GIII BL0 AIRFOIL (giiia-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GIII BL0 AIRFOIL (giiia-il) Reynolds number: 500,000 Max Cl/Cd: 62.81 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-giiia-il-500000-n5.txt Download as CSV file: xf-giiia-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GIII BL0 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
------ -------- --------- --------- -------- -------- --------
-14.500 -0.9553 0.08258 0.08004 -0.0110 1.0000 0.0054
-14.250 -1.0032 0.06456 0.06174 -0.0243 1.0000 0.0053
-14.000 -1.0295 0.05596 0.05291 -0.0300 1.0000 0.0053
-13.750 -1.0492 0.04994 0.04667 -0.0328 1.0000 0.0053
-13.500 -1.0645 0.04535 0.04186 -0.0337 1.0000 0.0053
-13.250 -1.0757 0.04174 0.03803 -0.0332 1.0000 0.0053
-13.000 -1.0837 0.03878 0.03485 -0.0319 1.0000 0.0054
-12.750 -1.0879 0.03633 0.03219 -0.0300 1.0000 0.0054
-12.500 -1.0889 0.03426 0.02992 -0.0278 1.0000 0.0055
-12.250 -1.0935 0.03197 0.02743 -0.0248 1.0000 0.0056
-12.000 -1.0920 0.03023 0.02552 -0.0220 1.0000 0.0057
-11.750 -1.0858 0.02887 0.02402 -0.0194 1.0000 0.0059
-11.500 -1.0760 0.02774 0.02277 -0.0172 1.0000 0.0061
-11.250 -1.0627 0.02673 0.02165 -0.0155 1.0000 0.0063
-11.000 -1.0477 0.02582 0.02062 -0.0140 1.0000 0.0065
-10.750 -1.0317 0.02493 0.01963 -0.0125 1.0000 0.0068
-10.500 -1.0152 0.02405 0.01860 -0.0110 1.0000 0.0071
-10.250 -0.9985 0.02311 0.01753 -0.0095 1.0000 0.0075
-10.000 -0.9814 0.02221 0.01649 -0.0080 1.0000 0.0078
-9.750 -0.9637 0.02137 0.01551 -0.0065 1.0000 0.0080
-9.500 -0.9480 0.02033 0.01435 -0.0047 1.0000 0.0084
-9.250 -0.9315 0.01946 0.01340 -0.0029 1.0000 0.0088
-9.000 -0.9135 0.01885 0.01274 -0.0014 1.0000 0.0092
-8.750 -0.8957 0.01829 0.01212 0.0003 1.0000 0.0097
-8.500 -0.8786 0.01775 0.01151 0.0022 1.0000 0.0102
-8.250 -0.8621 0.01723 0.01090 0.0042 1.0000 0.0108
-8.000 -0.8459 0.01679 0.01038 0.0063 1.0000 0.0114
-7.750 -0.8196 0.01612 0.00964 0.0062 0.9977 0.0122
-7.500 -0.7903 0.01550 0.00899 0.0054 0.9950 0.0134
-7.250 -0.7609 0.01502 0.00847 0.0048 0.9920 0.0144
-7.000 -0.7313 0.01453 0.00793 0.0041 0.9889 0.0155
-6.750 -0.6992 0.01410 0.00742 0.0029 0.9861 0.0165
-6.500 -0.6683 0.01349 0.00678 0.0019 0.9807 0.0186
-6.250 -0.6344 0.01304 0.00632 0.0004 0.9746 0.0207
-6.000 -0.6042 0.01266 0.00588 -0.0003 0.9659 0.0226
-5.750 -0.5746 0.01227 0.00545 -0.0008 0.9591 0.0252
-5.500 -0.5470 0.01188 0.00506 -0.0009 0.9519 0.0290
-5.250 -0.5191 0.01159 0.00472 -0.0010 0.9459 0.0321
-5.000 -0.4930 0.01127 0.00440 -0.0007 0.9388 0.0375
-4.750 -0.4661 0.01099 0.00411 -0.0006 0.9329 0.0443
-4.500 -0.4410 0.01069 0.00385 -0.0001 0.9258 0.0552
-4.000 -0.3909 0.01009 0.00336 0.0009 0.9119 0.0916
-3.500 -0.3414 0.00950 0.00297 0.0020 0.8979 0.1488
-3.250 -0.3163 0.00926 0.00278 0.0025 0.8900 0.1757
-3.000 -0.2915 0.00904 0.00261 0.0032 0.8789 0.2004
-2.750 -0.2674 0.00877 0.00243 0.0039 0.8664 0.2363
-2.500 -0.2449 0.00835 0.00223 0.0049 0.8531 0.3009
-2.250 -0.2312 0.00729 0.00191 0.0074 0.8393 0.4976
-2.000 -0.2114 0.00688 0.00179 0.0091 0.8241 0.5916
-1.750 -0.1888 0.00667 0.00170 0.0103 0.8078 0.6419
-1.500 -0.1651 0.00653 0.00161 0.0114 0.7877 0.6767
-1.250 -0.1413 0.00643 0.00152 0.0124 0.7566 0.7063
-1.000 -0.1187 0.00643 0.00142 0.0138 0.7096 0.7336
-0.750 -0.0960 0.00649 0.00138 0.0150 0.6660 0.7601
-0.250 -0.0475 0.00663 0.00141 0.0168 0.5991 0.8131
0.000 -0.0217 0.00672 0.00146 0.0173 0.5725 0.8367
0.250 0.0050 0.00682 0.00152 0.0177 0.5502 0.8573
0.500 0.0317 0.00694 0.00158 0.0180 0.5278 0.8742
0.750 0.0588 0.00708 0.00165 0.0183 0.5047 0.8889
1.000 0.0867 0.00724 0.00174 0.0183 0.4813 0.9004
1.250 0.1142 0.00739 0.00180 0.0184 0.4579 0.9089
1.500 0.1421 0.00756 0.00187 0.0184 0.4290 0.9153
1.750 0.1679 0.00779 0.00194 0.0187 0.3854 0.9219
2.000 0.1960 0.00811 0.00206 0.0185 0.3395 0.9265
2.250 0.2205 0.00846 0.00218 0.0190 0.2815 0.9329
2.500 0.2484 0.00879 0.00234 0.0188 0.2437 0.9372
2.750 0.2776 0.00904 0.00249 0.0184 0.2229 0.9410
3.250 0.3322 0.00941 0.00276 0.0184 0.2003 0.9502
3.500 0.3635 0.00961 0.00293 0.0175 0.1927 0.9527
3.750 0.3938 0.00977 0.00309 0.0169 0.1871 0.9556
4.000 0.4217 0.00996 0.00325 0.0168 0.1823 0.9595
4.250 0.4491 0.01013 0.00343 0.0168 0.1787 0.9632
4.500 0.4814 0.01030 0.00362 0.0156 0.1756 0.9649
4.750 0.5133 0.01048 0.00382 0.0146 0.1723 0.9667
5.000 0.5444 0.01068 0.00404 0.0137 0.1689 0.9688
5.250 0.5732 0.01091 0.00427 0.0133 0.1662 0.9718
5.500 0.6009 0.01108 0.00449 0.0132 0.1636 0.9749
5.750 0.6337 0.01124 0.00465 0.0118 0.1562 0.9761
6.000 0.6656 0.01147 0.00489 0.0107 0.1496 0.9776
6.250 0.6974 0.01161 0.00507 0.0096 0.1422 0.9795
6.500 0.7281 0.01182 0.00527 0.0087 0.1324 0.9820
6.750 0.7575 0.01206 0.00548 0.0081 0.1155 0.9853
7.000 0.7865 0.01316 0.00614 0.0068 0.0434 0.9874
7.250 0.8171 0.01384 0.00675 0.0056 0.0256 0.9897
7.500 0.8464 0.01435 0.00727 0.0049 0.0191 0.9920
7.750 0.8736 0.01487 0.00781 0.0045 0.0156 0.9941
8.000 0.9024 0.01537 0.00838 0.0038 0.0136 0.9954
8.250 0.9308 0.01586 0.00894 0.0032 0.0122 0.9967
8.500 0.9584 0.01645 0.00959 0.0027 0.0109 0.9982
8.750 0.9849 0.01720 0.01042 0.0023 0.0096 0.9997
9.000 1.0039 0.01768 0.01097 0.0036 0.0090 1.0000
9.250 1.0192 0.01820 0.01156 0.0056 0.0084 1.0000
9.500 1.0335 0.01877 0.01219 0.0078 0.0080 1.0000
9.750 1.0470 0.01937 0.01286 0.0101 0.0076 1.0000
10.000 1.0588 0.02004 0.01360 0.0127 0.0072 1.0000
10.250 1.0675 0.02091 0.01456 0.0156 0.0068 1.0000
10.500 1.0748 0.02181 0.01555 0.0188 0.0066 1.0000
10.750 1.0841 0.02255 0.01640 0.0216 0.0064 1.0000
11.000 1.0919 0.02337 0.01732 0.0246 0.0063 1.0000
11.250 1.0976 0.02426 0.01830 0.0278 0.0061 1.0000
11.500 1.1001 0.02515 0.01929 0.0314 0.0059 1.0000
11.750 1.1038 0.02616 0.02040 0.0345 0.0057 1.0000
12.000 1.1087 0.02729 0.02163 0.0369 0.0055 1.0000
12.250 1.1138 0.02855 0.02299 0.0389 0.0053 1.0000
12.500 1.1190 0.02993 0.02446 0.0406 0.0052 1.0000
12.750 1.1234 0.03148 0.02612 0.0419 0.0050 1.0000
13.000 1.1268 0.03326 0.02800 0.0428 0.0049 1.0000
13.250 1.1286 0.03535 0.03022 0.0434 0.0047 1.0000
13.500 1.1274 0.03794 0.03292 0.0435 0.0046 1.0000
13.750 1.1233 0.04117 0.03628 0.0430 0.0045 1.0000
14.000 1.1163 0.04509 0.04035 0.0417 0.0045 1.0000
14.250 1.1071 0.04967 0.04508 0.0397 0.0044 1.0000
14.500 1.0958 0.05480 0.05036 0.0372 0.0044 1.0000
14.750 1.0823 0.06045 0.05616 0.0344 0.0043 1.0000
15.000 1.0705 0.06602 0.06186 0.0316 0.0043 1.0000
15.250 1.0578 0.07191 0.06788 0.0286 0.0043 1.0000
15.500 1.0439 0.07808 0.07419 0.0255 0.0043 1.0000
15.750 1.0297 0.08449 0.08072 0.0222 0.0043 1.0000
16.000 1.0151 0.09103 0.08738 0.0190 0.0043 1.0000
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