BOEING 737 ROOT AIRFOIL (b737a-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: BOEING 737 ROOT AIRFOIL (b737a-il) Reynolds number: 100,000 Max Cl/Cd: 30.35 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-b737a-il-100000-n5.txt Download as CSV file: xf-b737a-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.000 -1.0090 0.07700 0.07044 -0.0133 1.0000 0.0782
-14.750 -1.0716 0.06295 0.05605 -0.0225 1.0000 0.0766
-14.500 -1.1007 0.05529 0.04804 -0.0269 1.0000 0.0819
-14.250 -1.1143 0.05021 0.04256 -0.0293 1.0000 0.0887
-14.000 -1.1201 0.04657 0.03865 -0.0306 1.0000 0.0936
-13.750 -1.1221 0.04361 0.03542 -0.0313 1.0000 0.0978
-13.500 -1.1214 0.04123 0.03287 -0.0315 1.0000 0.1013
-13.250 -1.1188 0.03914 0.03057 -0.0313 1.0000 0.1048
-13.000 -1.1148 0.03743 0.02877 -0.0307 1.0000 0.1083
-12.750 -1.1095 0.03588 0.02701 -0.0297 1.0000 0.1120
-12.500 -1.1016 0.03468 0.02581 -0.0283 1.0000 0.1150
-12.250 -1.0918 0.03358 0.02457 -0.0269 1.0000 0.1182
-12.000 -1.0789 0.03255 0.02346 -0.0256 1.0000 0.1211
-11.750 -1.0647 0.03163 0.02251 -0.0245 1.0000 0.1245
-11.500 -1.0487 0.03072 0.02145 -0.0234 1.0000 0.1279
-11.250 -1.0318 0.02993 0.02069 -0.0223 1.0000 0.1306
-11.000 -1.0136 0.02919 0.01992 -0.0212 1.0000 0.1334
-10.750 -0.9942 0.02845 0.01907 -0.0203 1.0000 0.1363
-10.500 -0.9746 0.02779 0.01841 -0.0193 1.0000 0.1387
-10.250 -0.9544 0.02720 0.01782 -0.0184 1.0000 0.1415
-10.000 -0.9333 0.02660 0.01715 -0.0175 1.0000 0.1445
-9.750 -0.9118 0.02602 0.01654 -0.0166 1.0000 0.1470
-9.500 -0.8901 0.02551 0.01605 -0.0157 1.0000 0.1492
-9.250 -0.8678 0.02501 0.01551 -0.0149 1.0000 0.1516
-9.000 -0.8452 0.02449 0.01495 -0.0140 1.0000 0.1542
-8.750 -0.8225 0.02400 0.01444 -0.0132 1.0000 0.1568
-8.500 -0.7999 0.02358 0.01405 -0.0123 1.0000 0.1594
-8.250 -0.7770 0.02315 0.01361 -0.0115 1.0000 0.1625
-8.000 -0.7538 0.02270 0.01311 -0.0106 1.0000 0.1659
-7.750 -0.7313 0.02233 0.01279 -0.0097 1.0000 0.1689
-7.500 -0.7085 0.02194 0.01242 -0.0087 1.0000 0.1722
-7.250 -0.6859 0.02152 0.01199 -0.0077 1.0000 0.1755
-7.000 -0.6636 0.02110 0.01159 -0.0067 1.0000 0.1784
-6.750 -0.6421 0.02071 0.01126 -0.0056 1.0000 0.1810
-6.500 -0.6210 0.02035 0.01093 -0.0044 1.0000 0.1842
-6.250 -0.6006 0.02000 0.01060 -0.0031 1.0000 0.1884
-6.000 -0.5815 0.01971 0.01036 -0.0018 0.9996 0.1924
-5.750 -0.5415 0.01937 0.01006 -0.0043 0.9858 0.1990
-5.500 -0.5026 0.01905 0.00976 -0.0065 0.9713 0.2066
-5.250 -0.4645 0.01875 0.00950 -0.0085 0.9552 0.2146
-5.000 -0.4233 0.01845 0.00920 -0.0108 0.9345 0.2232
-4.750 -0.3832 0.01815 0.00890 -0.0127 0.9074 0.2320
-4.500 -0.3446 0.01789 0.00859 -0.0141 0.8803 0.2403
-4.250 -0.3124 0.01768 0.00835 -0.0144 0.8567 0.2479
-4.000 -0.2837 0.01758 0.00814 -0.0139 0.8327 0.2555
-3.750 -0.2578 0.01741 0.00798 -0.0129 0.8075 0.2629
-3.500 -0.2319 0.01729 0.00781 -0.0119 0.7837 0.2696
-3.250 -0.2056 0.01720 0.00765 -0.0111 0.7635 0.2762
-3.000 -0.1802 0.01701 0.00751 -0.0102 0.7437 0.2835
-2.750 -0.1540 0.01688 0.00736 -0.0093 0.7230 0.2909
-2.500 -0.1280 0.01676 0.00721 -0.0085 0.7001 0.2973
-2.250 -0.1026 0.01659 0.00706 -0.0075 0.6741 0.3045
-2.000 -0.0771 0.01646 0.00690 -0.0066 0.6433 0.3136
-1.750 -0.0520 0.01634 0.00674 -0.0056 0.6050 0.3234
-1.500 -0.0275 0.01627 0.00655 -0.0044 0.5518 0.3348
-1.250 -0.0042 0.01631 0.00636 -0.0032 0.4761 0.3490
-1.000 0.0182 0.01651 0.00627 -0.0020 0.3985 0.3694
-0.750 0.0410 0.01663 0.00630 -0.0010 0.3523 0.4031
-0.500 0.0638 0.01665 0.00642 0.0000 0.3251 0.4567
-0.250 0.0867 0.01667 0.00668 0.0012 0.3067 0.5248
0.000 0.1105 0.01682 0.00698 0.0024 0.2930 0.5844
0.250 0.1352 0.01708 0.00723 0.0034 0.2817 0.6257
0.500 0.1605 0.01730 0.00749 0.0044 0.2721 0.6563
0.750 0.1858 0.01757 0.00773 0.0053 0.2635 0.6815
1.000 0.2110 0.01788 0.00798 0.0062 0.2565 0.7036
1.250 0.2366 0.01812 0.00825 0.0070 0.2495 0.7242
1.500 0.2617 0.01840 0.00851 0.0080 0.2432 0.7435
1.750 0.2865 0.01874 0.00878 0.0089 0.2378 0.7626
2.000 0.3115 0.01898 0.00909 0.0100 0.2321 0.7828
2.250 0.3360 0.01923 0.00937 0.0111 0.2267 0.8031
2.500 0.3602 0.01953 0.00963 0.0123 0.2218 0.8217
2.750 0.3853 0.01981 0.00996 0.0133 0.2170 0.8383
3.000 0.4110 0.02006 0.01028 0.0141 0.2117 0.8542
3.250 0.4370 0.02033 0.01055 0.0148 0.2069 0.8707
3.500 0.4640 0.02071 0.01085 0.0153 0.2028 0.8882
3.750 0.4941 0.02102 0.01130 0.0151 0.1980 0.9066
4.000 0.5279 0.02141 0.01173 0.0142 0.1931 0.9267
4.250 0.5652 0.02184 0.01213 0.0124 0.1888 0.9476
4.500 0.6045 0.02239 0.01265 0.0101 0.1848 0.9673
4.750 0.6435 0.02292 0.01328 0.0077 0.1802 0.9862
5.000 0.6766 0.02340 0.01377 0.0062 0.1762 1.0000
5.250 0.6957 0.02382 0.01411 0.0074 0.1735 1.0000
5.500 0.7176 0.02437 0.01452 0.0081 0.1711 1.0000
5.750 0.7398 0.02499 0.01529 0.0088 0.1679 1.0000
6.000 0.7628 0.02564 0.01601 0.0093 0.1650 1.0000
6.250 0.7863 0.02627 0.01665 0.0098 0.1623 1.0000
6.500 0.8102 0.02687 0.01722 0.0103 0.1600 1.0000
6.750 0.8345 0.02750 0.01776 0.0106 0.1581 1.0000
7.000 0.8569 0.02837 0.01876 0.0112 0.1555 1.0000
7.250 0.8787 0.02925 0.01980 0.0117 0.1527 1.0000
7.500 0.9009 0.03002 0.02064 0.0122 0.1501 1.0000
7.750 0.9238 0.03067 0.02130 0.0127 0.1479 1.0000
8.000 0.9474 0.03123 0.02180 0.0131 0.1460 1.0000
8.250 0.9683 0.03215 0.02281 0.0136 0.1438 1.0000
8.500 0.9862 0.03332 0.02422 0.0144 0.1411 1.0000
8.750 1.0054 0.03425 0.02527 0.0151 0.1386 1.0000
9.000 1.0259 0.03492 0.02597 0.0156 0.1365 1.0000
9.250 1.0480 0.03541 0.02641 0.0161 0.1347 1.0000
9.500 1.0659 0.03640 0.02749 0.0168 0.1328 1.0000
9.750 1.0768 0.03801 0.02939 0.0179 0.1303 1.0000
10.000 1.0899 0.03927 0.03080 0.0188 0.1281 1.0000
10.250 1.1051 0.04022 0.03183 0.0196 0.1262 1.0000
10.500 1.1219 0.04097 0.03260 0.0203 0.1247 1.0000
10.750 1.1414 0.04151 0.03308 0.0209 0.1235 1.0000
11.000 1.1371 0.04398 0.03587 0.0225 0.1218 1.0000
11.250 1.1263 0.04678 0.03896 0.0240 0.1203 1.0000
11.500 1.1129 0.05005 0.04247 0.0245 0.1189 1.0000
11.750 1.0958 0.05408 0.04672 0.0236 0.1176 1.0000
12.000 1.0701 0.05964 0.05250 0.0211 0.1165 1.0000
12.500 1.0976 0.06168 0.05449 0.0209 0.1139 1.0000
12.750 0.7420 0.13163 0.12524 -0.0227 0.1000 1.0000
13.000 0.7539 0.13315 0.12677 -0.0232 0.0980 1.0000
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