GIII BL332 AIRFOIL (giiij-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GIII BL332 AIRFOIL (giiij-il) Reynolds number: 500,000 Max Cl/Cd: 73.86 at α=3.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-giiij-il-500000.txt Download as CSV file: xf-giiij-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GIII BL332 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
------ -------- --------- --------- -------- -------- --------
-10.500 -0.4677 0.10347 0.10123 -0.0092 1.0000 0.0213
-10.250 -0.4697 0.09886 0.09663 -0.0109 1.0000 0.0213
-10.000 -0.5845 0.10547 0.10314 0.0003 1.0000 0.0211
-9.750 -0.5837 0.10052 0.09820 -0.0032 1.0000 0.0212
-9.500 -0.5830 0.09547 0.09316 -0.0068 1.0000 0.0212
-9.250 -0.5832 0.08987 0.08758 -0.0116 1.0000 0.0213
-9.000 -0.5866 0.08336 0.08106 -0.0190 1.0000 0.0213
-8.750 -0.6022 0.07633 0.07400 -0.0228 1.0000 0.0215
-8.500 -0.6030 0.07229 0.06994 -0.0237 1.0000 0.0217
-8.250 -0.5997 0.06877 0.06639 -0.0246 1.0000 0.0219
-8.000 -0.5943 0.06540 0.06297 -0.0256 1.0000 0.0222
-7.750 -0.5874 0.06198 0.05950 -0.0264 1.0000 0.0225
-7.500 -0.5792 0.05851 0.05594 -0.0271 1.0000 0.0229
-7.250 -0.5697 0.05495 0.05228 -0.0276 1.0000 0.0235
-7.000 -0.5591 0.05132 0.04851 -0.0278 1.0000 0.0243
-6.750 -0.5470 0.04753 0.04453 -0.0273 1.0000 0.0256
-6.500 -0.5296 0.04486 0.04140 -0.0253 1.0000 0.0271
-6.250 -0.5202 0.04221 0.03849 -0.0232 1.0000 0.0272
-6.000 -0.5143 0.02316 0.01963 -0.0187 1.0000 0.0280
-5.750 -0.4881 0.02031 0.01671 -0.0205 0.9973 0.0286
-5.500 -0.4592 0.01769 0.01396 -0.0224 0.9946 0.0294
-5.250 -0.4310 0.01537 0.01145 -0.0237 0.9908 0.0308
-5.000 -0.3932 0.01494 0.01064 -0.0247 0.9870 0.0347
-4.750 -0.3676 0.01036 0.00553 -0.0259 0.9841 0.0359
-4.500 -0.3392 0.00843 0.00354 -0.0271 0.9798 0.0372
-4.250 -0.3387 0.01748 0.01160 -0.0223 0.9846 0.0280
-4.000 -0.3037 0.01596 0.00990 -0.0236 0.9811 0.0277
-3.750 -0.2698 0.01414 0.00796 -0.0249 0.9770 0.0283
-3.500 -0.2346 0.01318 0.00698 -0.0265 0.9730 0.0295
-3.250 -0.2016 0.01246 0.00625 -0.0275 0.9677 0.0310
-3.000 -0.1705 0.01200 0.00576 -0.0282 0.9607 0.0332
-2.750 -0.1390 0.01160 0.00531 -0.0287 0.9544 0.0347
-2.500 -0.1138 0.01053 0.00422 -0.0281 0.9448 0.0366
-2.250 -0.0877 0.01004 0.00374 -0.0277 0.9351 0.0390
-2.000 -0.0612 0.00975 0.00343 -0.0272 0.9261 0.0419
-1.750 -0.0361 0.00946 0.00311 -0.0264 0.9143 0.0440
-1.500 -0.0109 0.00917 0.00278 -0.0257 0.9026 0.0459
-1.250 0.0142 0.00880 0.00238 -0.0249 0.8915 0.0505
-0.750 0.0664 0.00845 0.00194 -0.0238 0.8692 0.0606
-0.500 0.0823 0.00656 0.00162 -0.0223 0.8570 0.5351
-0.250 0.0953 0.00565 0.00174 -0.0186 0.8446 0.8269
0.000 0.1179 0.00558 0.00177 -0.0168 0.8319 0.8775
0.250 0.1422 0.00558 0.00178 -0.0154 0.8191 0.9067
0.500 0.1676 0.00562 0.00181 -0.0143 0.8062 0.9327
0.750 0.1959 0.00568 0.00185 -0.0139 0.7925 0.9520
1.000 0.2285 0.00576 0.00187 -0.0146 0.7772 0.9660
1.250 0.2669 0.00587 0.00190 -0.0165 0.7592 0.9770
1.500 0.3031 0.00594 0.00191 -0.0182 0.7406 0.9839
1.750 0.3403 0.00602 0.00187 -0.0202 0.7153 0.9872
2.000 0.3758 0.00612 0.00185 -0.0219 0.6791 0.9919
2.250 0.4117 0.00624 0.00184 -0.0237 0.6451 0.9959
2.500 0.4483 0.00638 0.00185 -0.0258 0.6078 0.9998
2.750 0.4730 0.00657 0.00187 -0.0253 0.5655 1.0000
3.000 0.4965 0.00680 0.00193 -0.0246 0.5216 1.0000
3.250 0.5197 0.00707 0.00202 -0.0239 0.4804 1.0000
3.500 0.5429 0.00735 0.00215 -0.0231 0.4390 1.0000
3.750 0.5656 0.00768 0.00228 -0.0223 0.3862 1.0000
4.000 0.5877 0.00812 0.00246 -0.0214 0.3264 1.0000
4.250 0.6093 0.00863 0.00269 -0.0205 0.2628 1.0000
4.500 0.6306 0.00920 0.00297 -0.0195 0.2000 1.0000
4.750 0.6519 0.00979 0.00328 -0.0185 0.1449 1.0000
5.000 0.6738 0.01032 0.00361 -0.0176 0.1075 1.0000
5.250 0.6964 0.01078 0.00396 -0.0168 0.0873 1.0000
5.500 0.7197 0.01120 0.00433 -0.0160 0.0746 1.0000
5.750 0.7436 0.01156 0.00468 -0.0154 0.0655 1.0000
6.000 0.7670 0.01203 0.00513 -0.0147 0.0578 1.0000
6.250 0.7907 0.01245 0.00554 -0.0140 0.0515 1.0000
6.500 0.8141 0.01295 0.00607 -0.0133 0.0465 1.0000
6.750 0.8382 0.01335 0.00648 -0.0128 0.0424 1.0000
7.000 0.8596 0.01415 0.00730 -0.0118 0.0386 1.0000
7.250 0.8837 0.01457 0.00778 -0.0113 0.0364 1.0000
7.500 0.9074 0.01506 0.00831 -0.0107 0.0341 1.0000
7.750 0.9286 0.01588 0.00913 -0.0098 0.0317 1.0000
8.000 0.9499 0.01676 0.01009 -0.0089 0.0302 1.0000
8.250 0.9728 0.01737 0.01079 -0.0082 0.0289 1.0000
8.500 0.9952 0.01806 0.01156 -0.0075 0.0276 1.0000
8.750 1.0175 0.01872 0.01226 -0.0069 0.0264 1.0000
9.000 1.0381 0.01964 0.01320 -0.0061 0.0251 1.0000
9.250 1.0554 0.02138 0.01507 -0.0048 0.0239 1.0000
9.500 1.0771 0.02216 0.01599 -0.0041 0.0233 1.0000
9.750 1.0977 0.02315 0.01711 -0.0032 0.0225 1.0000
10.000 1.1175 0.02418 0.01827 -0.0024 0.0217 1.0000
10.250 1.1372 0.02507 0.01925 -0.0015 0.0209 1.0000
10.500 1.1563 0.02589 0.02013 -0.0007 0.0201 1.0000
10.750 1.1717 0.02748 0.02181 0.0004 0.0193 1.0000
11.000 1.1802 0.03047 0.02508 0.0021 0.0187 1.0000
11.250 1.1942 0.03176 0.02659 0.0035 0.0183 1.0000
11.500 1.2046 0.03349 0.02855 0.0051 0.0179 1.0000
11.750 1.2113 0.03549 0.03078 0.0069 0.0174 1.0000
12.000 1.2134 0.03743 0.03294 0.0092 0.0170 1.0000
12.250 1.2135 0.03934 0.03502 0.0114 0.0166 1.0000
12.500 1.2135 0.04121 0.03703 0.0131 0.0163 1.0000
12.750 1.2121 0.04328 0.03925 0.0142 0.0160 1.0000
13.000 1.2095 0.04564 0.04175 0.0149 0.0157 1.0000
13.250 1.2062 0.04832 0.04454 0.0149 0.0154 1.0000
13.500 1.1999 0.05166 0.04801 0.0143 0.0152 1.0000
13.750 1.1886 0.05603 0.05254 0.0129 0.0151 1.0000
14.000 1.1725 0.06155 0.05824 0.0102 0.0150 1.0000
14.250 1.1515 0.06858 0.06548 0.0060 0.0150 1.0000
14.500 1.1201 0.07853 0.07570 -0.0007 0.0152 1.0000
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Polar data table (+)
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