GIII BL167 AIRFOIL (giiig-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GIII BL167 AIRFOIL (giiig-il) Reynolds number: 1,000,000 Max Cl/Cd: 73.04 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-giiig-il-1000000-n5.txt Download as CSV file: xf-giiig-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 -0.6094 0.12138 0.11977 0.0136 1.0000 0.0032
-10.750 -0.6095 0.11652 0.11492 0.0116 1.0000 0.0031
-9.750 -0.8873 0.02772 0.02475 -0.0243 1.0000 0.0027
-9.500 -0.8768 0.02362 0.02022 -0.0229 1.0000 0.0028
-9.250 -0.8583 0.02174 0.01811 -0.0221 1.0000 0.0029
-9.000 -0.8381 0.02034 0.01652 -0.0214 1.0000 0.0030
-8.750 -0.8170 0.01915 0.01516 -0.0206 1.0000 0.0032
-8.500 -0.7958 0.01807 0.01392 -0.0198 1.0000 0.0033
-8.250 -0.7745 0.01703 0.01273 -0.0189 1.0000 0.0035
-8.000 -0.7506 0.01604 0.01155 -0.0186 0.9984 0.0037
-7.750 -0.7212 0.01507 0.01041 -0.0194 0.9935 0.0039
-7.500 -0.6916 0.01422 0.00941 -0.0202 0.9874 0.0041
-7.250 -0.6619 0.01349 0.00855 -0.0210 0.9800 0.0043
-7.000 -0.6325 0.01266 0.00758 -0.0217 0.9710 0.0045
-6.750 -0.6036 0.01196 0.00679 -0.0222 0.9597 0.0051
-6.500 -0.5755 0.01163 0.00642 -0.0224 0.9463 0.0055
-6.250 -0.5491 0.01135 0.00608 -0.0223 0.9317 0.0061
-6.000 -0.5234 0.01108 0.00570 -0.0219 0.9168 0.0068
-5.750 -0.4979 0.01079 0.00532 -0.0215 0.9023 0.0072
-5.500 -0.4725 0.01044 0.00487 -0.0210 0.8887 0.0075
-5.250 -0.4478 0.00989 0.00420 -0.0205 0.8763 0.0086
-5.000 -0.4217 0.00963 0.00388 -0.0202 0.8655 0.0094
-4.750 -0.3955 0.00940 0.00358 -0.0200 0.8552 0.0102
-4.500 -0.3689 0.00920 0.00331 -0.0198 0.8452 0.0111
-4.250 -0.3423 0.00899 0.00303 -0.0196 0.8362 0.0117
-3.750 -0.2893 0.00846 0.00236 -0.0191 0.8201 0.0146
-3.500 -0.2625 0.00826 0.00214 -0.0190 0.8125 0.0172
-3.250 -0.2353 0.00811 0.00194 -0.0189 0.8050 0.0193
-3.000 -0.2084 0.00793 0.00177 -0.0188 0.7982 0.0265
-2.750 -0.1810 0.00780 0.00162 -0.0188 0.7915 0.0316
-2.500 -0.1539 0.00767 0.00149 -0.0187 0.7849 0.0389
-2.250 -0.1264 0.00756 0.00137 -0.0187 0.7782 0.0459
-2.000 -0.0991 0.00745 0.00126 -0.0187 0.7719 0.0550
-1.750 -0.0717 0.00732 0.00117 -0.0186 0.7642 0.0701
-1.500 -0.0448 0.00718 0.00107 -0.0186 0.7541 0.0935
-1.250 -0.0179 0.00705 0.00098 -0.0185 0.7426 0.1223
-1.000 0.0090 0.00686 0.00091 -0.0184 0.7316 0.1679
-0.750 0.0352 0.00658 0.00083 -0.0183 0.7207 0.2484
-0.500 0.0548 0.00534 0.00064 -0.0173 0.7097 0.5915
-0.250 0.0794 0.00505 0.00062 -0.0167 0.6978 0.6894
0.000 0.1057 0.00496 0.00063 -0.0164 0.6866 0.7332
0.250 0.1323 0.00490 0.00064 -0.0161 0.6759 0.7661
0.500 0.1590 0.00486 0.00065 -0.0159 0.6654 0.7909
0.750 0.1850 0.00481 0.00069 -0.0154 0.6545 0.8234
1.000 0.2120 0.00482 0.00071 -0.0152 0.6431 0.8386
1.250 0.2395 0.00486 0.00073 -0.0152 0.6312 0.8459
1.500 0.2670 0.00490 0.00076 -0.0152 0.6186 0.8542
1.750 0.2943 0.00494 0.00081 -0.0151 0.6051 0.8626
2.000 0.3209 0.00506 0.00085 -0.0149 0.5760 0.8716
2.250 0.3449 0.00548 0.00094 -0.0143 0.4774 0.8821
2.500 0.3689 0.00592 0.00111 -0.0137 0.3949 0.8934
2.750 0.3936 0.00630 0.00127 -0.0133 0.3296 0.9049
3.000 0.4189 0.00660 0.00142 -0.0130 0.2799 0.9172
3.250 0.4429 0.00711 0.00163 -0.0125 0.1976 0.9307
3.500 0.4679 0.00759 0.00188 -0.0122 0.1300 0.9439
3.750 0.4949 0.00796 0.00210 -0.0123 0.0876 0.9558
4.000 0.5238 0.00827 0.00232 -0.0128 0.0620 0.9662
4.250 0.5541 0.00853 0.00252 -0.0136 0.0464 0.9746
4.500 0.5853 0.00880 0.00274 -0.0146 0.0342 0.9811
4.750 0.6159 0.00907 0.00299 -0.0154 0.0261 0.9871
5.000 0.6474 0.00934 0.00325 -0.0165 0.0211 0.9917
5.250 0.6783 0.00965 0.00357 -0.0174 0.0173 0.9959
5.500 0.7100 0.00989 0.00383 -0.0186 0.0161 0.9992
5.750 0.7358 0.01015 0.00413 -0.0184 0.0149 1.0000
6.000 0.7594 0.01042 0.00441 -0.0177 0.0134 1.0000
6.250 0.7828 0.01077 0.00476 -0.0170 0.0116 1.0000
6.500 0.8062 0.01116 0.00520 -0.0163 0.0104 1.0000
6.750 0.8307 0.01142 0.00549 -0.0159 0.0098 1.0000
7.000 0.8551 0.01172 0.00583 -0.0154 0.0089 1.0000
7.250 0.8794 0.01204 0.00616 -0.0150 0.0078 1.0000
7.500 0.9028 0.01252 0.00667 -0.0144 0.0065 1.0000
7.750 0.9271 0.01287 0.00706 -0.0140 0.0060 1.0000
8.000 0.9510 0.01329 0.00752 -0.0136 0.0054 1.0000
8.250 0.9747 0.01373 0.00799 -0.0131 0.0048 1.0000
8.500 0.9980 0.01424 0.00853 -0.0126 0.0043 1.0000
8.750 1.0197 0.01499 0.00937 -0.0119 0.0038 1.0000
9.000 1.0420 0.01565 0.01011 -0.0112 0.0036 1.0000
9.250 1.0645 0.01626 0.01081 -0.0106 0.0035 1.0000
9.500 1.0864 0.01694 0.01161 -0.0100 0.0033 1.0000
9.750 1.1078 0.01767 0.01245 -0.0093 0.0031 1.0000
10.000 1.1289 0.01844 0.01332 -0.0086 0.0029 1.0000
10.250 1.1496 0.01922 0.01420 -0.0079 0.0028 1.0000
10.500 1.1702 0.01998 0.01505 -0.0072 0.0026 1.0000
10.750 1.1904 0.02077 0.01593 -0.0065 0.0024 1.0000
11.000 1.2089 0.02174 0.01700 -0.0056 0.0022 1.0000
11.250 1.2238 0.02317 0.01860 -0.0043 0.0021 1.0000
11.500 1.2338 0.02514 0.02083 -0.0025 0.0019 1.0000
11.750 1.2476 0.02645 0.02232 -0.0012 0.0019 1.0000
12.000 1.2591 0.02792 0.02396 0.0003 0.0019 1.0000
12.250 1.2672 0.02951 0.02574 0.0022 0.0018 1.0000
12.500 1.2706 0.03124 0.02765 0.0045 0.0018 1.0000
12.750 1.2709 0.03321 0.02980 0.0067 0.0018 1.0000
13.000 1.2678 0.03557 0.03236 0.0086 0.0018 1.0000
13.250 1.2620 0.03836 0.03535 0.0100 0.0018 1.0000
13.500 1.2533 0.04170 0.03889 0.0106 0.0018 1.0000
13.750 1.2414 0.04575 0.04314 0.0104 0.0017 1.0000
14.000 1.2260 0.05070 0.04829 0.0091 0.0017 1.0000
14.250 1.2064 0.05689 0.05467 0.0063 0.0017 1.0000
14.500 1.1817 0.06490 0.06288 0.0016 0.0017 1.0000
14.750 1.1511 0.07583 0.07400 -0.0060 0.0018 1.0000
15.250 0.9506 0.13527 0.13377 -0.0360 0.0022 1.0000
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