5774
3.500 0.5187 0.01183 0.00420 0.0016 0.1447 0.6249
3.750 0.5464 0.01190 0.00436 0.0019 0.1419 0.6501
4.000 0.5741 0.01201 0.00453 0.0022 0.1389 0.6707
4.250 0.6014 0.01214 0.00470 0.0025 0.1359 0.6888
4.500 0.6287 0.01229 0.00489 0.0028 0.1329 0.7049
4.750 0.6563 0.01242 0.00506 0.0030 0.1298 0.7196
5.000 0.6836 0.01257 0.00525 0.0033 0.1262 0.7333
5.250 0.7106 0.01275 0.00545 0.0036 0.1231 0.7467
5.500 0.7380 0.01291 0.00565 0.0039 0.1201 0.7596
5.750 0.7648 0.01308 0.00585 0.0042 0.1166 0.7710
6.000 0.7916 0.01329 0.00607 0.0045 0.1135 0.7825
6.250 0.8183 0.01345 0.00630 0.0049 0.1105 0.7948
6.500 0.8447 0.01365 0.00653 0.0053 0.1076 0.8074
6.750 0.8707 0.01387 0.00678 0.0057 0.1048 0.8225
7.000 0.8964 0.01404 0.00703 0.0062 0.1018 0.8396
7.250 0.9215 0.01423 0.00729 0.0068 0.0991 0.8605
7.500 0.9454 0.01441 0.00757 0.0077 0.0967 0.8936
7.750 0.9802 0.01462 0.00789 0.0064 0.0942 0.9616
8.000 1.0117 0.01493 0.00821 0.0055 0.0918 1.0000
8.250 1.0368 0.01528 0.00853 0.0059 0.0897 1.0000
8.500 1.0621 0.01560 0.00886 0.0062 0.0880 1.0000
8.750 1.0873 0.01593 0.00920 0.0066 0.0861 1.0000
9.000 1.1120 0.01630 0.00956 0.0070 0.0837 1.0000
9.250 1.1363 0.01670 0.00995 0.0074 0.0817 1.0000
9.500 1.1609 0.01705 0.01033 0.0078 0.0799 1.0000
9.750 1.1851 0.01744 0.01073 0.0083 0.0778 1.0000
10.000 1.2085 0.01789 0.01118 0.0087 0.0756 1.0000
10.250 1.2322 0.01829 0.01161 0.0092 0.0735 1.0000
10.500 1.2553 0.01873 0.01207 0.0097 0.0706 1.0000
10.750 1.2777 0.01923 0.01257 0.0103 0.0670 1.0000
11.000 1.2994 0.01976 0.01311 0.0109 0.0622 1.0000
11.250 1.3150 0.02084 0.01405 0.0119 0.0444 1.0000
11.500 1.3293 0.02194 0.01512 0.0131 0.0390 1.0000
11.750 1.3452 0.02284 0.01604 0.0142 0.0372 1.0000
12.000 1.3587 0.02375 0.01699 0.0155 0.0359 1.0000
12.250 1.3716 0.02464 0.01794 0.0169 0.0352 1.0000
12.500 1.3837 0.02561 0.01897 0.0181 0.0346 1.0000
12.750 1.3946 0.02671 0.02014 0.0192 0.0342 1.0000
13.000 1.4040 0.02800 0.02151 0.0200 0.0338 1.0000
13.250 1.4120 0.02953 0.02311 0.0205 0.0334 1.0000
13.500 1.4183 0.03132 0.02498 0.0206 0.0331 1.0000
13.750 1.4228 0.03341 0.02717 0.0205 0.0329 1.0000
14.000 1.4250 0.03585 0.02971 0.0201 0.0326 1.0000
14.250 1.4243 0.03874 0.03271 0.0193 0.0324 1.0000
14.500 1.4201 0.04220 0.03629 0.0181 0.0323 1.0000
14.750 1.4112 0.04646 0.04068 0.0162 0.0322 1.0000
15.000 1.3960 0.05185 0.04624 0.0135 0.0321 1.0000
15.250 1.3705 0.05916 0.05375 0.0095 0.0320 1.0000
15.500 1.3282 0.06975 0.06460 0.0036 0.0321 1.0000
15.750 1.2643 0.08395 0.07911 -0.0037 0.0323 1.0000
16.000 1.2015 0.09764 0.09304 -0.0106 0.0325 1.0000
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