GIII BL126 AIRFOIL (giiie-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GIII BL126 AIRFOIL (giiie-il) Reynolds number: 500,000 Max Cl/Cd: 60.36 at α=3.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-giiie-il-500000-n5.txt Download as CSV file: xf-giiie-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GIII BL126 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
------ -------- --------- --------- -------- -------- --------
-9.500 -0.6490 0.08258 0.08051 -0.0065 1.0000 0.0048
-9.250 -0.6696 0.07308 0.07103 -0.0163 1.0000 0.0047
-9.000 -0.6923 0.06454 0.06239 -0.0211 1.0000 0.0047
-8.750 -0.7924 0.03022 0.02663 -0.0214 1.0000 0.0046
-8.500 -0.7784 0.02762 0.02372 -0.0203 1.0000 0.0048
-8.250 -0.7614 0.02566 0.02150 -0.0193 1.0000 0.0049
-8.000 -0.7435 0.02379 0.01936 -0.0182 1.0000 0.0052
-7.750 -0.7249 0.02203 0.01729 -0.0171 1.0000 0.0054
-7.500 -0.7056 0.02037 0.01535 -0.0159 1.0000 0.0058
-7.250 -0.6853 0.01902 0.01377 -0.0148 1.0000 0.0062
-7.000 -0.6572 0.01799 0.01253 -0.0153 0.9934 0.0068
-6.750 -0.6250 0.01715 0.01150 -0.0166 0.9801 0.0072
-6.500 -0.5954 0.01533 0.00944 -0.0175 0.9639 0.0080
-6.250 -0.5643 0.01461 0.00863 -0.0185 0.9452 0.0086
-6.000 -0.5357 0.01398 0.00784 -0.0188 0.9250 0.0094
-5.750 -0.5101 0.01338 0.00710 -0.0184 0.9046 0.0102
-5.500 -0.4851 0.01296 0.00654 -0.0178 0.8868 0.0111
-5.250 -0.4611 0.01236 0.00579 -0.0171 0.8716 0.0123
-5.000 -0.4367 0.01179 0.00512 -0.0165 0.8589 0.0138
-4.750 -0.4114 0.01141 0.00464 -0.0160 0.8488 0.0150
-4.250 -0.3595 0.01083 0.00386 -0.0153 0.8320 0.0183
-4.000 -0.3340 0.01043 0.00338 -0.0149 0.8250 0.0214
-3.750 -0.3077 0.01014 0.00306 -0.0146 0.8184 0.0260
-3.500 -0.2814 0.00990 0.00278 -0.0144 0.8127 0.0336
-3.250 -0.2550 0.00964 0.00254 -0.0142 0.8072 0.0492
-3.000 -0.2286 0.00941 0.00236 -0.0140 0.8016 0.0680
-2.750 -0.2019 0.00923 0.00219 -0.0139 0.7966 0.0845
-2.500 -0.1751 0.00904 0.00205 -0.0138 0.7913 0.1058
-2.250 -0.1487 0.00880 0.00190 -0.0136 0.7865 0.1377
-2.000 -0.1221 0.00859 0.00177 -0.0135 0.7820 0.1710
-1.750 -0.0963 0.00822 0.00164 -0.0133 0.7767 0.2414
-1.500 -0.0752 0.00726 0.00139 -0.0126 0.7718 0.4527
-1.250 -0.0553 0.00646 0.00132 -0.0112 0.7672 0.6619
-1.000 -0.0303 0.00627 0.00131 -0.0105 0.7620 0.7238
-0.750 -0.0042 0.00621 0.00130 -0.0101 0.7565 0.7580
-0.500 0.0225 0.00615 0.00129 -0.0097 0.7488 0.7833
-0.250 0.0489 0.00611 0.00127 -0.0093 0.7408 0.8050
0.000 0.0757 0.00608 0.00127 -0.0089 0.7319 0.8230
0.250 0.1020 0.00604 0.00127 -0.0085 0.7231 0.8431
0.500 0.1274 0.00601 0.00130 -0.0077 0.7130 0.8698
0.750 0.1538 0.00600 0.00132 -0.0072 0.7017 0.8866
1.000 0.1813 0.00601 0.00132 -0.0071 0.6909 0.8945
1.250 0.2090 0.00603 0.00133 -0.0070 0.6804 0.9016
1.750 0.2643 0.00610 0.00138 -0.0069 0.6571 0.9174
2.000 0.2921 0.00615 0.00142 -0.0068 0.6438 0.9255
2.250 0.3204 0.00622 0.00147 -0.0069 0.6289 0.9334
2.500 0.3492 0.00630 0.00155 -0.0071 0.6111 0.9409
2.750 0.3775 0.00645 0.00162 -0.0073 0.5820 0.9488
3.000 0.4060 0.00673 0.00170 -0.0075 0.5257 0.9557
3.250 0.4328 0.00717 0.00184 -0.0076 0.4415 0.9637
3.500 0.4618 0.00775 0.00210 -0.0084 0.3595 0.9696
3.750 0.4904 0.00824 0.00234 -0.0090 0.2975 0.9763
4.000 0.5204 0.00886 0.00262 -0.0100 0.2170 0.9813
4.250 0.5493 0.00950 0.00293 -0.0109 0.1432 0.9869
4.500 0.5805 0.01006 0.00329 -0.0122 0.0910 0.9909
4.750 0.6113 0.01054 0.00364 -0.0133 0.0598 0.9951
5.000 0.6435 0.01096 0.00399 -0.0147 0.0407 0.9985
5.250 0.6695 0.01136 0.00434 -0.0147 0.0287 1.0000
5.500 0.6916 0.01170 0.00470 -0.0137 0.0239 1.0000
5.750 0.7137 0.01206 0.00510 -0.0128 0.0206 1.0000
6.000 0.7349 0.01258 0.00565 -0.0116 0.0169 1.0000
6.250 0.7572 0.01296 0.00609 -0.0107 0.0158 1.0000
6.500 0.7796 0.01338 0.00658 -0.0099 0.0145 1.0000
6.750 0.8022 0.01381 0.00706 -0.0091 0.0130 1.0000
7.000 0.8243 0.01433 0.00759 -0.0083 0.0112 1.0000
7.250 0.8445 0.01517 0.00854 -0.0072 0.0099 1.0000
7.500 0.8669 0.01572 0.00918 -0.0065 0.0093 1.0000
7.750 0.8886 0.01638 0.00992 -0.0056 0.0085 1.0000
8.000 0.9102 0.01707 0.01069 -0.0048 0.0078 1.0000
8.250 0.9322 0.01768 0.01136 -0.0042 0.0071 1.0000
8.500 0.9523 0.01857 0.01231 -0.0033 0.0064 1.0000
8.750 0.9725 0.01947 0.01333 -0.0024 0.0060 1.0000
9.000 0.9929 0.02037 0.01436 -0.0016 0.0056 1.0000
9.250 1.0120 0.02145 0.01563 -0.0006 0.0052 1.0000
9.500 1.0306 0.02259 0.01693 0.0004 0.0049 1.0000
9.750 1.0487 0.02376 0.01825 0.0014 0.0046 1.0000
10.000 1.0662 0.02492 0.01955 0.0024 0.0044 1.0000
10.250 1.0829 0.02608 0.02086 0.0035 0.0042 1.0000
10.500 1.0980 0.02738 0.02230 0.0046 0.0040 1.0000
10.750 1.1093 0.02909 0.02421 0.0061 0.0039 1.0000
11.000 1.1121 0.03178 0.02720 0.0082 0.0037 1.0000
11.250 1.1052 0.03497 0.03073 0.0113 0.0036 1.0000
11.500 1.1013 0.03760 0.03363 0.0134 0.0036 1.0000
11.750 1.0931 0.04078 0.03708 0.0150 0.0035 1.0000
12.000 1.0812 0.04460 0.04116 0.0156 0.0035 1.0000
12.250 1.0661 0.04915 0.04597 0.0152 0.0035 1.0000
12.500 1.0482 0.05458 0.05164 0.0134 0.0035 1.0000
12.750 1.0284 0.06107 0.05834 0.0101 0.0035 1.0000
13.000 1.0069 0.06893 0.06639 0.0050 0.0035 1.0000
13.250 0.9835 0.07890 0.07653 -0.0022 0.0035 1.0000
13.500 0.9554 0.09181 0.08959 -0.0108 0.0036 1.0000
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Polar data table (+)
Polar graphs
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