BOEING 737 MIDSPAN AIRFOIL (b737c-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: BOEING 737 MIDSPAN AIRFOIL (b737c-il) Reynolds number: 50,000 Max Cl/Cd: 32.98 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-b737c-il-50000.txt Download as CSV file: xf-b737c-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: BOEING 737 MIDSPAN AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.5347 0.11524 0.10852 0.0041 1.0000 0.2332
-9.250 -0.5348 0.11212 0.10546 0.0039 1.0000 0.2490
-9.000 -0.5413 0.10947 0.10289 0.0034 1.0000 0.2652
-8.750 -0.5265 0.10582 0.09927 0.0058 1.0000 0.2924
-8.500 -0.5237 0.10320 0.09670 0.0076 1.0000 0.3219
-8.250 -0.5080 0.10034 0.09386 0.0112 1.0000 0.3640
-8.000 -0.4962 0.09784 0.09139 0.0146 1.0000 0.4070
-7.750 -0.4838 0.09530 0.08889 0.0179 1.0000 0.4501
-7.500 -0.4692 0.09254 0.08615 0.0210 1.0000 0.4934
-7.250 -0.4338 0.08777 0.08132 0.0230 1.0000 0.5404
-7.000 -0.4238 0.08518 0.07877 0.0255 1.0000 0.5812
-6.750 -0.3950 0.08063 0.07420 0.0256 1.0000 0.6159
-5.750 -0.4519 0.06738 0.06144 0.0187 1.0000 0.5120
-5.500 -0.5167 0.06077 0.05507 0.0071 1.0000 0.4363
-5.250 -0.5252 0.04779 0.04124 -0.0150 1.0000 0.2899
-5.000 -0.4952 0.04279 0.03495 -0.0190 1.0000 0.2033
-4.750 -0.4671 0.03997 0.03124 -0.0183 1.0000 0.1620
-4.500 -0.4423 0.03732 0.02796 -0.0168 1.0000 0.1401
-4.250 -0.4180 0.03499 0.02514 -0.0153 1.0000 0.1276
-4.000 -0.3934 0.03319 0.02284 -0.0136 1.0000 0.1196
-3.750 -0.3701 0.03120 0.02057 -0.0123 1.0000 0.1183
-3.500 -0.3461 0.02945 0.01858 -0.0111 1.0000 0.1180
-3.250 -0.3209 0.02782 0.01676 -0.0099 1.0000 0.1166
-3.000 -0.2951 0.02640 0.01521 -0.0087 1.0000 0.1162
-2.750 -0.2699 0.02521 0.01391 -0.0074 1.0000 0.1178
-2.500 -0.2467 0.02429 0.01287 -0.0060 1.0000 0.1212
-2.250 -0.0290 0.01915 0.01040 -0.0270 1.0000 1.0000
-2.000 -0.0289 0.01881 0.00996 -0.0240 1.0000 1.0000
-1.750 -0.0354 0.01857 0.00967 -0.0200 1.0000 1.0000
-1.500 -0.0491 0.01852 0.00958 -0.0148 1.0000 1.0000
-1.250 -0.0652 0.01866 0.00965 -0.0094 1.0000 1.0000
-1.000 -0.0741 0.01888 0.00971 -0.0050 1.0000 1.0000
-0.750 -0.0741 0.01913 0.00976 -0.0019 1.0000 1.0000
-0.500 -0.0670 0.01940 0.00981 0.0002 1.0000 1.0000
-0.250 -0.0556 0.01971 0.00988 0.0016 1.0000 1.0000
0.000 -0.0416 0.02005 0.01002 0.0026 1.0000 1.0000
0.250 -0.0259 0.02043 0.01021 0.0033 1.0000 1.0000
0.500 -0.0091 0.02083 0.01046 0.0038 1.0000 1.0000
0.750 0.0085 0.02128 0.01076 0.0042 1.0000 1.0000
1.000 0.0265 0.02176 0.01110 0.0045 1.0000 1.0000
1.250 0.0448 0.02229 0.01153 0.0046 1.0000 1.0000
1.500 0.0888 0.02319 0.01234 -0.0002 0.9894 1.0000
1.750 0.1373 0.02415 0.01324 -0.0057 0.9757 1.0000
2.000 0.1831 0.02506 0.01413 -0.0106 0.9616 1.0000
2.250 0.2280 0.02594 0.01503 -0.0152 0.9466 1.0000
2.500 0.2739 0.02677 0.01592 -0.0197 0.9303 1.0000
2.750 0.3243 0.02753 0.01678 -0.0248 0.9130 1.0000
3.000 0.3616 0.02814 0.01749 -0.0273 0.8927 1.0000
3.250 0.4145 0.02856 0.01811 -0.0319 0.8715 1.0000
3.500 0.4577 0.02886 0.01859 -0.0346 0.8480 1.0000
3.750 0.5127 0.02874 0.01872 -0.0382 0.8243 1.0000
4.000 0.5632 0.02831 0.01859 -0.0402 0.8001 1.0000
4.250 0.6001 0.02805 0.01855 -0.0399 0.7738 1.0000
4.500 0.6362 0.02765 0.01836 -0.0389 0.7467 1.0000
4.750 0.6696 0.02717 0.01814 -0.0371 0.7175 1.0000
5.000 0.7006 0.02664 0.01776 -0.0344 0.6858 1.0000
5.250 0.7243 0.02640 0.01763 -0.0311 0.6487 1.0000
5.500 0.7486 0.02595 0.01723 -0.0275 0.6084 1.0000
5.750 0.7699 0.02567 0.01701 -0.0238 0.5629 1.0000
6.000 0.7878 0.02541 0.01681 -0.0202 0.5113 1.0000
6.250 0.8093 0.02454 0.01568 -0.0165 0.4599 1.0000
6.500 0.8270 0.02542 0.01620 -0.0136 0.3996 1.0000
6.750 0.8437 0.02663 0.01706 -0.0110 0.3444 1.0000
7.000 0.8597 0.02819 0.01839 -0.0086 0.2940 1.0000
7.250 0.8762 0.02989 0.01981 -0.0066 0.2496 1.0000
7.500 0.8932 0.03197 0.02181 -0.0047 0.2115 1.0000
7.750 0.9115 0.03416 0.02386 -0.0031 0.1802 1.0000
8.000 0.9292 0.03670 0.02655 -0.0015 0.1574 1.0000
8.250 0.9479 0.03946 0.02949 -0.0001 0.1413 1.0000
8.500 0.9638 0.04265 0.03306 0.0015 0.1305 1.0000
8.750 0.9790 0.04564 0.03621 0.0028 0.1205 1.0000
9.000 0.9863 0.04958 0.04078 0.0049 0.1164 1.0000
9.250 0.9924 0.05371 0.04536 0.0066 0.1138 1.0000
9.500 1.0080 0.05793 0.04954 0.0074 0.1094 1.0000
9.750 1.0005 0.06233 0.05450 0.0095 0.1085 1.0000
10.000 0.9886 0.06697 0.05957 0.0111 0.1082 1.0000
10.250 0.9743 0.07176 0.06465 0.0123 0.1083 1.0000
10.500 0.9586 0.07665 0.06974 0.0130 0.1087 1.0000
10.750 0.9429 0.08152 0.07472 0.0135 0.1092 1.0000
11.000 0.8282 0.09906 0.09232 -0.0025 0.1306 1.0000
11.250 0.8179 0.10705 0.10026 -0.0064 0.1345 1.0000
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Polar data table (+)
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