GIII BL332 AIRFOIL (giiij-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GIII BL332 AIRFOIL (giiij-il) Reynolds number: 500,000 Max Cl/Cd: 65.23 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-giiij-il-500000-n5.txt Download as CSV file: xf-giiij-il-500000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.6072 0.08057 0.07828 -0.0111 1.0000 0.0119
-8.750 -0.6178 0.07369 0.07140 -0.0188 1.0000 0.0118
-8.500 -0.6232 0.06736 0.06498 -0.0232 1.0000 0.0118
-8.250 -0.6255 0.06113 0.05863 -0.0262 1.0000 0.0119
-8.000 -0.6262 0.05446 0.05176 -0.0279 1.0000 0.0121
-7.750 -0.6274 0.04656 0.04354 -0.0282 1.0000 0.0125
-7.500 -0.6273 0.03883 0.03538 -0.0269 1.0000 0.0127
-7.250 -0.6309 0.03013 0.02604 -0.0239 1.0000 0.0129
-7.000 -0.6195 0.02709 0.02270 -0.0219 1.0000 0.0131
-6.750 -0.6053 0.02488 0.02025 -0.0200 1.0000 0.0133
-6.500 -0.5775 0.02238 0.01743 -0.0209 0.9959 0.0136
-6.250 -0.5485 0.02053 0.01532 -0.0217 0.9920 0.0140
-6.000 -0.5188 0.01892 0.01346 -0.0225 0.9879 0.0145
-5.750 -0.4894 0.01692 0.01116 -0.0231 0.9836 0.0151
-5.500 -0.4601 0.01536 0.00935 -0.0236 0.9783 0.0156
-5.250 -0.4294 0.01422 0.00802 -0.0243 0.9733 0.0161
-5.000 -0.3994 0.01340 0.00707 -0.0249 0.9662 0.0165
-4.750 -0.3696 0.01269 0.00633 -0.0254 0.9583 0.0172
-4.500 -0.3393 0.01231 0.00592 -0.0260 0.9498 0.0179
-4.250 -0.3113 0.01193 0.00551 -0.0261 0.9394 0.0187
-4.000 -0.2839 0.01152 0.00504 -0.0259 0.9289 0.0197
-3.750 -0.2573 0.01115 0.00459 -0.0256 0.9171 0.0207
-3.500 -0.2316 0.01077 0.00415 -0.0250 0.9046 0.0219
-3.250 -0.2056 0.01053 0.00391 -0.0247 0.8930 0.0233
-3.000 -0.1791 0.01032 0.00368 -0.0243 0.8833 0.0248
-2.750 -0.1529 0.01008 0.00338 -0.0239 0.8736 0.0262
-2.500 -0.1263 0.00990 0.00316 -0.0236 0.8632 0.0275
-2.250 -0.1004 0.00956 0.00278 -0.0231 0.8535 0.0293
-2.000 -0.0741 0.00932 0.00251 -0.0228 0.8436 0.0311
-1.750 -0.0475 0.00916 0.00232 -0.0224 0.8316 0.0331
-1.500 -0.0208 0.00901 0.00212 -0.0221 0.8186 0.0347
-1.250 0.0059 0.00888 0.00194 -0.0218 0.8056 0.0361
-1.000 0.0328 0.00877 0.00178 -0.0215 0.7933 0.0374
-0.750 0.0596 0.00863 0.00161 -0.0212 0.7810 0.0417
-0.500 0.0865 0.00855 0.00149 -0.0209 0.7678 0.0470
-0.250 0.1132 0.00845 0.00139 -0.0206 0.7522 0.0621
0.000 0.1255 0.00627 0.00122 -0.0185 0.7369 0.6803
0.250 0.1489 0.00608 0.00125 -0.0173 0.7210 0.7675
0.500 0.1738 0.00600 0.00127 -0.0164 0.7052 0.8102
0.750 0.1985 0.00596 0.00130 -0.0154 0.6882 0.8491
1.000 0.2236 0.00597 0.00134 -0.0145 0.6676 0.8790
1.250 0.2491 0.00604 0.00137 -0.0137 0.6418 0.9035
1.500 0.2759 0.00615 0.00142 -0.0133 0.6133 0.9257
1.750 0.3045 0.00631 0.00147 -0.0133 0.5780 0.9433
2.000 0.3326 0.00661 0.00152 -0.0134 0.5196 0.9527
2.250 0.3612 0.00694 0.00161 -0.0137 0.4681 0.9620
2.500 0.3931 0.00716 0.00170 -0.0146 0.4367 0.9686
2.750 0.4240 0.00738 0.00180 -0.0154 0.3996 0.9759
3.000 0.4557 0.00773 0.00193 -0.0165 0.3480 0.9820
3.250 0.4873 0.00808 0.00208 -0.0176 0.2994 0.9878
3.500 0.5190 0.00853 0.00227 -0.0189 0.2433 0.9929
3.750 0.5510 0.00898 0.00249 -0.0202 0.1905 0.9971
4.000 0.5805 0.00938 0.00271 -0.0209 0.1507 1.0000
4.250 0.6033 0.00974 0.00293 -0.0201 0.1212 1.0000
4.500 0.6262 0.01009 0.00317 -0.0193 0.0977 1.0000
4.750 0.6495 0.01040 0.00341 -0.0185 0.0823 1.0000
5.000 0.6732 0.01070 0.00366 -0.0178 0.0715 1.0000
5.250 0.6969 0.01101 0.00392 -0.0172 0.0626 1.0000
5.500 0.7212 0.01128 0.00419 -0.0166 0.0561 1.0000
5.750 0.7453 0.01159 0.00448 -0.0160 0.0498 1.0000
6.000 0.7698 0.01189 0.00477 -0.0154 0.0448 1.0000
6.250 0.7940 0.01224 0.00511 -0.0149 0.0402 1.0000
6.500 0.8186 0.01255 0.00545 -0.0144 0.0370 1.0000
6.750 0.8427 0.01294 0.00582 -0.0139 0.0334 1.0000
7.000 0.8669 0.01332 0.00623 -0.0134 0.0308 1.0000
7.250 0.8912 0.01368 0.00664 -0.0129 0.0287 1.0000
7.500 0.9152 0.01411 0.00708 -0.0124 0.0267 1.0000
7.750 0.9381 0.01469 0.00767 -0.0117 0.0247 1.0000
8.000 0.9620 0.01511 0.00817 -0.0112 0.0239 1.0000
8.250 0.9855 0.01559 0.00871 -0.0107 0.0229 1.0000
8.500 1.0089 0.01607 0.00925 -0.0102 0.0217 1.0000
8.750 1.0320 0.01657 0.00979 -0.0096 0.0206 1.0000
9.000 1.0539 0.01723 0.01048 -0.0089 0.0196 1.0000
9.250 1.0747 0.01802 0.01134 -0.0081 0.0189 1.0000
9.500 1.0968 0.01862 0.01205 -0.0075 0.0184 1.0000
9.750 1.1186 0.01924 0.01276 -0.0068 0.0177 1.0000
10.000 1.1401 0.01987 0.01347 -0.0061 0.0170 1.0000
10.250 1.1612 0.02053 0.01420 -0.0054 0.0164 1.0000
10.500 1.1815 0.02124 0.01500 -0.0046 0.0158 1.0000
10.750 1.2008 0.02204 0.01586 -0.0038 0.0153 1.0000
11.000 1.2172 0.02312 0.01703 -0.0026 0.0147 1.0000
11.250 1.2345 0.02407 0.01810 -0.0016 0.0143 1.0000
11.500 1.2524 0.02490 0.01906 -0.0006 0.0139 1.0000
11.750 1.2688 0.02584 0.02012 0.0005 0.0134 1.0000
12.000 1.2836 0.02685 0.02127 0.0017 0.0130 1.0000
12.250 1.2963 0.02788 0.02242 0.0032 0.0126 1.0000
12.500 1.3069 0.02895 0.02361 0.0049 0.0123 1.0000
12.750 1.3166 0.03007 0.02483 0.0065 0.0120 1.0000
13.000 1.3248 0.03132 0.02617 0.0080 0.0117 1.0000
13.250 1.3301 0.03286 0.02781 0.0094 0.0114 1.0000
13.500 1.3305 0.03495 0.03002 0.0107 0.0111 1.0000
13.750 1.3316 0.03714 0.03237 0.0116 0.0108 1.0000
14.000 1.3340 0.03936 0.03476 0.0121 0.0106 1.0000
14.250 1.3337 0.04201 0.03759 0.0121 0.0104 1.0000
14.500 1.3312 0.04511 0.04086 0.0117 0.0102 1.0000
14.750 1.3262 0.04876 0.04470 0.0107 0.0101 1.0000
15.000 1.3186 0.05304 0.04916 0.0091 0.0099 1.0000
15.250 1.3084 0.05804 0.05433 0.0067 0.0098 1.0000
15.500 1.2946 0.06399 0.06045 0.0035 0.0097 1.0000
15.750 1.2769 0.07097 0.06762 -0.0006 0.0097 1.0000
16.000 1.2543 0.07918 0.07601 -0.0054 0.0097 1.0000
16.250 1.2259 0.08884 0.08585 -0.0109 0.0097 1.0000
16.500 1.1913 0.10020 0.09737 -0.0173 0.0098 1.0000
16.750 1.1491 0.11353 0.11088 -0.0246 0.0100 1.0000
17.000 1.0969 0.12979 0.12730 -0.0332 0.0103 1.0000
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