GIII BL207 AIRFOIL (giiih-il) Xfoil prediction polar at RE=500,000 Ncrit=9
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Airfoil: GIII BL207 AIRFOIL (giiih-il) Reynolds number: 500,000 Max Cl/Cd: 78.87 at α=3.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-giiih-il-500000.txt Download as CSV file: xf-giiih-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GIII BL207 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.000 -0.4672 0.12960 0.12740 -0.0009 1.0000 0.0144
-11.750 -0.4668 0.12578 0.12359 -0.0021 1.0000 0.0144
-7.500 -0.5687 0.06151 0.05901 -0.0273 1.0000 0.0206
-7.250 -0.5605 0.05710 0.05442 -0.0277 1.0000 0.0207
-7.000 -0.5519 0.05274 0.04988 -0.0275 1.0000 0.0207
-6.750 -0.5294 0.03089 0.02799 -0.0278 1.0000 0.0215
-6.500 -0.5257 0.02763 0.02464 -0.0258 1.0000 0.0220
-6.250 -0.5215 0.02548 0.02242 -0.0232 1.0000 0.0224
-6.000 -0.5081 0.02297 0.01979 -0.0225 0.9982 0.0232
-5.750 -0.4806 0.01969 0.01629 -0.0243 0.9946 0.0251
-5.500 -0.5011 0.02544 0.02097 -0.0175 0.9966 0.0190
-5.250 -0.4697 0.02139 0.01639 -0.0184 0.9932 0.0193
-5.000 -0.4379 0.01845 0.01302 -0.0192 0.9891 0.0198
-4.750 -0.4036 0.01659 0.01085 -0.0205 0.9859 0.0204
-4.500 -0.3692 0.01446 0.00843 -0.0219 0.9835 0.0212
-4.250 -0.3373 0.01290 0.00678 -0.0230 0.9788 0.0232
-4.000 -0.3035 0.01234 0.00619 -0.0244 0.9734 0.0254
-3.750 -0.2693 0.01157 0.00536 -0.0258 0.9690 0.0276
-3.500 -0.2396 0.01115 0.00487 -0.0261 0.9600 0.0294
-3.250 -0.2119 0.01018 0.00386 -0.0262 0.9516 0.0345
-3.000 -0.1832 0.01000 0.00365 -0.0263 0.9426 0.0400
-2.750 -0.1583 0.00945 0.00308 -0.0257 0.9320 0.0471
-2.500 -0.1319 0.00926 0.00282 -0.0253 0.9225 0.0531
-2.250 -0.1067 0.00892 0.00247 -0.0247 0.9131 0.0629
-2.000 -0.0812 0.00866 0.00222 -0.0242 0.9030 0.0758
-1.750 -0.0570 0.00813 0.00199 -0.0236 0.8937 0.1572
-1.500 -0.0468 0.00606 0.00172 -0.0209 0.8837 0.6774
-1.250 -0.0247 0.00583 0.00174 -0.0193 0.8738 0.7722
-1.000 -0.0006 0.00575 0.00173 -0.0182 0.8632 0.8110
-0.750 0.0239 0.00571 0.00170 -0.0171 0.8515 0.8378
-0.500 0.0484 0.00569 0.00169 -0.0160 0.8409 0.8630
-0.250 0.0719 0.00569 0.00174 -0.0145 0.8310 0.8930
0.000 0.0956 0.00572 0.00179 -0.0131 0.8218 0.9175
0.250 0.1214 0.00577 0.00181 -0.0123 0.8131 0.9322
0.500 0.1486 0.00582 0.00184 -0.0119 0.8032 0.9461
0.750 0.1775 0.00587 0.00186 -0.0120 0.7939 0.9567
1.000 0.2098 0.00592 0.00186 -0.0129 0.7851 0.9627
1.250 0.2412 0.00595 0.00188 -0.0136 0.7749 0.9700
1.500 0.2769 0.00598 0.00190 -0.0154 0.7647 0.9742
1.750 0.3117 0.00603 0.00192 -0.0169 0.7542 0.9794
2.000 0.3470 0.00607 0.00193 -0.0186 0.7426 0.9839
2.250 0.3839 0.00609 0.00192 -0.0207 0.7215 0.9876
2.500 0.4188 0.00615 0.00191 -0.0222 0.6910 0.9924
2.750 0.4547 0.00624 0.00191 -0.0241 0.6607 0.9963
3.000 0.4907 0.00636 0.00194 -0.0260 0.6261 1.0000
3.250 0.5142 0.00652 0.00200 -0.0254 0.5848 1.0000
3.500 0.5364 0.00684 0.00206 -0.0245 0.5133 1.0000
3.750 0.5563 0.00747 0.00225 -0.0233 0.4118 1.0000
4.000 0.5767 0.00807 0.00251 -0.0223 0.3295 1.0000
4.250 0.5964 0.00877 0.00280 -0.0212 0.2377 1.0000
4.500 0.6140 0.00974 0.00324 -0.0198 0.1220 1.0000
4.750 0.6340 0.01045 0.00368 -0.0186 0.0704 1.0000
5.000 0.6553 0.01102 0.00416 -0.0175 0.0503 1.0000
5.250 0.6766 0.01163 0.00474 -0.0164 0.0393 1.0000
5.500 0.7001 0.01196 0.00512 -0.0157 0.0348 1.0000
5.750 0.7212 0.01266 0.00585 -0.0145 0.0299 1.0000
6.000 0.7426 0.01339 0.00666 -0.0134 0.0275 1.0000
6.250 0.7660 0.01384 0.00716 -0.0127 0.0249 1.0000
6.500 0.7887 0.01441 0.00776 -0.0120 0.0227 1.0000
6.750 0.8075 0.01571 0.00913 -0.0106 0.0206 1.0000
7.000 0.8274 0.01706 0.01063 -0.0093 0.0194 1.0000
7.250 0.8511 0.01763 0.01128 -0.0087 0.0182 1.0000
7.500 0.8741 0.01832 0.01205 -0.0081 0.0167 1.0000
7.750 0.8964 0.01923 0.01304 -0.0073 0.0156 1.0000
8.000 0.9176 0.02038 0.01426 -0.0065 0.0147 1.0000
8.250 0.9334 0.02375 0.01791 -0.0050 0.0137 1.0000
8.500 0.9508 0.02624 0.02073 -0.0036 0.0133 1.0000
8.750 0.9694 0.02791 0.02270 -0.0024 0.0128 1.0000
9.000 0.9864 0.02974 0.02481 -0.0012 0.0121 1.0000
9.250 1.0001 0.03211 0.02748 0.0003 0.0115 1.0000
9.500 1.0054 0.03612 0.03192 0.0026 0.0113 1.0000
9.750 1.0010 0.04131 0.03759 0.0054 0.0114 1.0000
10.000 0.9867 0.04725 0.04398 0.0083 0.0117 1.0000
10.250 0.9673 0.05239 0.04942 0.0110 0.0119 1.0000
10.500 0.9451 0.05682 0.05407 0.0127 0.0121 1.0000
10.750 0.9227 0.06173 0.05915 0.0122 0.0123 1.0000
11.000 0.9002 0.06760 0.06518 0.0094 0.0125 1.0000
11.250 0.8777 0.07493 0.07264 0.0041 0.0127 1.0000
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