GIII BL0 AIRFOIL (giiia-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GIII BL0 AIRFOIL (giiia-il) Reynolds number: 1,000,000 Max Cl/Cd: 77.16 at α=6.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-giiia-il-1000000.txt Download as CSV file: xf-giiia-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.250 -1.0122 0.06265 0.06050 -0.0252 1.0000 0.0061
-14.000 -1.0488 0.05275 0.05033 -0.0315 1.0000 0.0061
-13.750 -1.0689 0.04708 0.04445 -0.0336 1.0000 0.0061
-13.500 -1.0813 0.04312 0.04033 -0.0340 1.0000 0.0061
-13.250 -1.0909 0.03991 0.03695 -0.0331 1.0000 0.0061
-13.000 -1.0958 0.03743 0.03433 -0.0317 1.0000 0.0062
-12.750 -1.0993 0.03524 0.03198 -0.0296 1.0000 0.0063
-12.500 -1.1004 0.03334 0.02993 -0.0272 1.0000 0.0064
-12.250 -1.0994 0.03166 0.02810 -0.0246 1.0000 0.0064
-12.000 -1.0959 0.03017 0.02647 -0.0219 1.0000 0.0066
-11.750 -1.0914 0.02870 0.02484 -0.0191 1.0000 0.0067
-11.500 -1.0834 0.02729 0.02327 -0.0166 1.0000 0.0068
-11.250 -1.0725 0.02592 0.02175 -0.0146 1.0000 0.0070
-11.000 -1.0596 0.02467 0.02034 -0.0127 1.0000 0.0071
-10.750 -1.0453 0.02349 0.01900 -0.0109 1.0000 0.0073
-10.500 -1.0295 0.02244 0.01782 -0.0093 1.0000 0.0075
-10.250 -1.0122 0.02155 0.01681 -0.0078 1.0000 0.0077
-10.000 -0.9935 0.02084 0.01600 -0.0064 1.0000 0.0078
-9.750 -0.9830 0.01904 0.01398 -0.0038 1.0000 0.0082
-9.500 -0.9687 0.01796 0.01281 -0.0016 1.0000 0.0086
-9.250 -0.9504 0.01749 0.01230 0.0000 1.0000 0.0090
-9.000 -0.9324 0.01707 0.01185 0.0017 1.0000 0.0094
-8.750 -0.9158 0.01662 0.01135 0.0037 1.0000 0.0098
-8.500 -0.9012 0.01615 0.01082 0.0062 1.0000 0.0102
-8.250 -0.8890 0.01569 0.01030 0.0091 1.0000 0.0105
-8.000 -0.8628 0.01523 0.00978 0.0091 0.9989 0.0108
-7.750 -0.8344 0.01406 0.00849 0.0085 0.9968 0.0117
-7.500 -0.8013 0.01343 0.00784 0.0070 0.9950 0.0126
-7.250 -0.7669 0.01298 0.00735 0.0053 0.9926 0.0135
-7.000 -0.7330 0.01256 0.00690 0.0038 0.9893 0.0144
-6.750 -0.6995 0.01203 0.00632 0.0023 0.9866 0.0155
-6.500 -0.6668 0.01144 0.00571 0.0010 0.9842 0.0173
-6.250 -0.6354 0.01110 0.00534 0.0000 0.9807 0.0188
-6.000 -0.6059 0.01083 0.00505 -0.0004 0.9753 0.0200
-5.750 -0.5770 0.01029 0.00449 -0.0008 0.9710 0.0233
-5.500 -0.5490 0.01004 0.00423 -0.0009 0.9656 0.0260
-5.250 -0.5230 0.00969 0.00386 -0.0006 0.9590 0.0303
-5.000 -0.4963 0.00943 0.00360 -0.0004 0.9531 0.0349
-4.750 -0.4719 0.00912 0.00333 0.0003 0.9457 0.0436
-4.500 -0.4465 0.00885 0.00309 0.0008 0.9398 0.0561
-4.250 -0.4223 0.00854 0.00286 0.0015 0.9327 0.0766
-4.000 -0.3980 0.00823 0.00265 0.0022 0.9258 0.1052
-3.750 -0.3741 0.00795 0.00248 0.0030 0.9165 0.1370
-3.500 -0.3495 0.00771 0.00232 0.0037 0.9075 0.1664
-3.250 -0.3248 0.00747 0.00216 0.0043 0.8981 0.1973
-3.000 -0.3003 0.00720 0.00201 0.0050 0.8885 0.2352
-2.750 -0.2768 0.00685 0.00184 0.0058 0.8795 0.2933
-2.500 -0.2585 0.00605 0.00157 0.0075 0.8696 0.4393
-2.250 -0.2399 0.00544 0.00143 0.0093 0.8598 0.5778
-2.000 -0.2166 0.00521 0.00134 0.0103 0.8497 0.6313
-1.750 -0.1933 0.00503 0.00127 0.0114 0.8373 0.6761
-1.500 -0.1689 0.00491 0.00119 0.0122 0.8224 0.7077
-1.000 -0.1204 0.00469 0.00108 0.0141 0.7852 0.7687
-0.750 -0.0965 0.00464 0.00104 0.0151 0.7535 0.7968
-0.500 -0.0734 0.00469 0.00101 0.0163 0.7090 0.8231
-0.250 -0.0492 0.00479 0.00103 0.0172 0.6729 0.8451
0.000 -0.0242 0.00490 0.00106 0.0179 0.6392 0.8637
0.250 0.0013 0.00502 0.00110 0.0185 0.6095 0.8797
0.500 0.0274 0.00514 0.00116 0.0190 0.5840 0.8934
0.750 0.0540 0.00526 0.00122 0.0193 0.5609 0.9049
1.000 0.0801 0.00539 0.00127 0.0198 0.5379 0.9153
1.250 0.1066 0.00555 0.00135 0.0202 0.5145 0.9244
1.500 0.1342 0.00570 0.00144 0.0203 0.4917 0.9323
1.750 0.1595 0.00587 0.00153 0.0209 0.4681 0.9404
2.000 0.1878 0.00606 0.00162 0.0208 0.4371 0.9449
2.250 0.2154 0.00634 0.00172 0.0208 0.3882 0.9489
2.500 0.2394 0.00668 0.00185 0.0215 0.3364 0.9543
2.750 0.2649 0.00714 0.00202 0.0217 0.2619 0.9580
3.000 0.2949 0.00749 0.00220 0.0210 0.2254 0.9604
3.250 0.3253 0.00774 0.00236 0.0204 0.2074 0.9631
3.500 0.3539 0.00792 0.00250 0.0201 0.1976 0.9665
3.750 0.3798 0.00808 0.00264 0.0205 0.1910 0.9704
4.000 0.4139 0.00825 0.00278 0.0190 0.1853 0.9715
4.250 0.4478 0.00847 0.00297 0.0175 0.1791 0.9725
4.500 0.4825 0.00860 0.00312 0.0159 0.1768 0.9734
4.750 0.5165 0.00875 0.00328 0.0143 0.1741 0.9746
5.000 0.5496 0.00892 0.00345 0.0130 0.1707 0.9760
5.250 0.5812 0.00913 0.00364 0.0120 0.1639 0.9778
5.500 0.6119 0.00922 0.00375 0.0112 0.1601 0.9800
5.750 0.6379 0.00938 0.00390 0.0115 0.1549 0.9832
6.000 0.6718 0.00953 0.00405 0.0099 0.1486 0.9839
6.250 0.7058 0.00964 0.00416 0.0084 0.1421 0.9847
6.500 0.7391 0.00979 0.00431 0.0070 0.1335 0.9856
6.750 0.7716 0.01000 0.00444 0.0056 0.1155 0.9867
7.000 0.7960 0.01130 0.00524 0.0053 0.0329 0.9887
7.250 0.8251 0.01188 0.00576 0.0046 0.0202 0.9905
7.500 0.8546 0.01238 0.00628 0.0039 0.0162 0.9925
7.750 0.8854 0.01282 0.00674 0.0029 0.0140 0.9944
8.000 0.9190 0.01342 0.00741 0.0012 0.0121 0.9956
8.250 0.9523 0.01385 0.00788 -0.0004 0.0111 0.9969
8.500 0.9835 0.01434 0.00840 -0.0016 0.0102 0.9982
8.750 1.0113 0.01518 0.00933 -0.0022 0.0092 0.9995
9.000 1.0317 0.01594 0.01018 -0.0013 0.0088 1.0000
9.250 1.0478 0.01641 0.01072 0.0006 0.0085 1.0000
9.500 1.0625 0.01694 0.01132 0.0028 0.0082 1.0000
9.750 1.0759 0.01751 0.01195 0.0052 0.0079 1.0000
10.000 1.0883 0.01810 0.01261 0.0078 0.0077 1.0000
10.250 1.1000 0.01869 0.01325 0.0105 0.0074 1.0000
10.500 1.1110 0.01928 0.01389 0.0132 0.0071 1.0000
10.750 1.1201 0.01995 0.01461 0.0162 0.0068 1.0000
11.000 1.1222 0.02098 0.01574 0.0203 0.0066 1.0000
11.250 1.1104 0.02280 0.01770 0.0263 0.0063 1.0000
11.500 1.1175 0.02336 0.01832 0.0295 0.0062 1.0000
11.750 1.1210 0.02412 0.01917 0.0331 0.0061 1.0000
12.000 1.1258 0.02511 0.02025 0.0360 0.0060 1.0000
12.250 1.1307 0.02630 0.02154 0.0384 0.0059 1.0000
12.500 1.1348 0.02769 0.02303 0.0404 0.0058 1.0000
12.750 1.1377 0.02932 0.02476 0.0422 0.0057 1.0000
13.000 1.1396 0.03116 0.02672 0.0436 0.0056 1.0000
13.250 1.1402 0.03328 0.02896 0.0446 0.0056 1.0000
13.500 1.1398 0.03568 0.03149 0.0451 0.0055 1.0000
13.750 1.1377 0.03847 0.03440 0.0452 0.0054 1.0000
14.000 1.1346 0.04166 0.03772 0.0446 0.0054 1.0000
14.250 1.1299 0.04530 0.04150 0.0435 0.0053 1.0000
14.500 1.1239 0.04938 0.04572 0.0418 0.0053 1.0000
14.750 1.1161 0.05391 0.05038 0.0397 0.0052 1.0000
15.000 1.1069 0.05881 0.05542 0.0373 0.0052 1.0000
15.250 1.0948 0.06428 0.06102 0.0345 0.0052 1.0000
15.500 1.0813 0.07016 0.06703 0.0314 0.0052 1.0000
15.750 1.0656 0.07658 0.07359 0.0281 0.0052 1.0000
16.000 1.0497 0.08332 0.08045 0.0245 0.0052 1.0000
16.250 1.0324 0.09045 0.08771 0.0208 0.0052 1.0000
16.500 1.0136 0.09809 0.09548 0.0168 0.0052 1.0000
16.750 0.9946 0.10599 0.10351 0.0127 0.0052 1.0000
17.000 0.9737 0.11443 0.11207 0.0083 0.0053 1.0000
17.250 0.9518 0.12337 0.12112 0.0037 0.0053 1.0000
17.500 0.9295 0.13262 0.13050 -0.0011 0.0054 1.0000
17.750 0.9032 0.14329 0.14130 -0.0066 0.0055 1.0000
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