GIII BL75 AIRFOIL (giiic-il) Xfoil prediction polar at RE=500,000 Ncrit=9
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Airfoil: GIII BL75 AIRFOIL (giiic-il) Reynolds number: 500,000 Max Cl/Cd: 68.35 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-giiic-il-500000.txt Download as CSV file: xf-giiic-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GIII BL75 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
------ -------- --------- --------- -------- -------- --------
-11.250 -0.6276 0.11731 0.11512 0.0097 1.0000 0.0185
-11.000 -0.6432 0.10877 0.10663 0.0062 1.0000 0.0189
-8.750 -0.7885 0.03878 0.03524 -0.0177 1.0000 0.0134
-8.500 -0.7863 0.03458 0.03066 -0.0155 1.0000 0.0135
-8.250 -0.7798 0.03084 0.02656 -0.0134 1.0000 0.0137
-8.000 -0.7689 0.02754 0.02285 -0.0113 1.0000 0.0138
-7.750 -0.7548 0.02460 0.01955 -0.0094 1.0000 0.0138
-7.500 -0.7373 0.02253 0.01725 -0.0080 1.0000 0.0142
-7.250 -0.7177 0.02108 0.01562 -0.0068 1.0000 0.0147
-7.000 -0.6979 0.01981 0.01421 -0.0055 1.0000 0.0153
-6.750 -0.6799 0.01871 0.01298 -0.0039 1.0000 0.0159
-6.500 -0.6539 0.01750 0.01163 -0.0038 0.9968 0.0167
-6.250 -0.6182 0.01667 0.01065 -0.0057 0.9906 0.0179
-6.000 -0.5852 0.01507 0.00888 -0.0071 0.9832 0.0193
-5.750 -0.5540 0.01383 0.00757 -0.0081 0.9734 0.0208
-5.500 -0.5219 0.01315 0.00683 -0.0092 0.9637 0.0226
-5.250 -0.4913 0.01259 0.00620 -0.0099 0.9534 0.0247
-5.000 -0.4649 0.01198 0.00549 -0.0096 0.9417 0.0270
-4.750 -0.4412 0.01134 0.00480 -0.0088 0.9303 0.0310
-4.500 -0.4162 0.01101 0.00440 -0.0081 0.9206 0.0352
-4.250 -0.3926 0.01052 0.00388 -0.0072 0.9118 0.0460
-4.000 -0.3689 0.01003 0.00348 -0.0064 0.9028 0.0713
-3.750 -0.3448 0.00964 0.00323 -0.0058 0.8952 0.1115
-3.500 -0.3202 0.00930 0.00302 -0.0053 0.8875 0.1494
-3.250 -0.2957 0.00897 0.00283 -0.0047 0.8805 0.1964
-3.000 -0.2723 0.00849 0.00262 -0.0041 0.8730 0.2709
-2.750 -0.2525 0.00766 0.00235 -0.0029 0.8661 0.4178
-2.500 -0.2375 0.00667 0.00219 -0.0005 0.8584 0.6374
-2.250 -0.2154 0.00638 0.00216 0.0009 0.8519 0.7178
-2.000 -0.1918 0.00623 0.00217 0.0022 0.8448 0.7764
-1.750 -0.1668 0.00620 0.00218 0.0031 0.8385 0.8116
-1.500 -0.1410 0.00619 0.00219 0.0038 0.8312 0.8353
-1.250 -0.1150 0.00621 0.00218 0.0045 0.8250 0.8542
-1.000 -0.0885 0.00621 0.00217 0.0050 0.8175 0.8683
-0.750 -0.0620 0.00625 0.00218 0.0056 0.8109 0.8815
-0.500 -0.0354 0.00625 0.00218 0.0061 0.8019 0.8926
-0.250 -0.0091 0.00627 0.00217 0.0068 0.7910 0.9037
0.000 0.0167 0.00631 0.00217 0.0076 0.7798 0.9159
0.250 0.0423 0.00641 0.00224 0.0086 0.7698 0.9298
0.500 0.0690 0.00652 0.00235 0.0094 0.7585 0.9428
0.750 0.1004 0.00660 0.00240 0.0089 0.7471 0.9487
1.000 0.1271 0.00662 0.00237 0.0093 0.7351 0.9553
1.250 0.1611 0.00666 0.00237 0.0080 0.7225 0.9579
1.500 0.1947 0.00671 0.00238 0.0068 0.7097 0.9610
1.750 0.2269 0.00676 0.00239 0.0059 0.6957 0.9650
2.000 0.2569 0.00681 0.00241 0.0054 0.6814 0.9698
2.250 0.2938 0.00687 0.00243 0.0034 0.6643 0.9714
2.500 0.3299 0.00694 0.00246 0.0015 0.6467 0.9736
3.000 0.3968 0.00713 0.00255 -0.0011 0.6056 0.9803
3.250 0.4294 0.00724 0.00262 -0.0023 0.5826 0.9835
3.500 0.4652 0.00738 0.00268 -0.0042 0.5537 0.9855
3.750 0.5000 0.00754 0.00277 -0.0059 0.5205 0.9881
4.000 0.5331 0.00780 0.00289 -0.0073 0.4714 0.9911
4.250 0.5630 0.00848 0.00309 -0.0084 0.3576 0.9941
5.000 0.6629 0.00983 0.00383 -0.0136 0.2138 1.0000
5.250 0.6855 0.01011 0.00403 -0.0129 0.1901 1.0000
5.500 0.7074 0.01042 0.00425 -0.0121 0.1632 1.0000
5.750 0.7284 0.01082 0.00452 -0.0112 0.1290 1.0000
6.000 0.7450 0.01175 0.00505 -0.0097 0.0586 1.0000
6.250 0.7617 0.01262 0.00578 -0.0079 0.0320 1.0000
6.500 0.7799 0.01321 0.00638 -0.0063 0.0256 1.0000
6.750 0.7976 0.01384 0.00709 -0.0045 0.0227 1.0000
7.000 0.8159 0.01437 0.00768 -0.0029 0.0206 1.0000
7.250 0.8333 0.01499 0.00834 -0.0011 0.0189 1.0000
7.500 0.8435 0.01641 0.00985 0.0017 0.0169 1.0000
7.750 0.8634 0.01681 0.01033 0.0031 0.0161 1.0000
8.000 0.8806 0.01756 0.01115 0.0048 0.0152 1.0000
8.250 0.8974 0.01839 0.01207 0.0066 0.0144 1.0000
8.500 0.9144 0.01928 0.01302 0.0082 0.0137 1.0000
8.750 0.9314 0.02025 0.01405 0.0097 0.0131 1.0000
9.000 0.9470 0.02158 0.01545 0.0114 0.0125 1.0000
9.250 0.9602 0.02385 0.01786 0.0132 0.0121 1.0000
9.500 0.9731 0.02661 0.02089 0.0150 0.0117 1.0000
9.750 0.9908 0.02740 0.02184 0.0162 0.0113 1.0000
10.000 1.0064 0.02868 0.02331 0.0176 0.0108 1.0000
10.250 1.0185 0.03065 0.02551 0.0192 0.0106 1.0000
10.500 1.0269 0.03301 0.02813 0.0211 0.0104 1.0000
10.750 1.0311 0.03564 0.03104 0.0232 0.0103 1.0000
11.000 1.0292 0.03843 0.03411 0.0257 0.0103 1.0000
11.250 1.0211 0.04138 0.03731 0.0285 0.0103 1.0000
11.500 1.0090 0.04476 0.04095 0.0304 0.0103 1.0000
11.750 0.9939 0.04864 0.04507 0.0313 0.0104 1.0000
12.000 0.9766 0.05309 0.04974 0.0310 0.0104 1.0000
12.250 0.9577 0.05821 0.05508 0.0294 0.0105 1.0000
12.500 0.9378 0.06414 0.06119 0.0265 0.0106 1.0000
12.750 0.9171 0.07101 0.06823 0.0222 0.0107 1.0000
13.000 0.8957 0.07895 0.07633 0.0166 0.0109 1.0000
13.250 0.8731 0.08833 0.08584 0.0098 0.0110 1.0000
13.500 0.8472 0.09955 0.09717 0.0022 0.0112 1.0000
13.750 0.7224 0.09304 0.09067 0.0166 0.0113 1.0000
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