GIII BL167 AIRFOIL (giiig-il) Xfoil prediction polar at RE=500,000 Ncrit=5
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Airfoil: GIII BL167 AIRFOIL (giiig-il) Reynolds number: 500,000 Max Cl/Cd: 62.05 at α=2.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-giiig-il-500000-n5.txt Download as CSV file: xf-giiig-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GIII BL167 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
------ -------- --------- --------- -------- -------- --------
-9.000 -0.6168 0.08143 0.07933 -0.0098 1.0000 0.0048
-8.750 -0.6299 0.07407 0.07198 -0.0176 1.0000 0.0047
-8.500 -0.6368 0.06762 0.06546 -0.0219 1.0000 0.0047
-8.250 -0.6392 0.06143 0.05916 -0.0247 1.0000 0.0048
-8.000 -0.6379 0.05551 0.05309 -0.0264 1.0000 0.0048
-7.750 -0.6342 0.04957 0.04695 -0.0270 1.0000 0.0050
-7.500 -0.6301 0.04293 0.04003 -0.0266 1.0000 0.0051
-7.250 -0.6543 0.02468 0.02052 -0.0212 1.0000 0.0055
-7.000 -0.6408 0.02141 0.01678 -0.0191 1.0000 0.0059
-6.750 -0.6149 0.01948 0.01451 -0.0193 0.9963 0.0066
-6.500 -0.5849 0.01810 0.01284 -0.0202 0.9907 0.0072
-6.250 -0.5561 0.01606 0.01044 -0.0208 0.9845 0.0077
-6.000 -0.5262 0.01488 0.00908 -0.0217 0.9774 0.0084
-5.750 -0.4958 0.01422 0.00832 -0.0225 0.9691 0.0092
-5.500 -0.4655 0.01349 0.00747 -0.0232 0.9602 0.0101
-5.250 -0.4354 0.01290 0.00677 -0.0238 0.9506 0.0112
-5.000 -0.4063 0.01259 0.00637 -0.0242 0.9395 0.0120
-4.750 -0.3814 0.01152 0.00514 -0.0237 0.9269 0.0135
-4.500 -0.3555 0.01105 0.00459 -0.0233 0.9143 0.0147
-4.250 -0.3296 0.01071 0.00418 -0.0230 0.9022 0.0163
-4.000 -0.3038 0.01041 0.00379 -0.0226 0.8911 0.0181
-3.750 -0.2779 0.01012 0.00341 -0.0221 0.8806 0.0194
-3.500 -0.2525 0.00972 0.00296 -0.0216 0.8701 0.0240
-3.250 -0.2261 0.00952 0.00268 -0.0214 0.8603 0.0288
-3.000 -0.1998 0.00930 0.00245 -0.0211 0.8515 0.0364
-2.750 -0.1732 0.00914 0.00226 -0.0209 0.8429 0.0449
-2.500 -0.1465 0.00898 0.00209 -0.0207 0.8345 0.0539
-2.250 -0.1199 0.00882 0.00191 -0.0205 0.8268 0.0663
-2.000 -0.0932 0.00863 0.00177 -0.0204 0.8190 0.0857
-1.750 -0.0667 0.00843 0.00163 -0.0202 0.8119 0.1157
-1.500 -0.0404 0.00817 0.00151 -0.0201 0.8043 0.1673
-1.250 -0.0153 0.00771 0.00137 -0.0198 0.7975 0.2781
-1.000 0.0008 0.00623 0.00118 -0.0182 0.7894 0.6594
-0.750 0.0250 0.00604 0.00119 -0.0173 0.7799 0.7333
-0.500 0.0508 0.00598 0.00117 -0.0167 0.7689 0.7685
-0.250 0.0764 0.00592 0.00116 -0.0161 0.7580 0.7994
0.000 0.1023 0.00588 0.00117 -0.0155 0.7469 0.8245
0.250 0.1270 0.00583 0.00120 -0.0146 0.7360 0.8586
0.500 0.1530 0.00582 0.00122 -0.0140 0.7257 0.8776
0.750 0.1803 0.00584 0.00122 -0.0139 0.7160 0.8860
1.000 0.2078 0.00586 0.00123 -0.0138 0.7058 0.8952
1.250 0.2352 0.00588 0.00125 -0.0136 0.6956 0.9040
1.500 0.2627 0.00592 0.00129 -0.0135 0.6847 0.9136
1.750 0.2904 0.00597 0.00133 -0.0134 0.6730 0.9236
2.000 0.3189 0.00602 0.00138 -0.0136 0.6600 0.9328
2.500 0.3762 0.00624 0.00150 -0.0139 0.6132 0.9516
2.750 0.4052 0.00653 0.00156 -0.0143 0.5486 0.9596
3.000 0.4328 0.00705 0.00170 -0.0146 0.4475 0.9678
3.250 0.4608 0.00764 0.00193 -0.0151 0.3631 0.9759
3.500 0.4913 0.00819 0.00219 -0.0163 0.2858 0.9818
3.750 0.5202 0.00890 0.00249 -0.0172 0.1886 0.9881
4.000 0.5498 0.00966 0.00285 -0.0183 0.1002 0.9935
4.250 0.5815 0.01013 0.00317 -0.0196 0.0646 0.9978
4.500 0.6093 0.01048 0.00348 -0.0200 0.0468 1.0000
4.750 0.6321 0.01080 0.00377 -0.0191 0.0358 1.0000
5.000 0.6546 0.01117 0.00411 -0.0183 0.0284 1.0000
5.250 0.6779 0.01148 0.00446 -0.0175 0.0250 1.0000
5.500 0.7011 0.01183 0.00484 -0.0168 0.0220 1.0000
5.750 0.7240 0.01227 0.00530 -0.0160 0.0194 1.0000
6.000 0.7461 0.01284 0.00597 -0.0151 0.0171 1.0000
6.250 0.7699 0.01320 0.00639 -0.0145 0.0161 1.0000
6.500 0.7932 0.01365 0.00691 -0.0138 0.0148 1.0000
6.750 0.8169 0.01406 0.00735 -0.0133 0.0131 1.0000
7.000 0.8394 0.01464 0.00796 -0.0126 0.0112 1.0000
7.250 0.8607 0.01546 0.00887 -0.0117 0.0102 1.0000
7.500 0.8835 0.01604 0.00958 -0.0110 0.0094 1.0000
7.750 0.9057 0.01672 0.01035 -0.0103 0.0085 1.0000
8.000 0.9283 0.01734 0.01104 -0.0097 0.0077 1.0000
8.250 0.9511 0.01789 0.01162 -0.0092 0.0070 1.0000
8.500 0.9710 0.01893 0.01277 -0.0083 0.0062 1.0000
8.750 0.9923 0.01976 0.01373 -0.0075 0.0058 1.0000
9.000 1.0122 0.02084 0.01496 -0.0066 0.0054 1.0000
9.250 1.0318 0.02195 0.01624 -0.0057 0.0050 1.0000
9.500 1.0509 0.02306 0.01750 -0.0048 0.0047 1.0000
9.750 1.0697 0.02415 0.01878 -0.0039 0.0045 1.0000
10.000 1.0876 0.02529 0.02006 -0.0029 0.0042 1.0000
10.250 1.1028 0.02679 0.02174 -0.0017 0.0040 1.0000
10.500 1.1101 0.02943 0.02470 0.0002 0.0038 1.0000
10.750 1.1127 0.03257 0.02823 0.0025 0.0037 1.0000
11.000 1.1143 0.03541 0.03142 0.0047 0.0036 1.0000
11.250 1.1070 0.03857 0.03491 0.0077 0.0036 1.0000
11.500 1.0934 0.04225 0.03890 0.0101 0.0035 1.0000
11.750 1.0752 0.04667 0.04362 0.0112 0.0035 1.0000
12.000 1.0540 0.05199 0.04920 0.0107 0.0035 1.0000
12.250 1.0314 0.05832 0.05577 0.0081 0.0035 1.0000
12.500 1.0080 0.06605 0.06370 0.0033 0.0036 1.0000
12.750 0.9842 0.07595 0.07377 -0.0043 0.0036 1.0000
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Polar data table (+)
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