BOEING 737 ROOT AIRFOIL (b737a-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: BOEING 737 ROOT AIRFOIL (b737a-il) Reynolds number: 200,000 Max Cl/Cd: 46.87 at α=8.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-b737a-il-200000-n5.txt Download as CSV file: xf-b737a-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.500 -1.0377 0.09283 0.08659 -0.0030 1.0000 0.0418
-16.250 -1.0489 0.08750 0.08121 -0.0055 1.0000 0.0421
-16.000 -1.0643 0.08140 0.07503 -0.0085 1.0000 0.0424
-15.750 -1.0829 0.07478 0.06830 -0.0119 1.0000 0.0426
-15.500 -1.1026 0.06791 0.06128 -0.0156 1.0000 0.0428
-15.250 -1.1213 0.06124 0.05446 -0.0194 1.0000 0.0430
-15.000 -1.1369 0.05528 0.04834 -0.0227 1.0000 0.0433
-14.750 -1.1486 0.05022 0.04313 -0.0253 1.0000 0.0437
-14.500 -1.1563 0.04603 0.03879 -0.0272 1.0000 0.0442
-14.250 -1.1601 0.04255 0.03518 -0.0285 1.0000 0.0448
-14.000 -1.1601 0.03971 0.03221 -0.0292 1.0000 0.0455
-13.750 -1.1631 0.03672 0.02912 -0.0297 1.0000 0.0462
-13.500 -1.1630 0.03423 0.02652 -0.0297 1.0000 0.0470
-13.250 -1.1595 0.03220 0.02438 -0.0293 1.0000 0.0480
-13.000 -1.1534 0.03054 0.02262 -0.0286 1.0000 0.0491
-12.750 -1.1467 0.02905 0.02104 -0.0274 1.0000 0.0503
-12.500 -1.1406 0.02762 0.01955 -0.0258 1.0000 0.0517
-12.250 -1.1307 0.02644 0.01830 -0.0241 1.0000 0.0535
-12.000 -1.1189 0.02522 0.01707 -0.0227 1.0000 0.0563
-11.750 -1.1046 0.02416 0.01625 -0.0215 1.0000 0.0633
-11.250 -1.0564 0.02364 0.01554 -0.0202 1.0000 0.0954
-11.000 -1.0343 0.02323 0.01506 -0.0193 1.0000 0.0990
-10.750 -1.0118 0.02284 0.01457 -0.0185 1.0000 0.1022
-10.500 -0.9895 0.02241 0.01407 -0.0177 1.0000 0.1048
-10.250 -0.9682 0.02189 0.01354 -0.0168 1.0000 0.1072
-10.000 -0.9455 0.02146 0.01306 -0.0159 1.0000 0.1096
-9.750 -0.9220 0.02112 0.01262 -0.0151 1.0000 0.1116
-9.500 -0.9009 0.02051 0.01207 -0.0141 1.0000 0.1137
-9.250 -0.8785 0.02004 0.01161 -0.0132 1.0000 0.1157
-9.000 -0.8554 0.01963 0.01117 -0.0124 1.0000 0.1174
-8.750 -0.8320 0.01927 0.01077 -0.0115 1.0000 0.1189
-8.500 -0.8090 0.01887 0.01036 -0.0106 1.0000 0.1202
-8.250 -0.7871 0.01838 0.00992 -0.0095 1.0000 0.1216
-8.000 -0.7647 0.01797 0.00953 -0.0085 1.0000 0.1230
-7.750 -0.7422 0.01760 0.00918 -0.0075 1.0000 0.1243
-7.500 -0.7197 0.01726 0.00884 -0.0064 1.0000 0.1258
-7.250 -0.6975 0.01694 0.00853 -0.0053 1.0000 0.1272
-7.000 -0.6695 0.01663 0.00823 -0.0054 0.9955 0.1284
-6.750 -0.6320 0.01620 0.00785 -0.0074 0.9798 0.1300
-6.500 -0.5961 0.01582 0.00750 -0.0090 0.9574 0.1319
-6.250 -0.5580 0.01547 0.00716 -0.0109 0.9309 0.1343
-6.000 -0.5165 0.01516 0.00680 -0.0133 0.8966 0.1366
-5.750 -0.4817 0.01492 0.00648 -0.0141 0.8606 0.1384
-5.500 -0.4536 0.01476 0.00624 -0.0137 0.8336 0.1398
-5.250 -0.4271 0.01462 0.00603 -0.0130 0.8126 0.1415
-5.000 -0.4007 0.01447 0.00584 -0.0124 0.7949 0.1437
-4.750 -0.3743 0.01430 0.00567 -0.0117 0.7782 0.1469
-4.500 -0.3482 0.01413 0.00553 -0.0111 0.7601 0.1535
-4.250 -0.3221 0.01397 0.00540 -0.0104 0.7410 0.1665
-4.000 -0.2957 0.01386 0.00527 -0.0097 0.7204 0.1803
-3.750 -0.2688 0.01378 0.00514 -0.0091 0.7018 0.1910
-3.500 -0.2418 0.01369 0.00503 -0.0085 0.6836 0.1996
-3.250 -0.2147 0.01361 0.00491 -0.0080 0.6628 0.2069
-3.000 -0.1879 0.01353 0.00479 -0.0073 0.6381 0.2133
-2.750 -0.1610 0.01351 0.00467 -0.0067 0.6078 0.2194
-2.500 -0.1349 0.01348 0.00455 -0.0060 0.5693 0.2254
-2.250 -0.1092 0.01354 0.00443 -0.0053 0.5163 0.2312
-2.000 -0.0847 0.01379 0.00433 -0.0043 0.4303 0.2358
-1.750 -0.0602 0.01410 0.00431 -0.0036 0.3554 0.2403
-1.500 -0.0345 0.01429 0.00432 -0.0031 0.3153 0.2457
-1.250 -0.0079 0.01441 0.00435 -0.0027 0.2923 0.2520
-1.000 0.0188 0.01451 0.00438 -0.0023 0.2759 0.2589
-0.750 0.0456 0.01457 0.00442 -0.0019 0.2626 0.2660
-0.500 0.0727 0.01464 0.00446 -0.0015 0.2524 0.2736
-0.250 0.0995 0.01469 0.00451 -0.0011 0.2434 0.2823
0.000 0.1264 0.01476 0.00458 -0.0008 0.2365 0.2933
0.250 0.1533 0.01476 0.00465 -0.0004 0.2299 0.3076
0.500 0.1798 0.01478 0.00472 0.0000 0.2238 0.3302
0.750 0.2057 0.01474 0.00482 0.0004 0.2187 0.3677
1.000 0.2313 0.01456 0.00492 0.0009 0.2140 0.4332
1.250 0.2561 0.01442 0.00509 0.0016 0.2092 0.5124
1.500 0.2811 0.01445 0.00532 0.0024 0.2045 0.5782
1.750 0.3072 0.01457 0.00555 0.0030 0.1999 0.6196
2.000 0.3341 0.01468 0.00576 0.0035 0.1951 0.6499
2.250 0.3604 0.01484 0.00597 0.0041 0.1907 0.6763
2.500 0.3863 0.01507 0.00621 0.0047 0.1869 0.6995
2.750 0.4131 0.01525 0.00645 0.0053 0.1835 0.7185
3.000 0.4397 0.01542 0.00668 0.0058 0.1798 0.7350
3.250 0.4660 0.01559 0.00690 0.0064 0.1763 0.7496
3.500 0.4920 0.01582 0.00713 0.0069 0.1730 0.7651
3.750 0.5180 0.01607 0.00739 0.0075 0.1700 0.7811
4.000 0.5439 0.01623 0.00766 0.0082 0.1668 0.7963
4.250 0.5696 0.01642 0.00792 0.0089 0.1637 0.8113
4.500 0.5953 0.01662 0.00816 0.0095 0.1608 0.8263
4.750 0.6205 0.01688 0.00841 0.0102 0.1580 0.8415
5.000 0.6463 0.01707 0.00871 0.0108 0.1549 0.8575
5.250 0.6726 0.01725 0.00898 0.0114 0.1514 0.8756
5.500 0.7000 0.01744 0.00923 0.0116 0.1480 0.8987
5.750 0.7321 0.01773 0.00952 0.0109 0.1448 0.9297
6.000 0.7713 0.01801 0.00990 0.0086 0.1406 0.9709
6.250 0.8038 0.01831 0.01020 0.0075 0.1372 1.0000
6.500 0.8282 0.01864 0.01047 0.0079 0.1346 1.0000
6.750 0.8530 0.01900 0.01084 0.0083 0.1319 1.0000
7.000 0.8780 0.01936 0.01124 0.0087 0.1292 1.0000
7.250 0.9027 0.01974 0.01162 0.0091 0.1269 1.0000
7.500 0.9270 0.02013 0.01200 0.0095 0.1250 1.0000
7.750 0.9510 0.02056 0.01239 0.0100 0.1231 1.0000
8.000 0.9754 0.02100 0.01290 0.0104 0.1208 1.0000
8.250 0.9994 0.02144 0.01338 0.0108 0.1185 1.0000
8.500 1.0231 0.02187 0.01384 0.0113 0.1165 1.0000
8.750 1.0461 0.02232 0.01429 0.0118 0.1147 1.0000
9.000 1.0689 0.02283 0.01481 0.0123 0.1130 1.0000
9.250 1.0917 0.02335 0.01541 0.0128 0.1109 1.0000
9.500 1.1140 0.02385 0.01598 0.0134 0.1088 1.0000
9.750 1.1357 0.02435 0.01650 0.0140 0.1068 1.0000
10.000 1.1562 0.02489 0.01704 0.0146 0.1051 1.0000
10.250 1.1770 0.02552 0.01775 0.0153 0.1034 1.0000
10.500 1.1970 0.02616 0.01848 0.0160 0.1017 1.0000
10.750 1.2161 0.02682 0.01921 0.0167 0.1001 1.0000
11.000 1.2341 0.02749 0.01994 0.0176 0.0986 1.0000
11.250 1.2497 0.02819 0.02065 0.0186 0.0972 1.0000
11.500 1.2645 0.02899 0.02155 0.0197 0.0955 1.0000
11.750 1.2785 0.02986 0.02253 0.0208 0.0938 1.0000
12.000 1.2911 0.03082 0.02358 0.0217 0.0921 1.0000
12.250 1.3023 0.03188 0.02471 0.0226 0.0905 1.0000
12.500 1.3115 0.03314 0.02599 0.0232 0.0890 1.0000
12.750 1.3214 0.03456 0.02757 0.0235 0.0869 1.0000
13.000 1.3293 0.03618 0.02930 0.0236 0.0850 1.0000
13.250 1.3353 0.03804 0.03125 0.0235 0.0833 1.0000
13.500 1.3389 0.04022 0.03350 0.0231 0.0816 1.0000
13.750 1.3421 0.04262 0.03607 0.0226 0.0797 1.0000
14.000 1.3420 0.04548 0.03906 0.0216 0.0778 1.0000
14.250 1.3381 0.04892 0.04262 0.0202 0.0762 1.0000
14.500 1.3299 0.05308 0.04691 0.0182 0.0747 1.0000
14.750 1.3167 0.05820 0.05224 0.0156 0.0730 1.0000
15.000 1.2928 0.06520 0.05944 0.0116 0.0717 1.0000
15.250 1.2488 0.07592 0.07043 0.0053 0.0709 1.0000
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